Proposed is a dual-mode sensor for use aboard unmanned aircraft for safe operation in the NAS that:
1.	Incorporates high resolution Millimeter Wave radar with high resolution Electro-Optical sensor.
2.	Achieves complete real time, full time spherical coverage around the UAS platform by employing two hemispherical dual mode sensors, one directed forward and one directed to the rear.[which exceeds the detection range and field-of-regard (FOR) for all nearby air platforms in FAA Regulation 7610.4 and other requirements from DOD/FAA documents].
3.	Utilizes multiple coherent transceivers.
4.	Meets SWaP and cost requirements for most UASs, including price (less than $3000 in quantity), size (less than 1 cubic feet), weight (less than 2 lb) and power (less than 10W).
5.	Leverages as needed the Automatic Dependent Surveillance Broadcast (ADS-B), which will be implemented by the FAA in the NAS. 
6.	Considers aircraft that operate without ADS-B.
7.	Performs multiple functions; including autonomous detection, tracking, predicting of future track and specification of collision avoiding maneuvers.
8.	Is self-contained, with sensor capability combined with on-board computing and flight control system, yet can be operated with sense and avoid interoperability.
High bandwidth communication links are needed between satellites and ground stations, inter-satellite, and to airborne assets.  As data loads increase and satellites available payloads decrease keeping the information flowing becomes even more challenging.   In this SBIR program we will design and demonstrate the feasibility of ultra-low Size, Weight, and Power (SWaP) Micro-Laser Communications (MiLC) modules for high bandwidth (up to Gbps or possibly much higher)  data links between miniature satellites (e.g. cube-sats),  and ground stations, satellite clusters, and/or airborne assets.  One possible laser comm. modules will fit within a few cubic inch volume, require less than 1 watt of power and be able to provide ground station tracking (including orbital motion over wide angles and jitter correction) with a &gt;100 Mbps downlink and no moving parts. Higher bandwidths are possible with trade-offs. This will be enabled by replacing heavy and power consumptive mechanical scanners with new, game changing wide angle (120o x 120o), electro-optic laser scanners.
TUI proposes to develop and demonstrate a process for fabricating high-performance composite truss structures on-orbit and integrating them with thin film solar cell assemblies to enable the deployment of very large solar arrays with lower cost and increased power-per-mass than SOA array technologies.  On-orbit fabrication enables order-of-magnitude improvements in packing efficiency compared to state of the art deployables technologies such as coilable booms, deployable masts, and inflatable structures, and also enables geometric optimizations to provide order-of-magnitude improvements in structural performance.  The proposed effort will build upon an existing TRL-3 truss-fabrication mechanism design, called the "Trusselator", which adapts techniques used in 3D printing and automated fiber placement to fabricate arbitrarily-long composite trusses using compactly-wound spools of textile materials as a feedstock. The Phase I SBIR effort will evolve this design to enable fabrication of high-performance truss structures using space-worthy materials, and develop methods for integrating these truss structures with solar cell blankets and the necessary wiring.  The Phase II effort will prepare an advanced prototype and mature it to TRL-5 through environmental testing in the lab, preparing it for orbital validation testing in follow-on efforts.
The program leverages on our extensive expertise in developing high-performance driver ASICs for deformable mirror systems and seeks to expand the capacities of the proposed novel ASIC technology to beyond what have been possible by using traditional techniques. The overall goal of the SBIR program will be to develop a new class of Application Specified Integrated Circuit (ASIC) driver technology to be used in driver electronics of a deformable mirror (DM) system for reducing power dissipation, improving controllability, enforcing multiplexing bandwidth, and significantly reducing the form factors of the entire DM system for adaptive optics. Through the Phase I project, we aims to transform the technology readiness level from TRL 1 to TRL 2, and in Phase II, the technology readiness level for the proposed ASIC driver system will be promoted from TRL 2 to TRL 4 within a 2-year time frame.
Based on the recent success of the Mars Exploration Program and the Mars Science Laboratory mission, NASA has a desire to expand on the technology developed under each effort in order to increase future mission capabilities, namely an increase in payload capacity for entry to Mars, Venus and other Outer-Planets. Such a goal requires an innovative solution to the vehicle's entry, decent and landing system (EDL). In order to address this goal,NASA has recently invested in the development of low ballistic coefficient aeroshell technology concepts which typically consist of a flexible 3D woven carbon cloth that can be stowed during flight and deployed to serve as a semi-rigid aeroshell on atmospheric entry. The ability of individual groups of fibers within yarn bundles to undulate in multiple orientations relative to the major axis of the yarn bundle results in full anisotropy for the 3D woven preforms. In addition to adding more complexity to the accompanying analytical models, the testing of such materials is also complicated as compared to isotropic and transversely orthotropic materials.  Within the proposed Phase I effort, Materials Research &amp; Design will develop test methods for the materials characterization of a hybrid, woven 3D fabric for use in a flexible TPS application. The program willinvolve analytical, fabrication and experimental tasks to achieve the overall program goal of maturing technologies for advanced EDL systems. A few select tests will be performed at Southern Research Institute with strain data being captured for use in the anisotropic compliance matrix calculations. Finite element simulations, using a homogeneous representation of the anisotropic material, will be used to simulate each test and aide in the design of test specimens sufficient to generate measurable strain levels while simultaneously allowing the anisotropic material to deform naturally.
Sustainable Innovations, LLC, is developing an Electrochemical Methane Generator (EMG), which comprises a novel method of converting CO2 and H2O to hydrocarbon fuels (such as methane) and O2. When powered by a renewable energy source, such as solar or wind power, it can provide a method for producing high quality fuels in a distributed fashion. This is accomplished by harvesting CO2 from the atmosphere and processing it electrochemically to release methane fuel and water. Sustainable Innovations' EMG technology has the potential to lead to a global sustainable energy infrastructure and could also play a pivotal role in achieving both the energy and the life support needs of extraterrestrial bases.  For example, the Martian atmosphere, which is predominately CO2, can be directly used as a feedstock for the production of both fuel and water.  The water can then be recycled to produce breathing oxygen.
Under this proposed effort, we plan to test the feasibility of adapting our terrestrial jammer locator system (JLOC) to locating jamming signals in space by adapting our previously developed GPS software defined radio (SDR) technology to provide an SDR waveform that can operate on spacecraft to allow detection and identification of GPS interference.  We shall also experiment with this waveform to determine how the motion of a low earth orbiting platform can be used to provide geolocation of the interference source.
To enable future robotic exploration systems to have greater mobility, sensing, sampling, and communication capabilities on difficult terrain such as craters, cliffs, gullies, and skylights, Tethers Unlimited proposes to develop a "Sensing and Positioning on Inclines and Deep Environments with Retrieval" (SPIDER) system.  This system employs an innovative lightweight 'orbital winch' with the capacity for rapid tether deployment and high load retrieval or towing.  The unique design of the orbital winch accomplishes cable winding and deployment without rotating the spool, minimizing mass and power consumption, while eliminating the need for electrical and optical slip-ring.  The SPIDER system also integrates a launcher that can be used to deploy a wide variety of tethered end-effectors to provide new capabilities for sample retrieval and sensing.  A carousel of these stowed end-effectors will allow selection of appropriate implements for a desired task.  For example, tethered anchor end-effectors could give planetary rovers the ability to rappel down ravines, tow themselves up steep slopes, or free themselves from a stuck position.  Sensing and sampling end-effectors with data- and power- transmitting tethers can be deployed and retrieved from otherwise inaccessible areas, giving in-situ feedback via optical fibers.  The SPIDER system can also be a launch platform for subsurface boring or ice-penetrating probes such as the Cryobot.  Moreover, by launching an RF transmitter/receiver, the system could improve communications for a planetary rover entering a geologic feature that would impede radio contact, such as a lava tube. The Phase I effort will mature the SPIDER to TRL 4 by testing prototypes of key components, and the Phase II will mature an integrated system to TRL 6 by testing and qualifying a prototype in a relevant terrestrial environment.
The proposed technology is a revolutionary solar array advancement that relies on a structurally optimized platform to provide unparalleled specific-performance and affordability for extremely large area solar arrays.  The proposed technology is comprised of a central beam tensioned membrane architecture that leverages key heritage technology elements to provide low-risk and high end-user acceptance. The proposed technology will enable emerging Solar Electric Propulsion Space Science and Exploration missions through ultra-affordability, ultra-lightweight, ultra-compact stowage volume, design simplicity, robustness and high damage tolerance, broad scalability, high strength/stiffness, high voltage and high/low temperature operation capability within many environments. Once completely optimized through the proposed SBIR program the proposed technology promises to provide NASA/industry a near-term and low-risk solar array system that provides revolutionary performance in terms of high specific power (&gt;300 up to 500 W/kg BOL at the wing level, PV-blanket dependent), affordability (up to 40&#37; cost savings at the array level, PV-blanket dependent), ultra-lightweight, high deployed stiffness (10X better than current arrays), high deployed strength (10X better than current arrays), compact stowage volume (&gt;70-80 kW/m3 BOL, 10X times better than current arrays), high reliability, high radiation tolerance, high voltage operation capability (&gt;200 VDC), scalability (500W to 100's of kW), and LILT/HIHT operation.
ORBITEC proposes to develop and demonstrate the innovative Acoustic Resonance Reaction Control Thruster (ARCTIC) to provide rapid and reliable in-space impulse without the use of toxic hypergols, delicate catalyst beds, or cumbersome spark systems. The ARCTIC thruster will exceed current reliability standards, reduce RCS complexity, and provide system-level benefits by minimizing weight, decreasing power requirements, and improving serviceability.  The Phase I work will focus on the development and testing, both at sea level and vacuum conditions, of a prototype ARCTIC thruster, as well as the design of flight-weight ARCTIC thruster for Phase II implementation.
ANSIBLE (A Network of Social Interactions for Bilateral Life Enhancement) can be used pre, during, and post flight to connect the flight crew with their family, friends, and the ground crew to provide a sense of social consistency and permanence. ANSIBLE is a multi-modal toolset that 1) adapts, rearranges, and modifies human interaction streams to minimize the disruptive impact of communication latencies and 2) leverages virtual worlds (VW) to provide a space where humans and intelligent virtual agents (VA) can be companions, advisors, provided psychological support, and share experiences.  VAs capable of detecting changes in astronaut psychosocial states can increase astronaut self-awareness, suggest countermeasures, and provide rehearsal scenarios to maintain and enhance interpersonal skills.  University of Southern California(USC)'s Institute of Creative Technologies (ICT) have been at the forefront of applying VWs and VAs to training, therapy, and even detection of depression.  SIFT will leverage its ongoing work with NASA's BHP group in unobtrusive detection of psychosocial dimensions, and  work together with Dr. Jacquelyn Morie to apply and enhance these technologies to define the future social landscape that connects the flight crew with Earth.
We propose a next-generation cloud-based social media visual analytics disaster response system that will enable decision-makers and first-responders to obtain real-time analytics (both descriptive and predictive) for situational awareness and early-warning. Social media sites like Twitter and Facebook provide rapid "sensory" feedback from "human sensors" &amp;#150; the millions of people on the ground including those affected by the disaster as well as hundreds of first-responders and relief organizations. The problem is that this social media data can be overwhelming and noisy (lots of irrelevant stuff). Our proposed innovation is to combine and analyze this social media unstructured "big-data", together with other structured data from a variety of sources including NASA. The emphasis is on visual analytics which will allow all these diverse geospatial data to be integrated and analyzed on a real-time basis in an intuitive manner. We utilize geobrowsers such as COAST, Google Earth, and OpenStreetMap for display of the output of the visual analytics prediction system. This is an interactive system which enables the relevant users and decision-makers to provide input to the analytics process as the solution evolves.
The utility of stereoscopic 3D image representation in many applications is now well established.  It is not just a matter of stereo being better than 2D, but of stereo being necessary to interpret representations of complex data sets, physical phenomena, engineering designs and position in space.  The US Air Force has long recognized the potential for 3D displays in the cockpit but until now the limitations of 3D display technology have prevented implementation.  Interest in 3D image display has recently surfaced among SPAWAR and among agencies who use helicopters and firms that make camera systems for helicopters for use in power line inspection, law enforcement, and military applications. There is also interest in the use of plane mounted cameras in collision avoidance while taxiing on runways, where 3D display may be of benefit because it can show the pilot how much room there is between the plane and obstacles. 3D displays for these applications must be of the glasses free type, but current embodiments of such displays possess extremely low resolution, produce visual artifacts, and tend to produce very narrow viewing areas.  Under a recent DOE SBIR Phase II contract DTI developed a new glasses free 2D/3D switchable display that avoids the resolution loss, visual artifacts, and viewing restrictions associated with all other autostereoscopic displays, providing full HD resolution in 3D as well as in a 2D viewing mode.  DTI's believes that this new technology can lead to the first practical implementation of a 3D display in the cockpit. During this Phase I program DTI will investigate the adaptation of its 2D/3D displays to cockpit displays through compact design, ruggedizing, and the development of mechanical, electronic, computer, and software interfaces to an aircraft system.  This investigation will lead to a high level design and specification for a prototype display that can developed in Phase II and delivered for testing in a cockpit or simulator.
Sustainable Innovations has developed an innovative concept for highly efficient, reliable, potable water production based on technology from a commercial line of hydrogen recovery and compression systems the company is developing.   This Electrochemical Dehumidification and Life Support System (EDLS) system utilizes a small amount of hydrogen as a working fluid, operating in a sealed cavity, and leverages a hydrogen compression cycle to provide the driving force to both remove water from the local environment, passing it into a dry hydrogen stream, and condense pure, potable drinking water.  The hydrogen compression cycle used in this process is highly efficient, approaching the efficiency of an ideal isothermal compression process, and can be achieved without moving parts.  This technology could play a key role in critical NASA environmental control and life support applications.
Modern aircraft gas turbine engines utilize highly loaded airfoils in both the compressor and turbine to maximize performance while minimizing weight, cost, and complexity.  However, high airfoil loading increases the likelihood of flow separation at lower mass flow rates.  Dielectric Barrier Discharge (DBD) plasma actuators have been shown to be a very promising technique for compressor stall control.  DBD devices can either be installed directly on rotor/stator surfaces or the compressor end walls to control rotor tip flow.  A fundamental challenge in driving DBD actuators is providing appropriate electrical waveforms to the devices.  Creare proposes the development of an innovative DBD actuator charging circuit topology which enables (1) low voltage DC power distribution, (2) a modular approach to achieving total power delivery, (3) use of commercial-off-the-shelf (COTS) components, and (4) resolution of impedance matching issues associated with other DBD charging circuit topologies.
While it has become apparent that we can and will collect data at unprecedented rates thanks to a wide range of high-resolution high-throughput sensors, it has also become apparent that we do not have the algorithms and tools to satisfactorily analyze Big Data. Cloud computing as an infrastructure (e.g., Amazon Web Services), as a platform (e.g., Google Apps), and as a software ecosystem (e.g., Hadoop/MapReduce and NoSQL tools) offers a promising compute-and-store environment (complementary to supercomputing) to handle the massive amount of data created by NASA missions. In this proposal, we will develop a Cloud-based open architecture Analytics, Store and QUEry (CASQUE) system for data-intensive scientific computing for NASA missions. The architecture and workflow will be tailored for specific NASA missions and will be thoroughly tested in large-scale relevant cloud environments.
A novel composite material ablative TPS for planetary vehicles that can survive a dual heating exposure is proposed. NextGen's TPS concept is a bi-layer functional composite. The top ablative layer is a two polymer composite layer formed in a conformal shape by infiltrating ablative polymer in a Si based polymeric foam with controlled pore size distribution.  This layer is for the aerocapture portion of the mission. Underneath it is a ceramic foam core sandwiched between a top ceramic ply and the bottom structural laminated composite substrate. This layer is for the entry portion of the mission. The Si based polymer foam core is similar to the top layer but is already pyrolyzed and is not infiltrated with ablative polymer. The proposed TPS when subjected to aerodynamic heating at high integrated heat loads the foam polymer structure pyrolyzes to the high temperature structure and the filled phenolic or epoxy resin will be charred and ablated. The TPS will be designed to minimize areal density while meeting bondline temperature and ablation rate requirements. The proposed TPS is easy to fabricate in aerodynamic body conformal shapes by simple manufacturing steps. The basis for the proposed concept is recent successful TPS development work performed by NextGen Aeronautics and the University of Washington under the Air Force program.
NASA is leading a large-scale effort to conduct research, develop standards, and integrate technologies to facilitate the insertion of Unmanned Aircraft Systems (UAS) into the National Airspace System (NAS). One area of development to support this effort is the adaptation of existing weather technologies for manned cockpits for use in UAS ground control stations (GCSs). However, the lack of a defined concept of operations (ConOps) and specific GCS technologies for UAS integration in the NAS present challenges for proposed weather information systems. Aptima proposes to develop WINDSUN (Weather Information Display System for UAS in the NAS) as a flexible system architecture and innovative library of platform-agnostic interaction methods to support integration with various ConOps and GCS technologies. A successful Phase I effort will include: (1) a use case with a ConOps to define the core set of tasks around which the design is built; (2) an innovative system architecture that is adaptable to multiple workflows; (3) user interface designs for interaction and visualization; (4) a demonstrable proof of concept physical prototype; and (5) transition plans (implementation, evaluation, and commercialization) for WINDSUN. Phase II efforts, including (1) GCS integration, (2) experimental evaluation, and (3) transition to operational environments.
The objective of the current research is to develop the concept, algorithms and software necessary for enabling a novel surveillance system for airports ramp areas. The proposed technology can overcome the deficiencies of some of current-day surveillance systems especially in the ramp area. It  is expected to aid in both Safety and Efficiency improvements in ramp area operations. Phase I research developed the concept and requirements and demonstrated the core algorithms of technology. Using a 1:400 scale realistic airport ramp area model the following features were demonstrated: (i) detection of aircraft in the ramp area and (iii) 3D localization of aircraft 3D inertial frame of reference to an accuracy of 40 ft. Phase II research seeks to refine and extend the detection algorithms to include ground vehicles; identify aircraft type; and even determine the orientation of the aircraft. The localization algorithms will be extended to decipher the 3D geometry of the aircraft. Data fusion algorithms will be developed to track aircraft as they move through the ramp area. A significant portion of Phase II research involves development of the complete software and testing it using realistic airport data.
Constructing, maintaining, and adapting operational procedures for manned space operations is a complex task, requiring the procedure author to satisfy constraints resulting from the system configuration, current state, and applicable flight rules. This Phase 1 SBIR project will establish the feasibility of the Constraint-Checking Editor for Procedure Tracking (ConCEPT), a constraint-checking system for procedures represented in the Procedure Representation Language (PRL) and authored in PrIDE. Using automated translation and Constraint Satisfaction Problem generation technologies developed on previous projects, ConCEPT will assist users in identifying conflicts and inconsistencies in procedures as they are developed.  The user edits a procedure in PrIDE, using procedure steps that have been annotated with information about resources and state changes.  Configuration information, current state, and flight rules are stored in and obtained from the System Description, an existing component of PrIDE.  As the procedure is being developed, ConCEPT automatically and continuously gathers appropriate constraints from the domain model and flight rules, translates them into a constraint satisfaction problem (CSP) which is then submitted to a CSP solver, which alerts the user to any violated constraints.  Phase I will define relevant scenarios of use, establish the applicability and feasibility of ConCEPT, and provide a proof-of-concept demonstration.
The current NASA spacesuit community is focusing on utilizing a 13" hemispherical helmet for the next generation of extravehicular activity spacesuits. This helmet architecture presents the end user with a myriad of positive attributes, including a large field of view, enhanced CO2 washout and improved component durability/operational life. The 13" Dome Helmet architecture has proven these attributes via the NASA MK-III and Z-1 advanced EVA spacesuit test beds. Air-Lock's 2012 SBIR proposal advances the 13" Dome Helmet from NASA prototype/test bed to EVA Acceptability for Use by enhancing the design with a fully functional Extravehicular Visor Assembly (EVVA).

Phase I will see Air-Lock engineers leverage current Helmet/EVVA technologies, infuse the design with lessons learned from the EMU Program and implement the resultant design into a 13" hemispherical helmet architecture; heretofore referred to as the Advanced Extravehicular Helmet Assembly (AEHA). In addition to the design facet of the Phase I task, Air-Lock engineers will develop a Verification and Validation Test Plan (V&amp;V) based on current EMU S/AD and CARD requirements along with higher Advanced EVA operating pressures (8.0 psi). This test plan will lay the foundation for Phase 2 Acceptability for Use testing to facilitate the use of the AEHA aboard the International Space Station in support of NASA's planned 2017 ISS Advanced Spacesuit Demonstration Test.
This proposal is for the development of a dynamic fault detection filter for a formation of satellites operating in a highly nonlinear dynamic environment but processed at a ground station where measurement data may be available on an intermittent basis.  A previous SBIR study demonstrates that nonlinearities have an adverse effect on a linear dynamic filter's ability to accurately declare faults.  Thus, a fault detection filter capable of effectively accounting for nonlinear dynamics and measurement data interruptions is required.  During the proposed Phase I effort, such filters will be designed for faults in the three translational modes of 4 satellites flying in formation near a highly elliptical orbit.  The satellites will carry a limited suite of instruments, just sufficient to determine faults in the three translational modes and include a GPS receiver.  Furthermore, communication with a ground station will only be available near perigee and the measurement data will be transmitted in bursts, which will introduce planned and unplanned communication blackouts that represent breaks in the time history of measurements.  The proposed development will produce a fault detection and isolation algorithm that can mitigate these breaks and perform faster than a simple, cyclical restart implementation.
For the proposed CoNNeCT experiment, Innoflight and John Hopkins University Applied Physics Laboratory (JHU/APL) have formed a significant complimentary union with respect to each one's expertise in space networking.  Innoflight is bringing forward design and development expertise in cryptographically secure Internet Protocol (IP) for space links per NSA specifications while JHU/APL brings formidable Disruption Tolerant Networking (DTN) protocol and application to run above the secure transport.  The two combined provide a high-value space communications solution that can be tested and refined using CoNNeCT.  In addition, each one separately provides its own independent solution for a large variety of commercial and government applications.
Busek proposes to develop a flight version of a high power Hall Effect thruster.  While numerous high power Hall Effect thrusters have been demonstrated in the laboratory, no flight qualified options exist.  The baseline thruster would be tentatively sized at the 15kW power level.  Busek proposes to work with NASA to improve upon laboratory designs by incorporating both NASA and Busek unique HET product knowledge.  Specific features to be implemented include the use of Hiperco magnetic alloy, improved magnet field distribution using magnetic shielding, high temperature magnet coils and an advanced propellant distribution methodology.  Particular attention will be paid to thruster lifetime through a combination of magnetic modeling and erosion analysis using the JPL developed Hall-2DE code.  
In Phase I, we will prepare a detailed engineering design of the baseline thruster  Using internal funds and therefore at no cost to the Phase I effort, Busek will procure the Hiperco raw material for the thruster, have it forged to rough dimensions, heat treated and samples sent to an outside laboratory for magnetic property characterization.  This material will be held in inventory to support the thruster build in Phase II.  ULA will provide at no cost to NASA engineering support by performing a top level assessment and preliminary system engineering for incorporating a 30kW propulsion module (with two15kW thrusters) with the MegaFleX and RollOut solar array onto the ESPA.  In Phase II we will build and conduct performance and environmental testing of the thruster to raise the maturity level to TRL 6 at the end of the Phase II program.
NASA has drawn attention to an impending need to improve energy-efficiency in low supersonic (M&lt;~3) platforms. Aerodynamic efficiency is the foundation of energy-efficient flight in any regime, and low drag is one of the fundamental characteristics of aerodynamic efficiency. For supersonic aircraft, drag can be broadly decomposed into four components: viscous or skin friction drag, lift-induced drag, wave or compressibility drag, and excrescence drag. The relative impact of these four drag forces depends upon vehicle-specific characteristics and design. However, viscous skin friction drag stands out as particularly significant across most classes of flight vehicles. Therefore, effective techniques to reduce skin friction drag on a vehicle will have a major and far-reaching impact on flight efficiency for low supersonic aircraft. In an effort to address the need for increased aerodynamic efficiency of low supersonic vehicles, PM&amp;AM Research, in collaboration with Texas A&amp;M University, propose to demonstrate the feasibility of depositing energy using basic, well-demonstrated techniques along the surface in supersonic flow to control/compress/forcibly-move the boundary layer fluid by creating a low-density "bubble-like" region, thereby reducing the viscous skin friction. If successful, this solution will reduce the drag experienced by a low supersonic platform, allowing vehicles to exhibit increased aerodynamic efficiency.
NASA needs lower cost solar arrays with high performance for a variety of missions. While high efficiency, space-qualified solar cells are in themselves costly, &gt; $250/Watt, there is considerable additional cost associated with the parts and labor needed to integrate the Photovoltaic Assembly. The standard approach has evolved with only minor changes, sacrificing cost because of risk aversion. Integration cost can be as much as double the bare cell cost &amp;#150; i.e. &gt;$500/watt. Dramatic cost savings can be realized through manufacturing engineering of more efficient automated assembly processes. If the design of the Photovoltaic Assembly could be modified to be compatible with conventional and automatable electronic assembly and terrestrial solar panel assembly approaches, there could be considerable cost savings. There are many additional benefits with automation which include higher quality and consistency. This can reduce failures, increase production throughput, speed turnaround, and improve overall reliability. Cost and quality improvements can be realized on both thin and rigid arrays, increasing current capabilities, and enabling future high power missions. The benefits of automation are enhanced by the need for high power generation in support of energy intensive space missions. A 300kW array at $500/W would cost $150M just for the solar cell integrated array panels. A $150/W cell integration cost reduction would translate into savings of $45M, before considering the immediate and substantial benefits in consistency, reliability, and schedule. The Phase I effort demonstrates feasibility of a low cost array using an automated and integrated manufacturing approach, performed on an automation friendly solar cell, verified with environmental testing, and is used to predict array cost for a high power mission. Meeting these technical objectives will demonstrate reduced cost and justify a Phase II SBIR program preparing for a flight experiment.
Long-duration robotic and manned space missions have a number of unique requirements for mission success. These include ultra-high reliability, safety, sustainability and affordability of launch vehicles and spacecraft. These requirements, in turn, are allocated among critical subsystems, such as engines, propellants, structures, software systems, thermal protection, power, avionics, life support, guidance, communication and navigation. In this vein, novel integrated system health management (ISHM) technologies that evolve with the system life-cycle, viz., concept-&gt; design-&gt; development-&gt; production-&gt; operations and training, are essential for meeting the requirements of safe and ultra-reliable, sustainable and affordable launch vehicles and spacecraft. To improve the ISHM process, QSI proposes to emphasize advancement in the two following areas: 1) generation/selection of an optimal sensor suite for the system based on user selected performance requirements and system level constraints, and 2) enhancement of a drill-down diagnosis/next best test capability in terms of algorithms that can be implemented for low power, low memory CPU/hardware that are available for embedded diagnosis using TEAMS-RT. Outcome technologies of the proposed focus are expected to allow an improved ISHM process to systemically trade-off prevention, detection, diagnosis, decision, and response strategies to mitigate the failure effects, as well as enhance FM development process by improved/new capabilities of TEAMS&amp;#174; tool set.
We build a system that supports the weather information needs of  Unmanned Aircraft Systems (UAS) planning to fly in the National Airspace System (NAS).  This weather information service will supply information to UAS Ground Control Stations (GCSs) from the Next Generation Air Transportation System (NextGen) 4D Weather Data Cube, the Single Authoritative Source (SAS) for aviation weather information, and associated modules which will determine the impacts that weather will have on the UAS. A centralized distribution system, based on a Service Oriented Architecture (SOA), provides weather and constraint information to airlines and pilots (including UAS operators) - the design follows JPDO guidelines.   In NextGen, the design goal is for all aircraft flying in the NAS (including UASs) to have a consistent set of weather constraints.
Spacecraft operations demand a high level of responsiveness in dynamic environments. During operations, it is possible for unexpected events and anomalies to disrupt the mission schedule, and in the case of critical faults, even threaten the health and safety of the spacecraft.  Historically, it has been the responsibility of the mission operations team on the ground to issue command sequences and monitor spacecraft health and status to ensure that long-term science, engineering, and safety goals are achieved. Red Canyon Software is building upon previous designs for on-board, layered autonomous software flight systems employing continuous planning and command sequencing. The proposed innovation increases the robustness of on-board autonomy for space vehicle operation, while at the same time offers reductions in mission development costs by leveraging off of newer flight proven software technologies.  Also, developing, verifying, and validating spacecraft activity and constraint models for use with model-based autonomous planners and reactive sequencers are difficult and complex activities.  For robust, on-board autonomous systems with multiple layers of software performing varying levels of constraint checking prior to activity planning and command sequencing, more than one layer will need to be configured with the same model constraints.  To reduce the cost and risk of model development and use, a single, shared spacecraft domain model representation is proposed, along with development of a graphical editor that allows system engineers to easily encode domain information and that uses verification rules to detect inconsistencies or errors.
Pioneer Astronautics proposes a technology program for the development of an innovative photocatalytic oxidation reactor for the removal and mineralization of Volatile Organic Compounds to extend crewed space exploration beyond low earth orbit.  This novel technology, called the High Performance Photocatalytic Oxidation Reactor System (HPPORS) leverages recent progress in high power Light Emitting Diodes (LED) and efficient, visible wavelength photooxidation (PO) catalysts to completely oxidize Volatile Organic Compounds (VOCs) to carbon dioxide and water.  The basis of the innovation is the synthesis of commercial high power, high brightness LEDs with efficient geometric illumination of active visible-light activated PO catalyst in a high surface area to volume fiber optic reactor.   This combined approach leads to numerous performance benefits including high VOC conversion efficiency, compact reactor volume, and low pressure drop.  The development of the HPPORS technology will lead to a photocatalytic reactor that meets the rigorous compliance requirements of complete VOC mineralization to CO2 and H2O, while utilizing efficient visible LEDs or solar energy in a compact, scalable package.
Chronos Technology (the R&amp;D division of Frequency Management International, FMI) proposes to deliver a comprehensive, and fully investigated &amp; validated feasibility study (in Phase 1) for a novel approach leading to design &amp; fabrication of extreme Environment Silicon Carbide (SiC) circuit blocks  used in a variety of spacecraft power &amp; propulsion system. The circuits shall be used for a wide range of both manned and unmanned space missions. The resulting solutions uniquely enable new extreme environment and high temperature performance levels offered commercially in compact, miniature size &amp; rugged construction. There are no present alternatives for the proposed devices applicable to the extreme environment operating conditions. Based on the technology selection investigation and the road map defined, our proposed technology investigation and the resulting design effort in phase 1 shall conclude with identifying the best fit semiconductor fabrication process as well as component level design &amp; implementation/fabrication methodology plan. With the already stated interest from SiC processing companies such as Cree, we would be focused on targeting device designs for circuits like counter, basic gate, buffer/driver &amp; amplifier, all operating at industry std low voltages 
In phase 2, we will complete the design/fabrication of successful extreme environment integrated circuit blocks as described that will be used in high efficiency spacecraft power &amp; propulsion systems. We envision to deliver devices that will enable high efficiency power management as well as much improvement in energy density and specific power as required for the state of the art modular power unit architecture. Coupled with the extreme environment, high temperature operation and radiation hardened capabilities the resulting innovative devices will play its significant role as part of the emerging power and propulsion system for future missions.
Valuable time is spent by astronauts performing simple, mundane, or ergonomically taxing tasks. Therefore, one center of focus for NASA is to have robots increasingly perform these tasks to give the crew more time flexibility. Robots are also employed with tasks that are too dangerous for humans or when movement could affect the results and success of a task. The following proposal applies nanoGrip's expertise in design, fabrication, and characterization of gecko-inspired microfiber adhesives to produce a new generation of materials that increases the dexterity of these robots' manipulators so that they can perform a larger variety of manipulation tasks with higher precision. In this proposal, an emphasis will be placed on manipulating objects that are either small, delicate, or with a difficult to grip form factor where the current state of the art in manipulation may struggle. 

Microfiber adhesive materials developed during this project will be evaluated for their shear strength in contact with systems and materials which may be encountered by the Robonaut 2 (R2) manipulator on the International Space Station, for their ability to stick and unstick reliably through pick and place experiments, and for their ability to perform manipulation tasks when incorporated onto a robotic manipulator. Proof of concept robotic manipulation during these studies will be performed in collaboration with our consulting partner on Carnegie Mellon University's (CMU) Robotics Institute's bimanual dexterous manipulation robot. Additionally, prototypes will be delivered to NASA for qualitative or quantitative evaluation. At NASA's discretion, testing may be performed at the Johnson Space Center's Dextrous Robotics Lab for material evaluation on the ground-based R2 manipulator.
CO2 sensing using absorption bands near 1570nm is very attractive by taking advantage of the mature fiber-amplifier technology derived from fiber-optic telecom heritage. This necessitates sufficient power scaling in 1.5 micrometer fiber-amplifiers, either in the pulsed-mode, or in the cw-mode for modulation spectroscopy.In this SBIR program we propose the design, optimization, experimental evaluation and prototype development of a high-power,high wall-plug efficiency, 1571.1 nm fiber-amplifier laser transmitter, compatible with multi-line cw intensity-modulated integrated-path differential absorption spectroscopy, with the size, weight and power (SWaP) optimized for airborne and eventual space-qualifiable roadmap for ASCENDS mission. We leverage innovations in high-power 1.5 micrometer fiber-optic technology and fiber-amplifier architecture, while using high-reliability 1.5 micrometer silica-fiber based passive/active components. Our expectation is that at the end of Phase 2, a TRL-6 level hardware can be developed and delivered for an airborne mission, and which is also compatible with a space-flight maturation roadmap.
The National Airspace System (NAS) in the United States will become a complex array of commercial and general aviation aircraft, unmanned aircraft systems, reusable launch vehicles, rotorcraft, airports, air traffic control, weather services, and maintenance operations, among others.  The Federal Aviation Administration (FAA) projects that by 2025 air traffic will increase by more than 50 percent with 1.1 billion passengers a year and more than 85,000 flights every 24 hours contributing to further delays and congestion in the sky. This increased system complexity necessitates the application of systematic safety risk analysis methods to understand and eliminate where possible, reduce, and/or mitigate risk factors.  The product of this effort is the development of an Uninhabited Aerial System (UAS) safety analysis model, which hereafter is called USAM.  The USAM effort proposed herein is an extension of current efforts underway by the UAS community, and it extends these efforts by incorporating UAS scenarios and encounter geometries to populate existing safety analysis models, thereby producing credible future UAS safety metrics
Makel Engineering and the Ohio State University propose to develop a harsh environment tolerant gas sensor array for atmospheric analysis in future Venus missions. The proposed instrument will be very compact, require low power, and ruggedly packaged to be compatible with a drop sonde payload from a balloon for atmospheric composition analysis and/or for use on Venus surface lander or surface weather station. The goal is to provide information on local SOx  CO, O2, NOx, H2, OCS, HF, HCl, and water vapor concentrations in order to complement other measurement systems that were targeted in the 2009 Venus Flagship Mission Study such as a GC-MS, nephelometer, or camera/optical detectors.  Phase II will fabricate and test probe designs based on sensors tested in Phase I.  Complete sensor array including high temperature capable electronics (250 to 300 C) will be tested at the NASA Glenn Extreme Environment Rig (GEER) to provide simulation of the Venus atmosphere at different conditions.
Fluid handling applications in cryogenic and extreme environments require reliable actuation technology that can handle extreme temperatures, mechanical bind-up from ice and foreign contaminants, and operation in poor conditions.  A novel EM hammer drive technology is proposed for use in cryo-propellant fuel storage and regulation valves/devices.  In addition to high force, the new drive technology offers potential advantages for miniaturization, heat load reduction, and lower cost than traditional electromagnetic and piezoelectric actuators.  Dynamic Structures and Materials (DSM) proposes to focus the Phase II innovation on the development of a hammer drive actuation mechanism that will take the EM oscillatory power and produce continuous linear motion for operation at cryogenic and extreme environments.  DSM has demonstrated expertise in the operation of its high force linear motor actuators at temperatures down to 77 K.  The proposed actuator should operate from approximately 4 K to 400 K and should provide very low or no out gassing as well as operational capabilities in hard vacuum. The technology is proposed for applications in the cryo fluid management, pressure and flow control, and driving operational equipment and instruments. This proposal addresses DSM's approach to the development of flight-scalable demonstration components for the EM hammer drive technology.
The program will leverage recent advances in striction materials and coupled striction devices as to enable highly isolated (analog) voltage and current flow sensors very suitable for harsh space environment power monitoring.  Exhibiting negligible electromagnetic disturbance coupling and electromagnetic emission, these non-photonic striction based power flow monitoring introduces decided advantages of eliminating magnetics, processors, degradation and 'latch-up'.  These units are simpler and lower cost to manufacture than photonic or capacitive coupled methods of measurement and possessing and furthermore provide far greater (galvanic) isolation capability than is presently achievable.  Moreover they can safely/reliably operate over a wide temperature range to as low as cryogenic.  The innovation eliminates the present need for separate isolation and gain stages as these are now accomplished in a single step as to reduce design complexity and risk.  The effort is to show that these new striction power flow monitoring capabilities can measure power characteristics over wide bandwidth to DC and are highly suitable for widespread NASA use in wide temperature range and high radiation environments.  The proposed modular design will be easy to install and reduces the spares requirements.
Passive thermal control of cryogenic systems using foam insulations can help achieve Zero Boil-Off (ZBO). There is as much thermal energy transferred to Cryo tanks during the ascent phase as there is during 6 days of orbital operations using MLIs.

Spray on Foam Insulation (SOFI) still suffers from drawbacks both at chemistry and interfacial (bonding) levels. Currently, strong lightweight polymeric foam insulators cannot be (net shape) molded into larger complex shapes, using commercial foaming practices. The proposed Phase 1 research studies feasibility of an inventive (unprecedented) combination of processing and "green" foaming agents to "net-shape" mold low density robust (damage/MMOD tolerant) polymeric insulation foams into "monolithic" complex shapes (such as spherical or cylindrical shells, valve fittings). These can protect polymer matrix composite (PMC) tanks (such as COPVs) against external damages, hence enabling reliable, reusable cryogenic storage designs.

An added advantage of this invention is the "clean" decomposition of the blowing agent and development of an environmentally "green" insulative "net-shape" foaming technology.
Our overall goal is to enhance the overall behavior health and performance of personnel on (future potential) long-duration missions. We propose to use a local representation of the Second Life virtual world, along with our computer graphics and artificial intelligence background, to make a highly interactive and responsive environment between groups of people that are literally worlds apart in communication distance. By having the interactions occur this way, there is no communication latency that needs to be dealt with, because content is updated asynchronously. 
We will also leverage and adapt our Automated Behavior and Cohesion Assessment Tools system, previously developed under a recent NASA Phase II SBIR, to measure behavior health and performance.
NASA space exploration missions require radiation-hardened memory technologies that can survive and operate over a wide temperature range. Memristors (memory-resistors) are a promising technology for the next generation of non-volatile memory (NVM) applications and offer a highly-desirable combination of density, access speed, and power. Early investigations have also shown that memristors have high radiation hardness. In this SBIR, CFDRC and Arizona State University propose to develop, characterize, and demonstrate novel, memristor-based, radiation-hardened NVM for NASA space applications. In Phase I we will: 1) Fabricate state-of-the-art Chalcogenide Glass (ChG) memristors based on the CBRAM technology; 2) Examine their wide temperature performance (-230 to +130  deg.C) via thermal experiments; and 3) Add new models to CFDRC's NanoTCAD Mixed-Mode simulator for accurate physics-based simulation of memristors. The Phase I effort will evaluate suitability of ChG memristors for extreme temperature applications. In Phase II, we will extend our scope to include wide-temperature investigation of the competing transition-metal-oxide (TMO, e.g., TiO2) memristor technology. For both ChG and TMO, we will then perform irradiation testing and down-select the technology with the best extreme environment (radiation + temperature) performance. Subsequently, we will generate wide-temperature, radiation-enabled, device physics and compact models for the memristors, develop designs for memristor-based NVM, and perform mixed-mode simulations to determine their radiation and thermal response. These results, and physics-based understanding of device response, will be used to develop an NVM prototype that will be tested and demonstrated for NASA space applications.
Thermal Transfer is a critical part of power electronics application in both terrestrial and space environments.  Due to longer lifetime expectancies and harsh operational conditions, space vehicles require unique materials to deal with the increasing electrical and thermal loads placed upon the structure.  Increasing use of power electronics including high current carrying semiconductor devices such as IGBTs, MOSFETs, power transistors, and modules drive the need for specialty thermal management materials both in the packaging of the discrete devices as well as for the packaging of modules consisting of several or arrays of these devices. 

The overall objective of this program (Phase I and Phase II) is to adapt CarbAl(TM)-based advanced thermal management substrates from terrestrial to space applications.  CarbAl(TM) is a carbon-based thermal composite with a thermal performance exceeding that of many metals.  The low CTE provides excellent matching to state-of-the-art power transistor dies and the low density and robustness make it suitable for space vehicle applications.   The proposed Phase I program is a continuation of the materials development completed internally at ANI.  If successful, the technology developed through this project will provide and accurate, robust, reliable and cost effective.
Systems and Materials Research Corporation (SMRC) proposes combining its Manufacturing Technology and Materials Science expertise to address NASA's Advanced Food System Technology needs. Using progressive 3D printing and inkjet technologies, SMRC will design, build, and test a complete nutritional system for long duration missions beyond low earth orbit. The 3D printing component will deliver macronutrients (starch, protein, and fat), structure, and texture while the ink jet will deliver micronutrients, flavor, and smell. SMRC will team with the food science program at North Carolina State University and International Flavors and Fragrances to ensure the production of nutritious and flavorful mission supplies. SMRC proposes producing synthetic food which meets the nutritional needs of each and every mission specialist and astronaut. Using unflavored macronutrients, such as protein, starch and fat, the sustenance portion of the diet can be rapidly produced in a variety of shapes and textures directly from the 3D printer (already warm). Since basic sustenance will not ensure the long term physical and mental health of the crew, this is where the microjetting will add value. In addition to adding flavor, low volume micronutrients will be added as the food is processed by the 3D printer.	The macronutrient feed stocks will be stored in dry sterile containers and fed directly to the printer. At the print head, these stocks will be combined with water or oil per a digital recipe to minimize waste and spoilage. Flavors and texture modifiers can also be added at this stage. This mixture is blended and extruded into the desired shape. The micronutrients and flavors are stored in sterile packs as liquids, aqueous solutions or dispersions. SMRC's approach not only addresses uniform long term storage, sustenance, and micro-nutrition, but also variable and changing dietary needs, variety, and boredom.
Mesa Photonics proposes development of a passive optical sensor for simultaneous high-precision measurement of oxygen and carbon dioxide profiles within the full atmospheric column.  The approach, which is based on near-infrared heterodyne spectroscopy using solar occultation (i.e., direct solar viewing), is called Precision Heterodyne Oxygen-Calibrated Spectrometer, or PHOCS.  Oxygen measurements will provide dry gas corrections and &amp;#150; more importantly &amp;#150; will determine accurate temperature profiles that, in turn, improve the precision of the carbon dioxide column retrievals to better than 1&#37;.  Planned instruments will complement results anticipated from the Orbiting Carbon Observatory (OCO-2), Active Sensing of CO2 Emissions over Nights, Days, and Seasons (ASCENDS), and ground-based Fourier transform spectrometers.  PHOCS instruments will be small (not much bigger than a pair of binoculars), light weight, and low power.  In keeping with one of the goals of this SBIR topic, planned instruments will be initially configured for operation on the ground, and have size, weight, and power (SWAP) characteristics suitable for easy ground mobility and well as airborne or space-borne deployment.  
The Phase I project will test an all-fiber-optic heterodyne receiver that will simplify optical design and ensure long-term optical alignment.  Oxygen measurements will use the near-infrared band the 1.27 micron wavelength region instead of the more commonly used band at 0.76 microns.  The longer wavelength band is weaker; precise lineshapes of many individual rotational lines will be measureable without complications due to highly saturated absorbances or instrument line shape functions (ILS).  Carbon dioxide measurements will use the well-characterized band at 1.57 microns.
Advanced Scientific Concepts, Inc. (ASC) is a small business, which has developed a compact, eye-safe 3D Flash LIDARTM Camera (FLC) well suited for real-time spacecraft trajectory, speed, orientation measurements relative to the planet's surfaces and evaluating potential hazards during the critical landing sequence.  ASC's Flash LIDAR has been used for autonomous berthing with the International Space Station (ISS) and is currently under development for the OSIRIS-REx asteroid rendezvous mission.  Flash LIDAR is also being evaluated by JPL and NASA for Entry Decent and Landing (EDL) for ALHAT and Mars. Through the investigations at JPL and NASA Langley a number of improvements to the technology have been identified as beneficial to landing application.   Improved range resolution, spatial resolution, increased sensitivity and greater dynamic range would increase the functionality for successful landing operations. ASC has developed the core technology for Flash LIDAR with its 3D-FPA and is developing higher resolution arrays to address these concerns.  ASC currently has on hand high sensitivity 32x32 arrays (shuttle run for the 320x320) that have not been tested with detectors.  Initial evaluation suggests that they have increased sensitivity by 50x, spatial resolution by 2.5x, and range resolution by 3x.
New technology is needed to collect, stabilize, safen, recover useful materials, and store human fecal waste for long duration missions. The current SBIR Phase I proposal will examine an innovative torrefaction (mild pyrolysis) processing system that can be used to sterilize feces and produce a stable, free flowing powder than can be easily stored or recycled, while simultaneously recovering all of the moisture and producing minimal amounts of other gases. The system will also require minimal crew interactions, low energy demands, and tolerate mixed or contaminated waste streams. The objective of the Phase I study is to demonstrate the feasibility of this improved process using bench scale experiments. This will be accomplished in three tasks: 1) design and construct bench scale processing unit that can accommodate different modes of heating (conventional, microwave, radiant/solar); 2) laboratory and modeling studies on a fecal simulant over a range of process conditions (temperature, holding time, atmosphere); 3) evaluation of laboratory results and preliminary design of Phase II prototype.
ITN proposes to create an innovative anode supported membrane electrode assembly (MEA) for solid oxide fuel cells (SOFCs) that is capable of long-term operation at low temperature by the direct oxidation of dry methane or syngas fuel without coke formation on the anode. ITN's MEA is more efficient, durable, reliable, versatile and economical than the state of the art because it is made with transformative manufacturing techniques &amp;#150; microwave sintering and energy optimized plasma deposition (EOPD). The proposed fuel-flexible, direct oxidation MEA is capable of power densities up to 2 W/cm2 at 600?C. ITN's EOPD of thin, conformal YSZ electrolytes creates a stress free interface between the anode and electrolyte which improves MEA durability, cycle-ability and cell performance. The MEAs produced in this research effort can be incorporated into SOFC stacks capable of producing power in the 1-3 kW range.  Because the fuel is oxidized directly in the SOFC, without external fuel processing, the thermodynamic efficiencies from fuel source to DC output exceed 70&#37;.  Higher efficiencies translate to minimal cooling required as obtained by way of conduction through the stack to a radiator exposed to space and/or by anode exhaust flow.
We propose to design, build and test a 1 kg, single actuator, sample acquisition drill. The drill uses a novel method of core or powder acquisition. The core acquisition bit can be used for either a rock core, icy-soil or loose regolith acquisition. The continued development of robust sample acquisition and handling tools is of critical importance to future robotic and human missions to Mars, the Moon, Asteroids, and other planetary bodies. For these missions, consolidated or unconsolidated core samples (as opposed to, say, scooped regolith or collected drill cuttings) are of particular interest.
The proposed load-bearing, tank-applied, multi-layer insulation system consists of a set of highly reflective radiation shields made from 1 mil thick aluminized Mylar that is supported from a "pop-up tent like" support frame.  In addition, the support frame carries the mass of an actively cooled shield and outer MLI blanket enabling ultra low heat leak storage of cryogenic fluids.  The support frame is conveniently mounted to the top and bottom center tank penetrations, eliminating any direct supports to the cryogen tank itself, which reduces the heat leak to near the theoretical minimum.  The novel design approach is significantly better than conventional MLI, which does not possess the required structural or thermal capabilities required.  The technical approach is to integrate low-risk, high Technology Readiness Level (TRL) (TRL 7-9) components into a new and unique low-cost, light-weight, high-strength, thermally efficient MLI system.  This approach enables the system to meet and exceed all requirements for reduced heat leak, low-mass, and high strength to withstand flight loads.  The NASA Cryogenic Propellant Storage and Transfer Program will directly benefit from the development of the proposed MLI system.
Future NASA space missions require advanced systems to convert thermal energy into electric power.  These systems must be reliable, efficient, and lightweight.  In response, we propose to develop a turbo-Brayton power converter with high efficiency and specific power.  The converter will use gas bearings to provide reliable, maintenance-free, long-life operation.  It will also consist of discrete components that can be packaged to fit optimally with other subsystems, and its continuous gas flow can communicate directly with remote heat sources and heat rejection surfaces without ancillary heat transfer components and intermediate flow loops.  Creare is well suited to succeed because we have a long history of developing advanced turbomachines, heat exchangers, and Brayton systems for challenging spaceflight applications.  We will complete detailed analyses, trade studies, fabrication trials, and preliminary designs for the components and converter assembly during Phase I, followed by fabrication and testing of a breadboard converter during Phase II.
&lt;p&gt;Each individual NASA Center has full discretion on the use of the funds and the Center Chief Technologists coordinates a competitive process at their Center for the selection of projects.&amp;nbsp;Kennedy Space Center (KSC) considers CIF very important because it encourages employees to develop innovative concepts that, if successful, can solve future mission needs. As in prior years, KSC put a strong emphasis on low Technology Readiness Level (TRL) technologies for CIF in support of Space Technology Area Roadmaps that align with KSC core capabilities.&lt;/p&gt;&lt;p&gt;KSC has emphasized partnerships for several years and has benefited in many ways from the other NASA centers and government agencies, academia and industry collaborations. In keeping with this emphasis, a key selection criterion for KSC CIF relates to collaborations and partnerships (with leveraged funding).&amp;nbsp;&lt;/p&gt;
We propose to develop an active sensor for in situ measurement of the inherent optical properties (IOPs) absorption and backscattering at multiple wavelengths. Multi- or hyper-spectral absorption of particles and dissolved materials is routinely measured in the laboratory and in situ in order to characterize, for example, the quantities and types of phytoplankton based on concentrations of specific absorbing pigments. Similarly, backscattering is employed to estimate the concentration of suspended material. Measurements of absorption and backscattering concurrently, and at multiple wavelengths, are useful as proxies for biogeochemical measurements such as particle composition, concentration of particulate organic carbon, and particle size distribution, as well as for remote sensing calibration and validation.
The current state of the art for phytoplankton observation using optical sensors on autonomous platforms relies on linking biomass with optical backscattering and chlorophyll. The ability to quantify phytoplankton using absorption not only overcomes limitations of backscattering and fluorescence-based approaches, but multi-spectral (visible wavelength) measurements of absorption also provide the means to discern the presence of accessory pigments and pigment packaging, ultimately leading to not only improvements in phytoplankton biomass estimates, but also the potential for resolving phytoplankton functional types.
Briefly, the proposed sensor emits a collimated beam of light into the water and measures the backscattered light as a radial function from the beam location. An inversion algorithm is then used to convert this backscattered intensity as a function of distance from the beam to the inherent optical properties absorption and backscattering. Multiple source wavelengths are used and the sensor is packaged in a compact, flat-faced geometry easing integration into autonomous platforms.
Large, lightweight, deployable solar array structures have been identified as a key enabling technology for NASA with analysis and design of these structures being the top challenge in meeting the overall goals of the NASA Space Technology Roadmap. The use of analysis to drive design from an early stage is critical to their success, yet conflicting design requirements and demanding space constraints make traditional design/build/test methods challenging and expensive. The proposed SBIR program focuses on overcoming this through the development of a user-friendly multi-disciplinary design and analysis software toolkit that can rapidly perform parametric studies and design optimization of solar array concepts. The software package will provide a graphical user interface and underlying analysis procedures to evaluate critical performance metrics (e.g. deployment, packaging efficiency, strength, stiffness, mass, etc.), while eliminating the unnecessary pre-processing and computational overhead associated with current approaches. The user will be able to interactively investigate effects of design parameter changes (e.g. array geometry, size, number of panels/sections, joint properties, control system parameters) on critical performance metrics and analysis results. Analysis capabilities will include flexible multi-body dynamics, array deployment, loading due to thrust, and modal analysis. Parametric study and design optimization capabilities will also be key features of the tool. Model creation will be simplified through the use of an extensible, hierarchical blockset solution and a library of blocks specific to deployable solar array analysis. The Phase I effort will focus on developing accurate analysis capabilities, a parametric study workflow, and the GUI for controlling them and interpreting results. Phase II will incorporate additional analysis types (e.g. thermal, uncertainty propagation, sensitivity analysis, etc.) as well as a design optimization framework.
Busek Company, Inc. proposes to develop a micro thermionic cathode that requires extremely low power and provides long lifetime.  The basis for the cathode is a Barium impregnated dispenser cathode.  The innovation will be the heating technique.  We are proposing to heat the cathode to emission temperatures through radio frequency induction heating.  The current state of the art micro cathodes utilize a resistive heater typically operated by passing a DC or AC current through a small refractory wire, heating the wire through ohmic heating.  This requires significant sized wires and mechanics that create a heat sink through the leads, greatly increasing the power required to heat the cathode. Alternative development programs for micro cathodes have proposed utilizing lasers to heat the backside of the cathode.  The drawback for this method of heating is the low power efficiency of state of the art lasers.
In support of our proposed concept, Busek has recently developed an innovative RF generation circuitry that leads to applications like the proposed.  The circuit is highly efficient and load variant tolerant.  During Phase I we will design, build and test a model cathode with integrated induction heater coil and RF generator.  Phase II will optimize the design and develop a commercial cathode for applications such as sensors, traveling wave tubes or micro ion engines.
Tactical Departure Scheduling (TDS) is a common activity in Air Traffic Control (ATC) in the National Airspace System (NAS) that requires significant coordination for individual flights and that has the potential to impose delay on impacted flights. Some of the delay that is imposed through the TDS process is necessary, but some of the delay may be unnecessary. The current TDS process is implemented through the Call for Release (CFR) process, which is also referred to as the Approval Request (APREQ) process. In this process, the Traffic Management Unit (TMU) informs the Air Traffic Control Tower (ATCT) that a specific group of flights cannot be cleared by the ATCT to take off until the departure release is approved by the TMU on an individual flight basis. When such CFR programs are in place, an ATC Specialist (ATCS) in the ATCT must contact the TMU via a voice line to request approval for a flight to depart. Once the TMU provides a release time window for the flight, the ATCS in the ATCT must then maneuver the flight to make sure that it takes off within the release time window, or else a new release time must be requested.
The purpose of this proposal is to address research and development on the TDS by Exception process, or TDS-E. The TDS-E concept includes a computer automation system that monitors traffic demand in the en route streams of traffic, as well as demand of flights that will depart from airports under the en route stream and climb into the overhead stream. Instead of requiring all such departures to receive individual approval before they take off, under the TDS-E concept, the computer automation system will provide advisories to the TMU and to the ATCT to indicate when CFR procedures are required, and specifically which flights should be subject to CFR. Additional features of the TDS-E capability may provide guidance indicating that some of the normal CFR restrictions can be relaxed.
A new detector evaluation method (DEM) is proposed to determine the response of graphene detectors to low fluxes of photons, neutral atoms/molecules, and ions in the space environment of high to ultra-high vacuum. The method, aimed mainly at evaluation for space applications of new graphene detectors, is also applicable to other detectors operating in non-space environments. DEM will test graphene response to very low fluxes of atoms and molecules, ions, and photons; if sensitive to extremely low fluxes of a few 100/s, the timing of pulses produced by bunched events may open up an entirely new avenue to time-of-flight mass spectrometry. Closely coordinating with the NASA GSFC Detector Systems Branch, DEM will characterize the detector response to enable low-cost demonstrations of ionosphere-thermosphere investigations in low-Earth-orbit in CubeSats and sounding rockets. Space-borne measurements require knowledge of the response to the three kinds of particles: photons, ions, and neutrals, to properly design experiments. DEM controls vacuum pressure at the detector and can validate the application of these new detectors to a new series of mass spectrometers that can operate over a broad range of vacuum pressures (0.1 milliTorr and lower) because of their small size &amp;#150; DEM will add value to cost effective NASA balloon, sounding rocket, and satellite investigations.
Ferrite control components including circulators and isolators are fundamental building blocks of Transmit/Receive modules (TRM) utilized in high data rate active space transceivers and transponders for both long-range (LR) and low earth orbit (LEO) systems. These components are utilized to protect high power amplifiers (HPA) during the transmit cycle from destabilizing, and potentially harmful, power reflections from the antenna element. During receive cycle these components are utilized to direct lower power received signals with minimal attenuation to the low noise amplifiers (LNA). As such, performance specifications of these ferrite control components, such as bandwidth, insertion loss, isolation, power handling, temperature stability, radiation hardness, and linearity impose strict limitations on the overall system performance. Over the course of the proposed Ph1 SBIR program self-biased ferrite control components based on highly textured hexagonal ferrite compacts which have the potential to eliminate biasing magnets and significantly reduce the size, cost, and weight of the TRM while concurrently increasing power handling capability, and improving temperature stability and radiation hardness will be investigated. Specifically, a research and development path to realizing high performance self-biased ferrite materials and device designs for operation in space based environments at Ka-band (&gt;27 GHz, 31.5 - 34 GHz targeted) is outlined.
This proposal addresses NASA's science objectives with innovative lidar architecture for atmospheric CO2 measurements.  Specifically, the proposed work can support and potentially enhance the Active Sensing of CO2 Emissions over Nights, Days, and Seasons (ASCENDS) technologies. Using an active laser measurement technique, our system is designed to enhance the capabilities of CO2 remote sensing from high-latitude regions and nighttime observations with sensitivity in the lower atmosphere, and enable investigations of the climate-sensitive southern ocean and permafrost regions, provide insight into the diurnal cycle and plant respiration processes, and provide useful new constraints to global carbon cycle models.
An eye-safe, multispectral cross-track scan subsystem with a large receiver aperture and a narrow FOV is proposed for the NASA Cloud Physics Lidar to increase horizontal area coverage. The  +/-15 degree cross-track scan capability will cover +/- 5 km from nadir at a 20 km altitude. The cross-track scanner uses a whiskbroom pattern with three simultaneous  scans and independent receiver FOV's which provides 30,000 points per sweep. Solar background is reduced with a narrow bandpass filter and a narrow transmitter linewidth with center wavelength control. The scanner accounts for the return pulse lag angle due to pulse time of flight. Vertical resolution is maintained at 30 m. Photon counting SPAD detectors and PMT's are used with photon counting modules and multichannel scalers.
Advanced Scientific Concepts, Inc. (ASC) is a small business that has developed 3D Flash LIDAR systems for space and terrestrial applications.  3D Flash LIDAR is ideal for determining real-time spacecraft trajectory, speed and orientation to the planet's surface, as well as evaluating potential landing sites.  Flash LIDAR sensors utilize a 3DFPA and rely on the illumination of a 10nsec pulse from a diode pumped solid state (DPSSL) q-switched Nd:YAG laser.  Improvements in pulse shape and stability are crucial to improve range resolution for higher resolution landing maps.  ASC is proposing an innovative approach to the laser and thermal management to meet NASAs requirement for a compact, robust planetary landing sensor.  An innovative approach for an optically triggered "semi-active" q-switch will allow for increased power stability in a very compact laser design.  The semi-active fused q-switch will eliminate the need for a mechanical or electro optical q-switch by actively bleaching the passive q-switch with a laser diode.  The advantage of the Cr4:YAG crystal over active q-switches is that it can be fused directly onto the YAG laser rod creating a monolithic laser cavity reducing the number of coated surfaces and the overall size.
Our proposed multilayered, flexible, graded Z radiation shielding, RadFlexPro, provides radiation protection for astronauts in EVA for NASA's future space missions.  RadFlexPro can be integrated into current space suit TMG designs and act as multifunctional layers, providing additional protection from micrometeoroids.  Current RadFlexPro designs have three layers. The outer layer serves as a first barrier to decelerate high speed and high energy particles: the following layer decelerate particles more, and the final layer protects from possible secondary radiation. It is proposed that RadFlexPro will significantly increase radiation protection without compromising bulk and mobility in a space suit. 
RadFlexPro is a composition of several materials and layers, with different properties selected to protect against various types of radiation. Compared to single-material shielding, such as Demron, the same mass of Graded-Z coating shows increased radiation opacity; as an alternative, a lower mass of graded z shielding can provide the same level of protection as a single material sheild. In a typical graded-Z shield, the high-Z layer effectively scatters protons and electrons. 
Because the matrix of RadFlexPro is adjustable, the coating can be sprayed on surfaces, rolled or laminated, and/or dipped into solution.  A matrix solution can be made with different viscosities and densities to suit several bonding techniques. Coated fabrics can in turn be cut out according to flat patterns and sewed with other pieces into a TMG configuration.  FFD has considerable experience and hardware to sew thick, heavy, rubbery materials effectively.
This program addresses the need for non-destructive evaluation (NDE) methods for quality assessment and defect evaluation of thermal protection systems (TPS), including permanently installed sensors for TPS condition, stress and temperature monitoring.  Novel linear drive eddy current methods are proposed for NDE of carbon-based TPS materials, such as three dimensional woven fiber composites and felts. Using a combination of physics-based models, multivariate inverse methods, high resolution imaging, and innovative sensor array constructs the developed methods will independently monitor the material characteristics of interest.  In Phase I, the focus is on enhancing and adapting methods developed for carbon-based composite structures and laminates and demonstrating feasibility of these enhanced methods for three-dimensional woven composites and felts.   JENTEK's physics-based methods for diagnostics of layered media using MWM-Array technologies, including an eddy current micromechanical model extension for composites, have been demonstrated for condition stress and temperature monitoring.  MWM-Arrays have a linear drive that permits both scanning type imaging and permanent installation for  monitoring of anisotropic properties, temperature, and stresses at multiple depths.  The projected depth of the magnetic field into the test material can be adjusted through the sensor dimensions and excitation frequencies; this enables inspection of materials more than 1.0-in. thick and supports measuring far-side surface recession in ablator materials.  JENTEK delivered the MWM-Array solution used by NASA KSC on the Space Shuttle Leading Edge to detect damage of the Reinforced Carbon-Carbon (RCC) thermal protection tiles; thus JENTEK is well-positioned to deliver a practical TPS NDE solution.
Thermal and environmental control systems for future exploration spacecraft must meet challenging requirements for efficient operation and conservation of resources.  Regenerative CO2 removal systems are attractive for these missions because they do not use consumable CO2 absorbers.  However, these systems also absorb and vent water to space along with the carbon dioxide.  We propose to develop an innovative water recovery system that minimizes water lost from regenerative CO2 control systems without the need for low-temperature condensing heat exchangers.  This approach addresses the need for water recovery systems in long-duration missions, reduces the need for consumables by enabling use of state-of-the-art regenerative CO2 removal systems, and minimizes demands on the spacecraft thermal control system.  In Phase I we proved the feasibility of our approach through proof-of-concept tests that demonstrated efficient water recovery from a compact exchanger with low pressure losses.  Trade-off studies using our mass transfer analysis models have yielded a design for a full-size prototype that meets all the requirements for service on future spacecraft.  In Phase II we will build the prototype and measure its performance in ground tests of a full-scale, regenerative CO2 removal system.
NASA has a critical need for improved bi-directional data transmission rates from a variety of spacecraft to Earth.  NASA estimates that the current Mars to Earth transfer rate of 6 Mbps might be increased to 600Mbps using a laser comm (LC) system.  Because the LC beam is less than 10 microradians wide and the Earth at apogee is 32 microradians wide, as seen from Mars, LC beam jitter caused by spacecraft base motion must be reduced to sub-microradian levels to enable beaconless optical beam pointing.  To meet the need, NASA is seeking innovative compact, lightweight, space-qualifiable vibration isolation platforms for payloads massing between 3 and 50 kg that require less than 15 W of power and mass less than 3 kg that will attenuate an integrated angular disturbance of 150 ur to less than 0.5 microradians (1-sigma), from &lt;0.1 Hz to ~500 Hz.  ATA has a long track record of producing stabilized platforms to host small optical payloads.  Building on a previous NASA SBIR, ATA now produces the stable platform used in NASA's LLST and LCRD programs.  ATA will create a Compact, Lightweight Isolation Platform (CLIP) that could host the LC collimator telescope and provide a stabilized platform to prevent the 150-microradian spacecraft disturbance environment from reaching the LC terminal.  Advances in the suspension flexure, the platform structure, and actuators will be required to meet the size, weight and power requirements.  One challenging requirement is that an angular-motion sensor is required for the control system.  Gyros exist that can measure adequately but they are too heavy, too large, and use too much power. ATA will develop a small, lightweight, nanoradian-class angular noise Capacitive Angular Position Sensor (CAPS).  The sensor will have low power and high reliability, which ATA will demonstrate by producing TRL 4 prototypes in Phase I.  ATA will develop the CLIP, a 0.5 microradian residual motion stable platform, in Phase II for programs like iROC.
The objective of this Phase I SBIR program is to develop polymer derived rare earth silicate nanocomposite environmental barrier coatings (EBC) for providing next-generation corrosion resistance and thermal insulation to Aerojet's Nuclear Thermal Propulsion (NTP) systems.  The NTP environmental barrier coatings will be developed from NanoSonic's innovate inorganic polymeric nanocomposite resins that crosslink to dimensionally stable gels under ambient conditions and gracefully transition to high temperature corrosion and thermally insulative resistant coatings at elevated temperatures.  Through a synergism of nanoparticle &amp;#150; rare earth silicate load transfer pathways, NanoSonic's proposed EBC topcoat technology will readily absorb and dissipate high velocity impact threats while providing exceptional thermal shock resistance necessary for enhanced survivability of nickel-chromium based alloys within current and future NTP rocket engine rocket thrust chambers and nozzles.  Working with team members Aerojet and the University of Washington, NanoSonic will molecularly engineer a family of rare earth silicate polymeric precursors that are specifically optimized for rocket engines within Aerojet's NTP space technology program.  

For the proposed effort, NanoSonic, the University of Washington and Aerojet have created an SBIR research team to rapidly identify, optimize and transition next-generation polymer derived rare earth silicate coatings specifically optimized to extend the operational utility of NTP rocket thrust chambers and nozzles.  Within this teaming partnership, NanoSonic will continuously synthesize and optimize rare earth polymeric precursor coatings whereas the University of Washington will test coated nickel-chromium based alloys within flow conditions simulating NTP rocket exhaust. ANSYS thermal modeling will be employed to interpret and jointly optimize promising rare earth silicate coatings with Aerojet.
In October 2011, NASA initiated the Nuclear Cryogenic Propulsion Stage (NCPS) program to evaluate the feasibility and affordability of Nuclear Thermal Propulsion (NTP).  A critical aspect of the program is to develop a robust, stable nuclear fuel.  One of the nuclear fuel configurations currently being evaluated is a cermet-based material comprised of uranium dioxide particles encased in a tungsten matrix.  To prevent excessive fuel loss from reaction with the hot hydrogen gas passing through the cooling channels, both the internal surfaces of the cooling channels and the exterior of the fuel element must be clad with a hydrogen compatible material such as tungsten.  To reduce the potential for uranium hydride formation that can lead to grain boundary separation and cracking, the diffusion of hydrogen into the cermet must be minimized.  Therefore, fine-grained tungsten claddings are needed.  Recently, advanced electrochemical processing techniques (EL-Form&amp;#61666;) have been developed that enable the tailoring of refractory metal microstructures through process parameter manipulation and/or alloy additions.  Therefore, these innovative electrochemical forming techniques will be used to produce fine-grained, hermetic tungsten claddings for both the internal and external surfaces of cermet based nuclear fuel elements.
The Mars Program Planning Group (MPPG) Final Report reiterates the importance of planetary sample return stating that sample return architectures provide a promising intersection of objectives for long term collaborations.  The proposed innovation is an enabling technology for robotic planetary sample return missions. The proposed concept is a passive mechanism that works within a larger sample drilling system.  Bear developed a complete planetary sample acquisition system called the Universal Sampling System (USS) which includes the baseline drill with Non-Rotating Technology (NRT Coring Drill) which was funded under a SBIR Phase 2 contract.  Bear has several concepts for creating additional capabilities among them is the proposed Surface Abrasion Tool (SAT).  The proposed innovation is a critical system component for meeting the science objectives of planetary sample return. Bear proposes to research and advance a Rock Abrasion (MER Rovers) like tool that can attach to and is driven by an existing coring drill thus requiring no additional motors.  The proposed innovation has broad significance for the exploration of planets and small bodies. The proposed project is directly relevant to the topic as it addresses the importance of technologies for robotic mobility, manipulation, and sampling for in-situ analysis or return to earth from planetary small bodies, including Mars, Venus, comets, asteroids, and planetary Moons.

Two main goals of the research are to:
1. Develop a method for attaching the surface abrasion tool to the larger coring drill without additional motors or wires. 
2.  Research the possible benefits/tradeoffs of cutting rather than grinding to remove rock surface with power constraints.
Regardless of which technique is used to prepare the surface (cutting or grinding), the passive tool will strive to reduce the time it takes to prepare rock surfaces versus state of the art.
Solar-blind ultraviolet (UV) imaging is critically important in the fields of space astronomy, national defense, and bio-chemistry. United Silicon Carbide, Inc. proposes to develop and commercialize a unique JFET-based monolithically-integrated radiation-tolerant solar blind active pixel sensor (APS) UV imager.  Silicon carbide is the ideal materials system due to its negligible dark currents, excellent radiation tolerance, intrinsic insensitivity to visible and near IR light, and technological maturity.  The Silicon carbide JFET is an ideal choice as an IC building block, as it is immune to the presence of stacking faults in wafer material and is free from possible threshold voltage drifting associated with the SiC MOSFET.
The proposed PiN and LJFET based APS circuitry has the potential for reliable operation at temperatures exceeding 150 C.  The proposed design of the active pixel sensor can be adopted for detection of more energetic particles, such as EUV and soft-X-ray, by increasing the thickness of the active low doped layer. Such APS detector arrays could be custom designed, including pixel size and epilayer thickness, and would be of nearly UNIVERSAL USE in nuclear particle detection and spectroscopy. 
While the active pixel sensor market is niche, applications in related Silicon Carbide LJFET based analog processes offering temperature operation above 200 C have tremendous value in the commercial, industrial &amp; high temperature market space.  LJFET IC building blocks such as voltage references, oscillators, comparators and regulators form the cell circuits for such products as PWM controllers, power transistor gate drivers, voltage regulators and amplifiers.
We build a tool that accelerates Research and Development (R&amp;D) aimed at introducing Unmanned Aircraft Systems (UAS) into the National Airspace System (NAS).  In the proposed effort, FACET will form the basis of a collaborative R&amp;D platform, an environment where users can share open source software modules (software and data sets developed to reside outside the FACET Application Programmers Interface (API)) between users at the same or different universities, so that each user can benefit from the open source software and data contributions of others.  Thus, when a student who has never used FACET before enters into a collaborative study of UAS integration in the NAS, he/she is able to download open source software and data to get going on rich R&amp;D experiment without having to start from scratch.  A student can download weather data sets, Special Use Airspace (SUA) data, air traffic demand data, UAS models (e.g., Base of Aircraft Data (BADA)) and flight plans, metrics, or anything that is posted on the open source library, to get a "running start" with R&amp;D.  When completing innovative modules outside the API, the student can post software to the open source repository for others to benefit.  This collaborative environment will also allow for FACET-based research to be performed in a distributed manner &amp;#150; where simulations at one university may be run with models and parameters provided by other users at different universities, and the results posted back to the common repository for all users to share.  This open-source collaborative platform is demonstrated on R&amp;D problems aimed at introducing
Final Frontier Design (FFD) proposes to develop and deliver an advanced pressure garment arm with low torque and high Range of Motion (ROM), and increased durability, using their unique single layer approach to the pressure vessel joint.
	FFD has developed a flat patterned asymmetric shoulder joint for their current space suit pressure garment, with a natural position in human rest adduction, approximately -10 degrees.  In addition, this joint has a focused point of rotation, like the human shoulder. Their design reduces discomfort from gathering of fabric in the armpit, provides a large ROM, favorable torque, and allows for close tracking of natural human anthropometry.  In addition, FFD's elbow joint design show consistently high performance, in terms of ROM, torque, and operating pressure.
This proposal also utilizes a unique approach to the pressure garment: the single layer integrated pressure garment joint as opposed to a traditional double layer bladder-restraint pressure garment.  FFD's pressure garments have a host of important advantages over double layer pressure garments, including a lower mass, increased ROM, decreased torque, a thinner wall, the reduction of suit layers, the elimination of  indexing, lower cost manufacturing, and flat-patterned ease of scaling and repeatability.  
 This proposal will develop two design iterations of FFD's single layer pressure garment arm, to include both the elbow flexion-extension joint and the shoulder ad-abduction joint.  The arms will be designed and tested for +8PSI operating pressure, to meet current ROM standards of NASA's pressure garments and test and increase FFD's technology cycling ability.  FFD aims to increase their TRL in this project from 4 to 6 through Phase II of this contract.
United Silicon Carbide, Inc. proposes to develop a novel compact, efficient and high-temperature power module, based on unique co-packaging approach of normally-off silicon (Si) MOSFET with silicon carbide (SiC) normally-on power JFET in a cascode configuration. A much desired silicon MOS gate control is provided readily compatible with the conventional gate drivers, making a proposed module a plug-in replacement for conventional Si IGBT modules offering smaller size and higher power density, lower conduction and switching losses, and higher operating temperature for a wide range of civilian, aerospace and military applications, where compact power converters are needed with minimum cooling requirements.
The proposed hybrid Si/SiC cascode approach offers substantial improvement in module power density, by up to 50&#37;, with unique packaging approach, greatly reduced size of a power switch, and elimination of separate antiparallel diode, which is replaced with an intrinsically fast and efficient body diode of a low-voltage Si MOSFET. Significant reduction in static and dynamic power losses compared to Si IGBTs and SiC MOSFETs are achieved by utilization of a fast switched normally-on SiC JFET with ultra-low on-resistance and hence much lower static and dynamic losses than state-of-the-art Si IGBTs and SiC MOSFETs.
It is hard to understate the need for compact power converters in aerospace applications, where the allowed on-board space and the weight for the power management systems are very limited. The proposed cascode power module will also enable circuit designers to provide significantly smaller, more reliable, more efficient and lower cost solutions for more mainstream applications such as power factor correction circuits, photovoltaic micro-inverters, power supplies, motors &amp; pump drives, industrial power converters, and consumer appliances
.
In this program, Innovative Technology Applications Company (ITAC), LLC and collaborators propose to advance "synthetic phased array" technology to improve understanding of noise from landing gear. The technology, initially developed in a previous NASA SBIR project for trailing edge noise, will be applied to improve beamforming analysis methods, facilitate the design of more effective microphone arrays, and significantly enhance the understanding and characterization of noise sources from landing gear.
The proposed approach involves the use of Large Eddy Simulation (LES) to generate data on the nearfield unsteadiness in jet flows. The nearfield noise is then numerically propagated to the farfield phased array microphone locations. Beamforming analysis methods will be used to predict noise source locations, and these predictions will then be compared with the original LES results. Discrepancies between the phased array prediction and the LES flowfield results will be used to guide development of new and improved phased array source models, as well as develop improved methods for positioning Ffowcs-Williams Hawkings (FWH) integration surfaces around complex noise-generating configurations such as landing gear.
When fully developed, this technique offers the potential for significant benefits. First, it will empower experimental aeroacoustics researchers to customize the layout of microphone arrays for a given experimental configuration. Similarly, this approach offers the potential to customize the analysis of the recorded data they take for optimum accuracy. Beyond this, the improved FWH and beamforming methods that will be developed using this technique will benefit any experiment which makes use of phased arrays of microphones. Finally, the work will add to the overall understanding of landing gear noise.
The ability to successfully manage thermal loads is increasingly a primary design constraint for many emerging engineered systems.  Systems ranging from military aircraft to computational platforms to photovoltaic (PV) power generation all generate unwanted heat and traditional methods for transporting and removing this heat are often heavy, cumbersome, power hungry, or lack adequate heat removal capacity.  Excess heat can result in reduced efficiency in PV systems, limit duty cycles for pulsed power applications, and ultimately cause failure of critical components if not managed properly.  Similar problematic scenarios exist for many power generation systems, high power radio frequency (RF) devices, portable electronics, and lasers, to name a few.
	A host of thermal management techniques are currently available including heat pipes, liquid immersion, jet impingement and sprays, thermoelectric coolers, and refrigeration.  While these techniques are adequate in some cases, none of these methods alone can meet the needs of future high power thermal management without incurring large penalties of weight, power, or volume.  The technology proposed here overcomes these limitations through autonomic, self-powered, and self-cooling functionality by directly converting the unwanted thermal energy into useable mechanical energy for use in coolant pumps or refrigeration compressors.
Flight-testing is a crucial component in NASA's mission to research and develop new aeronautical concepts because it allows for verification of simulated and wind-tunnel experiments and exposes previously unforeseen design problems. Video is an invaluable tool for flight-testing, allowing the collection of a wealth of information such as craft position, speed, health, as well as tracking different phases of flight, capturing events, extracting performance figures, and documenting historical flights.  For several cases of interest (high-speed/high-altitude aircraft, lakebed remote landings, vehicle re-entry, smoke airflow traces, etc.) it is not feasible or physically possible to install external cameras close to the aircraft whose behavior is being filmed.  Long-range imaging equipment is typically used in these cases, but the captured footage is severely limited in quality by atmospheric effects, which are often the dominating source of image degradation, long before diffraction-related limitations occur.  In consequence, long-range imagery typically suffers from scintillation, blurring, poor spatial resolution, and low contrast.  Since these problems result from atmospheric conditions, they cannot be overcome by simply improving imaging hardware.  What is needed is a solution to combat atmospheric distortion.  In Phase I, EM Photonics demonstrated a signal processing technique based on initial research from Lawrence Livermore National Laboratory.  We modified and implemented this core algorithm and showed its ability to enhance imagery collected from the long-range imaging systems at NASA DFRC.  In Phase II, we will evolve and integrate the prototype components developed in Phase I and deliver an image enhancement device capable of running in real time to mitigate the image distortion present in data collected from NASA DFRC's long-range cameras.
ORBITEC, in collaboration with Lucigen, proposes a rapid nucleic acid-based detector for spaceflight water systems to enable simultaneous quantification of multiple waterborne pathogens with minimal consumables and crew time. The Rapid Multiplex Microbial Detector (RMMD) amplifies the genetic material in a liquid sample to allow near real-time identification of specific genetic sequences of predetermined bacteria and fungi. This easy-to-use device incorporates a patented polymerase enzyme that enables rapid RNA amplification by reagents with superior long-term shelf life and thermal stability. To operate, a water sample is injected into the RMMD, where it is concentrated and mixed with the reagent. The RMMD is rapidly heated and maintained at an elevated temperature for approximately 15 minutes, then quickly cooled back to room temperature to amplify the genetic material in the sample, which is detected in real time by changes in fluorescence due to dye binding, thus providing quantification. pathogenic cells in the water sample can be rapidly detected quantitatively based on the time of development of fluorescence. Phase 1 activity will result in prototype hardware and software genetic amplification and detection of several pathogenic bacteria and fungi that will bring the technology to TRL 5. The anticipated results of the Phase 2 are an engineering development unit that consists of an amplification/detection process controller, sample cartridges, and reagents, that can be tested in space.
NASA has numerous missions that involve radar and radiometry. In the past, the practice has been to build each system as a one-off program, which makes MMIC design unattractive from a cost perspective. In an era of reduced budgets and the need for higher efficiencies both in R&amp;D cost reduction and performance, a better approach is needed. Linear Signal proposes a wideband analog blockset approach, where critical design blocks can be used at multiple bands, on multiple platforms, and for both radar applications and satellite communications markets. Transceiver components can be used for chips targeted for communications application or radar application from P band through X band, for pulsed, chirped pulse and FMCW applications. The work proposed in Phase I and II would result in core IP blocks that can be quickly and relatively inexpensively adapted to a single chip radar transceiver for mission specific objectives. Linear Signal's expertise in wideband SiGe designs and beamforming applications is perfectly suited for this effort.
This SBIR Phase I project will deliver a breakthrough in particle-detection sensors, by integrating an amplifying junction as part of the detector topology.  Focusing on energetic particle detection in the heliosphere, the resulting leap in the resolution with which the deposited charge is measured results in far more precise energy and position measurements, from which the certainty in the particle identification is increased.  Silicon is chosen as the material upon which the avalanche particle detector (APaD) will be developed because it possesses high stopping power for ions, low material cost, and an extensive microelectronic fabrication base.  We have previously made both: a) low-noise silicon detectors for ion and high-energy sensing, and b) avalanche photodiodes (APDs) for optical photon sensing.  The objective of the project is to integrate the two topologies so that we can compare the energy resolution with and without on-chip amplification across the energy range 10 keV &amp;#150; 3 MeV, with a goal of three times improvement in resolution at 80 keV.
We proposes to build a prototype Convective-Induced Turbulence (CIT) hazard detection system based on total lightning sensing as an indicator of the location and severity of in-cloud CIT.   Total lightning is the combination of cloud-to-ground and in-cloud lightning and has been shown to correlate well with storm dynamics. Total lightning activity will be measured globally at high temporal resolution from total lightning detectors onboard future geostationary satellites such as the Geostationary Lightning Mapper (GLM) on the Geostationary Operational Environmental Satellite R-Series (GOES-R) and the Lightning Imager (LI) on the Meteosat third generation satellites. Thus, we seek to investigate the relationship between in-cloud convective turbulence and total lightning measurements, and determine the skill of total lightning as an indicator of in-cloud CIT.  We investigate how to use proxies for GLM lightning data to enhance the diagnosis of hazardous turbulence over the Continental United States (CONUS) where verification data is readily available from ground-based (radar-based) systems.   This system will enhance safety of flight for aircraft in the CONUS as well as oceanic and global airspace.  Such a technology would be useful to all aircraft that fly, from General Aviation (GA) aircraft to Unmanned Air Systems (UASs) to business jets and commercial jets.
U.S. space exploration missions have long considered returning to the Moon and exploration of Mars that challenge life support systems. For these long duration missions, NASA is interested in replacing the iodine water treatment system with ionic silver. Although iodine treated water has been used successfully with the International Space Station, its use requires that the iodine be removed before being consumed by astronauts due to its adverse effects on the thyroid. For long duration exploration missions, minimal mass systems are desired that lessen logistical supply requirements for storing and distributing potable water. In particular, it is imperative that an effective biocide is used that prevents microbial growth, biofilm formation, and microbially induced corrosion in the water storage and distribution systems. To address these needs, Reactive Innovations, LLC proposes to develop an electrochemical silver ion generator that produces an effective biocide concentration throughout the water storage and distribution system. The generator and system control will also minimize spurious deposition of silver on the wetted components of the water system maintaining a viable biocide activity to prevent biofilm growth. Materials compatibility testing will be examined with the generator to assess long duration operation.
Surface temperatures in atmospheric reentry simulations range from 1500-2300 K, while stagnation temperature on the leading edge of a Mach 6 flight vehicle at 25 km altitude is 1817 K.  Sensors that can operate at temperatures well above 1273 K are needed to provide reliable validation data for TPS modeling and design tools.

We propose to develop a low-intrusive fiber-optical pyrometer capable of measuring temperature profiles within an ablating thermal protection system (TPS).  In this concept a bundle of parallel sapphire fibers is embedded in a step-wise manner into a multilayered "plug" of TPS material.   The sensing tip of each fiber consists of a metallic coating, forming an isothermal cavity; graybody emission from this cavity is transmitted through the fiber to a fiber-optic multiplexer, and thence to a compact near-infrared (NIR) spectrometer.   By fitting the thermal spectrum from the shortest fiber to a Planck distribution (adjusted to account for spectral absorption in the sapphire fiber), a cold-side temperature can be inferred first.  The next longest fiber can use this temperature to estimate the distorting effects of self-emission in the heated fiber.  Sequential evaluation of fiber tip temperatures at known locations along the bundle will allow effective estimation of temperature gradient and subsequent calculation of heat flux.

The proposed fiber-optic sensors are thermally and physically robust, lightweight, electrically passive, and immune to electromagnetic and radio-frequency interference.  Additionally, our proposed fiber-optic pyrometer is optimized for high temperatures.  As the TPS-embedded sensing tip temperature increases, the wavelength peak for the thermal emission spectrum moves from 2634 nm (at 1000 K) to 1260 nm (at the sapphire melting point of 2300 K), while the integrated spectral intensity increases as the 4th power of the temperature.  Both effects improve the pyrometer signal-to-noise ratio.
Integrate advanced nanotechnology with energy storage technology to develop advanced cathode materials for use in Li-ion batteries while maintaining a high level of safety, stability, and cycle life, allowing the cathodes to be tailored to provide very high specific energy or very high specific power depending on the relative ratio of the three components-active material, current conductors/collectors, and binders, thus maximizing specific energy (Wh/kg) and energy density (Wh/l).
Emergent Space Technologies proposes to develop a flexible, service-oriented Fault Management (FM) architecture for cluster fight missions. This FM architecture will include algorithms to be run on each cluster module for fault detection, isolation, and recovery, software to be used at a ground station to direct recovery actions, and protocols for communication of fault information between cluster modules and between modules and the ground station. Individual components of the architecture will be designed so that they do not work together directly, but interact through predetermined interfaces. This will allow for flexibility, scalability and robustness. During Phase 1 of the proposed research, the focus of the research will be a fault detection and isolation system to be incorporated into the FM architecture.
Refueling spacecraft in space offers tremendous benefits for increased spacecraft payload capacity and reduced launch cost.  A key technology challenge for space refueling is the storage of liquid cryogenic fuel in space.  To meet this need, we propose to develop a reliable, compact, efficient cryogenic mixing pump with no moving parts.  The mixing pump will prevent thermal stratification of the cryogen and simplify pressure control for storage tanks.  The mixing pump uses an innovative thermodynamic process to generate fluid jets to promote fluid mixing, eliminating the need for mechanical pumps.  Our innovative mechanism will be able to self-prime and generate a high-pressure rise.  The device will significantly enhance the reliability of pressure control systems for storage tanks.  In Phase I, we will prove the feasibility of our approach through building and testing a proof-of-concept mixing pump and developing an analytical model to optimize the mixing pump design.  In Phase II, we will build and test a laboratory-scale cryogenic mixing pump and demonstrate its performance in a representative cryogenic environment.
Single crystal silicon is a desirable mirror substrate for scan mirrors in space telescopes. As diameters of mirrors become larger, existing manufacturing capabilities of single crystal silicon (SCSi) cannot supply sizes that are larger than about 450 mm in diameter. Onyx Optics proposes to develop a process based on our established technique of Adhesive-Free Bonding (AFB&amp;#174;) of single crystals, optical ceramics and glasses that can produce sizes that are larger than commercially available SCSi. The precision composites, consisting of SCSi components, are expected to perform as well as a single crystal. Precision grinding and polishing of large composite SCSi without subsurface damage is a desirable feature for large scan mirror substrates. As part of the proposed manufacturing process, Onyx Optics proposes to develop a technique that is based on electrolytic in-process dressing (ELID) of grinding wheels of decreasing diamond grain sizes. The process is generally applicable to ductile grinding of hard materials such as glass, sapphire, silicon carbide, silicon nitride and SCSi and is known to result in low stress components. 

Composite SCSi interfaces will be charactized interferometrically at 1.55 micron by their transmitted wavefront. Heat transfer measurements across bonded interfaces of SCSi will be performed at room temperature and liquid nitrogen. Equi-biaxial fracture strength of composite disks will be determined and compared with control disks.
We propose a portable data acquisition and prognostic system that contains both hardware and software with several innovative ideas. First, our hardware system consists of a high speed data acquisition card and a portable lunchbox PC. The portable lunchbox PC has advanced prognostics algorithms and user friendly Graphical User Interface (GUI) for displaying component fault status and trends. Second, the prognostics software has several innovative algorithms, which will be implemented in Labview. The first one is an adaptive physics based prognostic tool. The idea is motivated by damage mechanics, which associates the vibration amplitude and natural frequency of the vibration to the damage status. This idea has been experimentally proven to be very accurate in bearing failure prediction. The second prognostic tool is data driven and is a Hidden Markov Model (HMM) based approach that can predict the degraded state of the system. Tests using experimental data showed that the various degraded states can be correctly and unambiguously identified by the algorithm. The third tool is a hybrid one and was proven to achieve very high performance in the 2008 PHM Challenge. Finally, to further enhance the prognostic performance, we propose to apply Dempster Shafer algorithm to perform prognostic fusion.
Luna Innovations Incorporated is proposing to design, build, and test a shape, length, and tension sensing tether for robotic exploration and sample-gathering missions on remote planets and moons.  The proposed tether system is capable of determining the location and orientation of marsupial robots as they navigate difficult terrain.  The tether system will also provide shape and tension information along the entire tether, distinguishing elevation changes, tension due to snags, and potential points of harm.  The tension feedback is particularly crucial, as it can be used to determine whether the rover has fallen down a slope or cliff, lost traction, or whether it is still moving under its own power.  The system is based on Luna's unique fiber optic position and shape sensing technology, and is an enabling technology for obtaining images, data, and samples in areas with difficult terrain.  In addition to providing new, vital feedback, the fiber optic shape sensor within the tether is lightweight, small, and flexible.  Luna's unique shape sensing fiber also has the potential to provide both communication and power through the same fiber, further reducing the size and weight of the total tether package.
Busek proposes to develop a high performance, non-toxic storable, "green" monopropellant thruster suitable for in-space reaction control propulsion.  The engine will deliver 100N (~25lbf) vacuum thrust with specific impulse exceeding 240sec.  Estimated Isp-density is on the order of 348 sec-g/cc, a 48&#37; increase from the state-of-the-art hydrazine systems.  The most important feature that sets this thruster apart from other similar devices will be the use of an innovative, long-life catalyst.  This proprietary catalyst, constructed without any bed plate or ceramic substrate, was recently demonstrated in Busek's 0.5N micro thruster.  It has shown the ability to suppress catalyst-related performance degradation problems that often plague green monopropellant thrusters.  
	The proposed Phase I program will focus on developing a 5N green monopropellant thruster by scaling up the long-life catalyst design from the 0.5N thruster.  Both empirical and modeling works are proposed to validate the scaling theory.  Thruster performance will be evaluated based on hot-firing test results that include c* and vacuum thrust measurements.  The Phase I findings will lead to the design of a full-scale, 100N green monopropellant thruster to be developed in Phase II.
This program focuses on reducing the cost of substrate reclaim for high-efficiency solar cells fabricated via an epitaxial lift-off (ELO) process, while increasing the number of reuse cycles possible for a given substrate.  We will introduce a new multi-layer etch-stop structure into inverted metamorphic (IMM) triple-junction solar cells grown on 100-mm GaAs substrates.  The etch-stop structure will be grown between the original GaAs substrate and the ELO release layer, thereby becoming the effective substrate surface after the ELO process.  The purpose of the etch-stop structure is to prevent pits and surface damage incurred during ELO from damaging the original GaAs surface.  
The standard method of reclaiming the GaAs substrate after ELO is to employ chemo-mechanical polishing (CMP) to remove the defect-ridden GaAs surface and chemically polish the underlying GaAs to a yield surface that is suitable for successive epitaxial growth.  This process works effectively but reduces resultant substrate thickness and causes some wafer damage itself, which then requires further polishing.  These factors accumulate over time, practically limiting the number of reclaim cycles to 5&amp;#150;10 for a given substrate.  
With the incorporation of the proposed multi-layer etch-stop structure, the defects are isolated in the etch-stop structure, which can be dissolved by successive selective wet chemical etches to produce the original pristine GaAs surface with its original thickness.  All mechanical polishing is eliminated in this proposed work, ensuring a constant substrate thickness through repeated substrate reclaim cycles and also drastically reducing the estimated cost of the recycling process to &lt;$1 per substrate.
An approach for maximizing Hall thruster electrical system efficiency is to power the thruster directly from a high voltage solar array by a method commonly referred to as direct-drive.  These direct drive system designs eliminate the power processing unit (PPU) and therefore have a substantial advantage in terms of overall electrical efficiency and mass savings.
  
This Phase I/II proposal effort is comprised of the development of a Hall thruster direct drive unit (DDU).  The DDU will include a method for cathode current sharing such that multiple thrusters can be operated in parallel from a single power source.  In Phase I cathode current sharing approaches will be experimentally investigated.  Approaches to be evaluated include passive and active methods of cathode current control.  Active approaches involves independently controlled voltage sources placed in series with each cathode while passive approaches involve controlling cathode emission using  heater and keeper power.  In Phase II we will develop a nominal 15kW proto-flight brassboard level DDU and deliver it to NASA for additional characterization testing.  The DDU unit will include the balance of PPU per specifications provided by NASA for thruster magnets, cathode heater and keeper etc. operation.
NASA's "Ground Systems Development and Operations Program" is moving towards transforming parts of the Kennedy Space Center from a historically government-only launch complex to a spaceport bustling with activities involving government and commercial vehicles alike. The success of this transformation drive largely depends on achieving the ability to process multiple types of vehicles, within a rather short time and in an economic way. QSI proposes developing a COTS (Commercial off-the-Shelf) Software to facilitate 'Plug and Play Real-time Diagnosis for Ground Processing System Integration' to support achieving the objective of the program. QSI will add capabilities to their TEAMS (Testability Engineering and Maintenance System) toolset such that it will enable NASA to perform diagnostic analysis for various vehicular and ground systems without the requirement to build the analytic models and software tools from ground-up. Here, NASA is only required to build the diagnostic models (required for system integration, testing, assembly, maintenance/troubleshooting and pre-launch checkout) of the systems. Upon building, those can be used in a plug-and-play fashion through the analytic/diagnostic environment of TEAMS in conjunction with monitored data and test results from the vehicular and ground systems for obtaining diagnostic, prognostic, time to alarm, time to maintenance, etc. decisions.
The Phase I objective is to develop a preliminary design and manufacturing plan for carbon fiber composite reflectors and/or a carbon fiber telescope that are traceable to the requirements of current and future CMB missions.  The Phase II objectives are to complete the design and manufacturing planning, fabricate necessary tooling, manufacture hardware components that include two reflector support structures, integrate and align the reflectors and confirm telescope optical performance via analysis of as-built mechanical alignment and surface accuracy data.  To prepare for and conduct the PDR within six months, the proposed Phase I tasks will include:  1) Develop telescope requirements in conjunction with CMB researchers and/or NASA with the goal of resolving sufficient detail to evaluate CFRP technology for CMB missions, 2) Compare the requirements to CFRP heritage, as-built results, and experience, 3) Develop a concept based upon high (currently 4-9) TRL CFRP component technologies, 4) Predict the performance of the concept, 5) Develop a pricing model to predict recurring cost, 6) Define a preliminary manufacturing plan that includes predicted versus budgeted errors, 7) Develop a summary technical/cost compliance matrix that summarizes all technical and cost predictions versus requirements, 8) Summarize all engineering, manufacturing, and cost information in preparation for PDR including the envisioned path to telescope TRL6 during Phase II, and 9) Conduct a PDR with support from mechanical, optical, structural, thermal, materials, and manufacturing engineers.
Ventions proposes the development of a pump-fed, 2-stage nano launch vehicle for low-cost on demand placement of cube and nano-satellites into LEO. The proposed vehicle uses high T/W and Isp pump-fed engines that operate at chamber pressures &gt;750psi without the weight penalty of high pressure tanks, thereby realizing payload fractions in the 1-2&#37; range.  Ventions has already completed several component-level demonstrations in the area, and is proposing additional optimization / testing of a 5,000lbf LOX / RP-1 turbopump-fed engine as part of this Phase I in-order to demonstrate a flight-ready 1st stage propulsion system.
For a wide range of remote sensing applications, there is a critical need to develop imaging arrays that simultaneously achieve high spatial resolution, high sensitivity, and sub-nanosecond timing resolution. Many of these remote sensing applications furthermore are satellite and space based, where the imaging array also needs to be rad hard; particularly for the harsh radiation environments typically found on certain deep space missions, such as to the moons of Jupiter. LightSpin Technologies is developing a high performance solid-state cross-strip anode imaging single photon avalanche diode (SPAD) array technology using rad hard GaAs SPAD arrays. This approach promises substantial improvements in spatial resolution (&lt; 10 microns), timing resolution (&lt; 100 psec), and count rate (&gt; 10 Gcps). LightSpin has proven the concept provides excellent performance in small arrays (8 X 8 pixels) and developed a theoretical foundation enabling rapid scaling of the arrays to achieve Megapixel resolution at low cost.
A novel design for an in situ air sampling sensor for CO2 and trace gases is proposed. The sensor, named AirCore, provides the advantages of existing in situ sensors (e.g. high resolution) but eliminates possible biases in analysis that often originate from imperfect measurement condition. The AirCore provides a significant savings in cost and weight while increasing the capabilities of existing in situ sensors. The AirCore system consists of the AirCore gas sampler and the support system to accomplish its high altitude (nominally 70,000+ ft.) mission. This support system includes the sensor launch and recovery components. The AirCore can be launched and recovered by a limited crew, which reduces the operational cost of the system.
Development of a nonlinear particle filter for engine performance is proposed. The approach employs NASA high-fidelity C-MAPSS40K engine model as the central element, and addresses the issue of lack of observability of some of the engine health parameters in previous Kalman filter formulations. Proposed approach does not require linearity of the dynamics or Gaussian noise assumptions for satisfactory operation. The feasibility of real-time implementation of the proposed approach will be demonstrated using commercial, off-the-shelf General Purpose Graphical Processing Units.  Phase I feasibility demonstration will show that the particle filter formulation of the engine performance monitoring system can overcome the limitations of previously employed approaches. Phase II research will develop a prototype implementation for hardware-in-loop simulations and eventual flight test.
A compact microgravity and hypogravity compatible vacuum device is proposed to provide medical suction and containment of extracted fluids.  The proposed aspirator will draw up to 40 L/min of air and produce a nominal vacuum of 500-mm Hg, which is comparable to commercially available medical aspirators.  The unit will also provide a means for separation and containment of up to 1000 mL of aspirated fluids.  Waste material separation will be accomplished by a reticulated foam trap that will utilize hydrophilic adsorbent materials to sequester liquids within the reticulated foam structure.  The aspirator assembly will also include a sub-micron filter to prevent aerosol from escaping to the spacecraft cabin.  During the Phase I research, an efficient trap will be designed and tested using a commercial off the shelf (COTS) vacuum pump.  Additional trap features will be investigated including collapsible walls to minimize storage space and chemical resistance to enable suction of corrosive and/or toxic materials.  Phase II research will focus on improving overall ESM and incorporating features such as a trap fill level indicator, an emergency shutoff in case of liquid breakthrough, and an alarm indicating a blocked airway, which will improve microgravity performance.
In this proposal, we propose to demonstrate and build a widely tunable, narrow linewidth, single frequency fiber laser near 2.05 micron by developing an innovative Ho-doped single mode fiber. Such near 2.05 micron fiber laser is needed for coherent lidar and interferometric fiber sensing. Based on our successful demonstration in Phase I, our newly developed Ho-doped fibers have the capability of single frequency fiber laser operation in a wide spectral range from 2040nm up to 2100nm. In Phase II, we will further optimize our innovative H0-doped single mode fiber, develop a new laser cavity design for fast and broad tuning, build a deliverable prototype laser unit with wide mode-hop-free fast tuning to NASA.
This SBIR Phase I effort proposes to establish the feasibility of leveraging advances in compact laser technology with integration of space qualified techniques into AdvR's Planar Lightwave Circuit (PLC) and iodine reference cell technology for the design of a space qualifiable,  frequency stabilized seed laser system in support of  NASA Langley's High Spectral Resolution Lidar (HSRL) program. The Phase II effort will focus on space qualifiable systems integration, packaging, and testing of the locked seed laser system under applicable environmental conditions. Successful development of this technology, due to its compact, efficient, and reliable design, will enable further uses of the HSRL-based remote sensing system both in current flight-based systems and in future space-based systems.
Complex aeroelastic and aeroservoelastic phenomena can be modeled on complete aircraft configurations generating models with millions of degrees of freedom. Starting from a freely supported version of the model, a two-step model reduction process is proposed to create aeroelastic models that include rigid body dynamics. In the first step, proper orthogonal decomposition at a set of flight conditions reduces the model order from millions to hundreds of degrees of freedom. In the second step, a linear matrix inequality further reduces the order and creates a linear parameter varying reduced order model. The model includes a trimmed and parameterized description of aeroelastic forces valid over a region of the flight envelop. The same model can be used for rapid simulation and for linear parameter varying flight control design. Feasibility of this two-step process has been demonstrated in the Phase I work and a plan has been developed for a prototype implementation. Specific improvements to the rigid body model, technical risks in the development effort, and a risk reduction plan have been identified. An X-56A vehicle model will be developed and then used to demonstrate the model reduction process and to demonstrate applications including a linear parameter varying flight control system.
Bridger Photonics Inc. (Bridger) proposes to develop the most compact, efficient and low-cost ultra-violet ozone differential absorption lidar (DIAL) transmitter available.  This system will use a frequency-doubled, conductively-cooled, q-switched Nd:YAG laser to pump a combination optical parametric oscillator (OPO)  and sum frequency generation (SFG) cavity to deliver 6 ns, 1.5 mJ and 1 kHz pulses at three wavelengths within the 280 nm to 316 nm ozone DIAL band.  Bridger will employ mechanically robust and environmentally insensitive monolithic laser and OPO designs making the transmitter well suited for continuous DIAL measurements from ground-based, airborne and space-based platforms.  Bridger estimates that the high efficiency and compact packaging offered by the proposed pump laser and OPO will result in an ozone DIAL transmitter that weighs &lt;30 kg (including the control electronics), consumes less than 550 W of power at 110VAC, and costs less than $75,000 per unit.
Microelectromechanical systems (MEMS) technology has the potential to create deformable mirrors (DM) with more than 10^4 actuators that have size, weight, and power specifications that are far lower than conventional piezoelectric and electrostrictive DMs. However, considerable development is necessary to take state-of-the-art DMs today and make them flight-like. This Phase I SBIR proposal addresses two critical areas in MEMS DM development towards the goal of developing flight-like hardware. Namely, Phase I research will further develop Iris AO's proven hybrid MEMS DM technology to: 1) make a critical assembly step in the fabrication process scalable to wafer scales and 2) increase drive electronics resolution to 16 bits while simultaneously reducing power requirements more than three-fold over existing 14-bit resolution electronics. The increased spatial and actuator resolution afforded by the development here will enable picometer resolution DMs required to reach 10^10 contrast levels necessary for direct detection of Earth-sized terrestrial planets.
The proposed work will provide NASA with an integrated visualization environment providing greater insight and a more intuitive representation of large technical data sets. Engineering framework tools now provide a new level of integration with systems engineering, high fidelity computation, mission modeling, and collaborative infrastructures. Innovative visualization technology is required to represent the larger and more complex outputs generated by these frameworks. Our proposed solution will address these issues by developing a visualization environment designed from the start to handle extremely large data sets and providing greater flexibility in terms of the graphical output types that can be produced. This work will involve the use of software technology to parallelize operations, use the GPU, improve memory allocation, and use modern libraries such as OpenGL for efficient rendering. Algorithms to study the "white space" in trade spaces and extend Pareto frontiers into these blank areas will be included. New data mining and clustering algorithms for obtaining insight into complex data sets, involving many parameters, will be built into the visualizer.  Features to interact with the underlying computational model (in ModelCenter) and change it easily to observe its effect on the visualized output will be provided. A representative example will be created as a means of demonstrating the new features to NASA and industry. The example will incorporate several new framework technologies (MBSE, mixed fidelity modeling, etc.) and show how the new visualization environment complements these. The new visualizer will be incorporated and commercialized within ModelCenter as a plug-in alongside existing visualization environments.
Wireless Sensor Technologies has for several years been developing a passive Wireless Temperature Sensor (WTS) for gas turbine engine and other harsh environment applications under the under sponsorship of the Air Force (Non-destructive Test Program) and the Navy (SBIR Topic N08-004).  Once productized, the functional and operational goals for the sensor as they relate to the gas turbine engine are to:

? Measure the surface temperature of the Yttria Stabilized Zirconia Thermal Barrier Coatings (YSZ TBC's) typically applied to turbine blades in the hot section of the gas turbine engines
? Measure temperature at specific locations on the surface of the combustor liner to determine both radial and circumferential temperature variations (pattern factor)  
o Thin film passive wireless sensors will be arrayed in an annular ring around the combustor to determine pattern factor in an effort to sense the uniformity of combustion downstream from the fuel injectors.
? Measure the surface temperature of any area of interest using a weldable coupon version of the wireless temperature sensor
? Measure heat flux across the section thickness of thermal barrier coatings by pairing several of the proposed wireless temperature sensors (for the surface temperature measurement of TBC's.

This program will characterize the longterm drift and reliability of the WTS and in Phase 2 result in a sensor with a TRL level of 6 to 7.
This SBIR project is to develop a novel Hemispherical and Dynamic Camera(HDC) with ultra-wide field of view and low geometric distortion. The novel technology we proposed would lead to ultra-compact, low-power, light weight, and high resolution hemispherical camera for EVAs.   We successfully completed the Phase 1 project with a novel optical design, functional prototypes, extensive experimental results and commercialization potential. All Phase 1 objectives are met and exceeded.
Phase 2 program will afford us to design and build a fully functional miniature EVA camera systems, and perform extensive tests for NASA's EMU and EVA applications. Capitalizing upon the breakthrough we have made thus far, we propose the following Phase 2 technical objectives:     
Objective 1:   Design and build a fully functional prototype of the EMU camera system; 
Objective 2:   Carry out extensive validation experiments and improve the EMU camera prototype;
Objective 3:   Design and build a prototype of EVA Smart PTZ camera; 
Objective 4:   Carry out extensive validation experiments and improve EVA Smart PTZ prototype;
Objective 5:   Work closely with COTR to facilitate NASA applications and broad adoption of the Neo360 optics and Smart PTZ technologies developed under this SBIR;
Objective 6:   Pursue commercialization of the developed Neo360 and Smart PTZ technology.
In this Phase I research, ZeCoat Corporation will develop an affordable, low-stress silicon cladding process which is super-polishable for large UVOIR mirrors.  The proposed ion-assisted evaporation process is directly scaleable to SiC mirrors several meters in diameter.  The process is based on a novel, low temperature, ion-assisted, evaporation technique (IAD), whereby the coating stress of a silicon film may be manipulated from compressive to tensile, in order to produce a near-zero net stress for the complete layer.   A cladding with little intrinsic stress is essential to minimize bending that would otherwise distort the figure of very lightweight mirrors.   
Current methods to produce a polishable silicon cladding utilize CVD processes that produce highly stressed Si coatings.  The current processes require high-temperatures (hundreds of degrees Celsius) and are not readily scaleable to large mirrors.  CVD Si cladding is currently limited to mirror substrates less than 1-meter in diameter.   The proposed IAD process produces little heat, and the mirror size is limited only by the size of the vacuum chamber.
Large silicon carbide (SiC) mirrors (3-4 meters in diameter) are being considered for future space-based UVOIR astronomy missions.   These lightweight mirrors will likely require a highly-polishable layer of silicon (10 to 50 microns) applied on top of the SiC.   A relatively thick layer of Si is desirable for the purpose of reducing figuring time and for achieving a super-polished surface, suitable for UV astronomy. 
	Normal incidence 4-meter class UVOIR telescopes have been cited as a high priority by multiple government review panels including; the National Research Council's (NRC) study of NASA's Space Technology Roadmap and Priorities, The Office of the Chief Technologist, The Cosmic Origins Program and NWNH Decadal.
Radar technology offers a very flexible, powerful tool for applications such as object detection, tracking, and characterization, as well as remote sensing, imaging, sounding, weather measurement and analysis.  Historically, radar systems have tended to be either large, complex, power-hungry, purpose-built systems, or extremely simple systems of limited capability.  More recently, miniaturization of high-performance programmable integrated circuit technologies as embodied in field-programmable gate arrays, as well as rapid advances in high-speed data conversion technologies at a gigasample per second and beyond, have enabled the implementation of direct-conversion radio frequency (RF) systems, including radar, that operate almost completely in the digital domain.  In addition, solid-state high-power RF device technologies have improved in efficiency and speed to the point where highly efficient pulsed transmit sources are possible.  As these device technologies have matured, their application in space environments has accelerated to the point where extremely flexible programmable radar systems can be implemented in a very small size, weight, and power footprint.   Trident Systems has developed a powerful radar architecture called RAPTOR, validating it through flight testing on a number of Department of Defense programs;  initial analysis has shown the feasibility of transitioning this design to the space environment.  Through a comprehensive program of requirements development, trade studies, critical component and design analyses, fault mitigation simulation, and system design, Trident will develop the design for a complete space-qualifiable UHF/L-band radar transceiver in a 96mm x 90mm x 31mm PC-104e form factor that meets all customer mission needs, and is applicable to a wide range of applications (NASA and others).  By basing the solution on Trident's proven RAPTOR technology, the system will rapidly achieve a high TRL.
The Zero G Mass Measurement Device (ZGMMD) will provide the ability to quantify the mass of objects up to 2,000 grams, including live animal specimens in a zero G environment, an innovative because there currently are no such devices available to perform mass measurement of smaller masses (&lt; 2000 grams) in space. At present there are no tools on board the International Space Station (ISS) to measure low mass objects, which is a capability that is extremely important for biological research. The ZGMMD would provide the capability to quantify the mass of an object, while limiting the acceleration applied to the object. The ZGMMD would be capable of being used in the Microgravity Sciences Glovebox (MSG) or could someday be integrated with payloads such as the Plant Habitat (PH). The ZGMMD innovation provides a fundamental capability (measuring mass of an object) that would increase the capabilities of NASA's fundamental space biology program. A significant amount of fundamental biology has occurred on the ground that has utilized mass measurements; therefore to compare zero G results with previously conducted ground experiments, mass measurement capabilities should be provided. Successful completion of Phase I and II efforts would provide these previously mentioned capabilities.
Core noise will become a larger component of engine noise overall, as more efficient design trends of fan and jet noise reduction technologies are implemented. The necessity to keep weight and material costs low, as well as the complex geometry and high temperatures involved with the combustion region, make the production of acoustic liners a difficult task.  CRG will develop and produce a prototype acoustic liner test sample for the combustion region that will address all of these issues.  CRG will use its Sialyte(TM) material and simple manufacturing processes to produce a lightweight, inexpensive liner, that contains inherent high-temperature resistant properties.  Sialyte(TM) is a low-cost material system developed for use in high-temperature and high-pressure applications.  CRG will tailor Sialyte(TM) liner properties to demonstrate fabrication control of Sialyte(TM) open-cell foams or combination with Sialyte(TM) honeycomb. These materials will provide broadband acoustic attenuation in relevant frequency ranges, as well as tailoring material properties for mechanical and thermal performance requirements.  The Sialyte(TM) liner will conform to complex, curved geometries and will withstand the high temperatures and stresses in the combustion region.  CRG will demonstrate performance of TRL 4 in Phase I.
To enable NASA's next-generation missions, there is a critical need for a reconfigurable FPGA that can withstand the wide temperatures ranges and radiation of the space environment while consuming minimal power without compromising on performance.  To address this need, GoofyFoot Labs proposes the E2-AMP FPGA, a radiation hardened, high performance, low power AMP FPGA capable of operating reliably over wide temperature ranges and rapid thermal changes.  The 150-nm E2-AMP FPGA achieves up to 790-MHz peak performance while consuming 7x less power than conventional, commercial counterparts, implementing TMR.  The E2-AMP FPGA provides exceptional protection from SEUs, SETs, SEL, and high TID while maintaining high performance and low power levels that exceed even today's highest performing, commercial FPGAs.  The E2-AMP FPGA's reconfigurability enables last-minute, no-cost design changes and upgrades even after launch, greatly enhancing mission profile while reducing mission cost and risk.  Unlike any other FPGA, rad hard or unhardened, the E2-AMP FPGA can operate reliably at extreme hot and cold temperatures and can also seamlessly tolerate rapid thermal changes without sacrificing performance and without significant designer effort.  To handle extreme temperatures, conventional ICs are protected via onboard heat shields or warm boxes to maintain ambient temperatures to a much smaller range. This equipment increases the SwaP of the system and also degrades system reliability. The E2-AMP FPGA will operate correctly across a large temperature range reducing the amount of required thermal regulation.  Moreover, we will enhance the E2-AMP FPGA's native low power consumption through the incorporation of a number of power savings techniques.  With the E2-AMP FPGA, designers of space-based or high-altitude systems operating in hostile radiation environments and at extreme temperatures can reduce system SWaP, while adding flexibility, capability, and robustness to any system.
For the purposes of advancing integral field spectrograph (IFS) microlens capabilities, a new class of high-quality optics-grade nanostructured organic-inorganic nanocomposite three-dimensional (3D) gradient index (GRIN) microlens optical materials is proposed. In the Phase I program, solid state freeform (SFF) fabrication of high contrast 3D-gradient-index microlens array elements will be demonstrated using a research grade printer. A design of experiment will be conducted to optimize a series of 3D-GRIN films with axial, radial, and vertical gradient optical index patterns with microlenses of varying diameter, pitch, and focal length, including those symmetric and asymmetric. The films will be thoroughly characterized using optical coherent tomography and spectral interferometric techniques, and their power will be tested using collimated and converging light. A series of planar microlens arrays of varying shape, diameter, density, focal length will then be fabricated, and then planar films with two-surface microlens array, including masking, will be fabricated using the measured process parameters (i.e. &amp;#916;n, &amp;#916;n/(&amp;#916;x,y,z), dispersion, etc.)
NASA has recognized the need to develop new on-orbit analysis capabilities.  This need arises because of the high cost associated with returning samples to Earth for analysis, the limited availability of crew time, and the relatively modest capabilities and interfaces of the existing hardware on the International Space Station (ISS).  The goal of this project is the development of a miniature variable-pressure scanning electron microscope (MVP-SEM) that can be rapidly developed, space qualified, and deployed on the ISS.  The MVP-SEM is a cross-cutting tool for in situ topographical imaging and compositional X ray fluorescence mapping of uncoated conductive and non-conductive samples useful to multiple disciplines, including nondestructive imaging of inorganic and organic materials, surface contamination analyses, and scientific studies.  We can achieve our goal by leveraging previous NASA investments in the development of an electron gun control system, an electron focusing column design, and scanning and imaging system technology at NASA Marshall Spaceflight Center; a novel cathode from Applied Physics Technologies Incorporated (APTech); and space-qualified vacuum system technology and electronics from Creare.  With the head start provided by these previous investments, the MVP-SEM technology will provide flight qualified hardware that is similar to commonly used tools in biological and material science laboratories and could allow for an increased capacity of on-orbit analysis.
This Phase I research project will investigate a novel method of operating an atomic magnetometer to simultaneously measure total magnetic fields and vector magnetic fields. Magnetometry has provided critical scientific information throughout the history of space exploration. The ideal magnetic sensor for space applications would be one which shares the advantages of the fluxgate (vector precision, robust operation) with the precision and absolute accuracy of the atomic magnetometer. Our approach will result in an all-optical vector magnetometer (AOVM) that can be calibrated from the fundamental quantum properties of the atoms. Stable calibration is essential if magnetic dynamics are to be inferred by flying different missions to the same planet separated by decades. The sensor and electronics will be small and lightweight and operate from a few Watts of electrical power.
For spacecraft developers who spend millions to billions of dollars per unit and require 3 to 7 years to deploy, the LoadPath reduced-order (RO) modeling thermal design tool is an innovative software tool that will significantly reduce labor costs and effort associated with the design and analysis of spacecraft thermal control systems. Unlike traditional approaches that take weeks to months to develop and obtain results, our approach can provide results in seconds to minutes.

This proposed Phase I effort includes the development of a RO spacecraft thermal model utilizing a combination of a high-resolution thermal model, Latin Hypercube space-filling approaches, and Gaussian Process methods. Combined, these key components have the capability to provide a spacecraft thermal modeling software tool that provides thermal results, on average, within 3K of high-resolution models. In addition to its accuracy, the thermal software tool will be able to provide these results almost instantaneously. The ability to obtain results quickly is especially advantageous during design stages. In addition, it is especially useful for parametric studies. Parametric studies that could easily take days to complete, due to computational expense, can be completed within minutes utilizing the proposed software tool.
This proposal introduces an innovative sensor concept for the mitigation of aircraft hazards due to reduced visibility in fog, drizzle and light rain and the detection of hazards/obstacles on runways. Specifically, this effort will build upon a developing synthetic vision system for landing piloted aircraft to: 1) customize the design and feasibility for targeted unpiloted autonomous systems (UAS), and 2) incorporate interferometry for terrain mapping and hazard detection.

Dubbed "PathIn", the proposed sensor is comprised of a Ka-band digitally beamformed (DBF) radar interferometer that will serve as a complement to existing infrared (IR) and near-IR enhanced visualization systems and provide a real-time data interface for ground-collision avoidance systems.  The proposed effort is aligned with the effort to integrate UAS into the National Airspace (NAS).  The Phase 1 effort will assess the PathIn performance for sample UAS flight scenarios over variable terrain using a high-fidelity point target simulator to provide synthetic digital surface maps and obstacle detections.  This will demonstrate the potential of the PathIn as a technology that can contribute toward safe UAS operation in the NAS and in the terminal area. 
 
In Phase II we will realize a prototype of the PathIn sensor, leveraging our extensive radar, interferometry and DBF experience and key technology capabilities.  In particular a FPGA-based digital receiver system will be extended for real-time beamforming and interferometry. At the end of the Phase I, a technology readiness level of 3 will be achieved.
Over the past decade, research into active combustion control has yielded impressive results in suppressing thermoacoustic instabilities and widening the operational range of gas-turbine combustors.  Active Combustion Instability Control (ACIC) controls the combustion process such that the heat release profile is modulated to dampen the naturally occurring thermoacoustic instabilities. A major challenge to effective implementation of active combustion control is the availability of valves and actuators that provide adequate flow modulation control authority. The majority of the published work revolves around valves designed to modulate the main combustor flow. At present these valves are not designed to operate in a harsh environment and as such are required to be located outside the main flow path, reducing their control authority. To effectively meet the challenge, valves and sensors that are smaller, more responsive and robust must be developed. Ultimately the control valves are co-located with the fuel injection manifold. The trade-off for the harsh environment operation is the ability to maximize the flow modulation control authority. The objective of this research is to integrate the required control authority into an operational environment. This research initiates the development of a light weight fast-acting fuel control valve for harsh environment operation.  The valve will allow the precise time dependent fuel control required for lean-burn combustor operability. In this Phase I research a proof-of-concept valve is designed, fabricated and cold-flow tested using commercially-available driver circuitry to uncover potential performance benefits and demonstrate feasibility of the approach for further development.
Integrate advanced nanotechnology with energy storage technology to develop advanced cathode material for use in Li-ion batteries while maintaining high level of safety, stability and cycle life, allowing the cathodes to be tailored to provide very high specific energy or very high specific power depending on the relative ratio of the three components- active material, current conductors/collectors and binders, thus maximizing specific energy (Wh/kg) and energy density (Wh/l).
Kennedy Space Center (KSC) has the most complex, enormous, difficult, diverse, distributed, and unique set of integrated scheduling problems in the world and it is only getting more difficult as ground resources need to be shared by different organizations. KSC's scheduling problem is decomposed into many individual but coordinated scheduling problems, each with its own unique set of resources, tasks, constraints, ground rules, and scheduling techniques, resulting in different scheduling processes for each of the individual applications. Stottler Henke's existing Aurora intelligent planning and scheduling system development framework was specifically designed for KSC ground operations scheduling and to be highly adaptable to different domains and has already proven to be adaptable by its successful applications in many dozens of widely varying domains (including multiple KSC scheduling domains). In every domain where a comparison was performed, Aurora always generated more optimal schedules.  
The proposed vision is to develop one scheduling tool that SMEs in wildly different KSC areas can adapt to create automated scheduling software for different scheduling applications. New capabilities need to be added to address the new KSC realities and to make the adaptation process more SME-friendly. Initially the Intelligent Operations Scheduling System (IOSS) would be fielded in a small number of vehicle and payload processing applications.  Later SMEs could adapt IOSS themselves. Eventually, IOSS-based automatic scheduling systems might constitute the majority of schedule decision making at KSC. These separate IOSS scheduling applications could automatically interact, providing automated coordination capabilities. These applications will also be able to interoperate with legacy scheduling systems. Ultimately, by automating, replacing, or interfacing to every scheduling function or system, extreme synergies of coordination and manpower savings would result.
The development of rocket-based and turbine-based combined cycle engines are a high priority for transportation into space.  In order to test components and systems, and certify life cycles for these  engines, non-intrusive flow diagnostics are required.  In particular, high-speed measurements of pressure, velocity, and temperature profiles across both inlet and outlet ducts of these engines would  provide a better understanding of engine performance.

Southwest Sciences, Inc. proposes to develop a high-speed, non-intrusive monitor to measure such flows.  This fiber optic sensor is based on a novel approach derived from wavelength modulation spectroscopy, in which high bandwidth measurements can be acquired and processed with simple electronics.  Phase I will focus on validating the proposed technique and in Phase II, a fully operational prototype will be constructed, tested and delivered to NASA.
Current NASA programs, such as Adaptable, Deployable Entry and Placement Technology (ADEPT) and Woven Thermal Protection Systems (WTPS) are looking to fill a gap in ablative TPS for future missions to Venus and Saturn, human missions beyond Lunar, and Mars Sample Return Missions.  Both of these programs rely on the use of 3D woven carbon fiber preforms.  Therefore, there is a need to be able to predict the properties and performance of a woven material.  Validation of predictive modeling tools would allow for the use of these tools to design and optimize the 3D weaves, significantly reducing the cost of fabrication and testing of a variety of configurations. While there are proven tools for the prediction of laminate composite properties, textile composites are relatively new materials and much less effort has been focused on modeling this class of materials. Materials Research &amp; Design (MR&amp;D) has experience in working with and designing 3D woven preforms for use in composite material reinforcement and has developed a suite of analytical tools to define the detailed geometry of 3D woven preforms for use in calculating material properties.  However, these tools currently do not have the capability to predict material strengths.  Within the proposed Phase I effort, MR&amp;D will enhance the existing tool by incorporating the ability to calculate material strengths of 3D weaves.  Strength predictions will be made for two different 3D woven hybrid preform reinforced phenolic panels and compared to measured test data for validation.
The unique built-in design features of the proposed mini pulse tube cryocooler avoid all thermal expansion issues enabling it to operate within a cold, 150 K environment.  As such, the cooler addresses the need to prevent boiloff of cryogenic propellants on long duration remote missions.

Due to its high heat capacity regenerator matrix, the cooler has a high efficiency and a small footprint, making its launch mass minimal.  The coherent regenerator matrix configuration prevents movement and so prevents degradation over time.  Due to its unique compressor being cold-tolerant down to 150 K the cooler can keep running even where the sun is so far away and dim that the energy captured by the spacecraft cannot keep the compressor warm.  The compressor being designed to run cold and on minimal input power allows it to run at the inherently low solar intensity, which seriously depresses solar cell power generation.

In all, our cryocooler innovation is an enabling technology for far-flung missions that have the need to preserve mission propellants in their liquefied state until needed to maneuver near a destination or a midway point.

The design concept calls for: 1) Using regenerator materials from a recently developed class of high heat capacity rare earth alloys;  2) A compressor and coldhead design optimized for a low temperature heat sink;  3) Minimizing the known losses in the pulse tube proper.  The cryocooler design will be possible due to the long standing cryocooler design and manufacture heritage of the team members.

Phase I will verify the low temperature capabilities down to 150 K of an available mini compressor, and, will put forth the design of the crucial components of a complete 0.3 W at 35 K cryocooler targeted to run in a 150 K environment.

Phase II will build and test a complete prototype cryocooler that is small in size and power consumption enabling long durations missions to planetary objects at remote locations within the solar system.
Cryogenic propellants are important to NASA's missions. Improvements in cryogenic propellant storage and transfer are critical to future long duration NASA spacecraft and missions. Advanced Cooled Shield - IMLI (ACS-IMLI) is an innovative ultra high performance system in which an Advanced Cooled Shield is fully integrated into the IMLI layer structure, reducing mass, forming a single robust system, with integrated cooled gas distribution in a cooled shield layer, eliminating heat flux through thermal shield tank standoffs or supports, and operable in both passive (vapor cooled shield) and active (broad area cooled shield) modes.

NASA's TA-02 Roadmap calls "Zero Boil Off storage of cryogenic propellants for long duration missions" the #2 ranked technical challenge for NASA mission objectives and needs.  Quest Thermal Group has developed IMLI, an advanced thermal insulation that uses proprietary discrete spacer technology to reduce heat flux. IMLI's unique structure is able to self support various loads, including a thin, lightweight vacuum shell for in-air operation, high strength ballistic layers for MMOD shielding, an external Broad Area Cooling Shield with cooling tubing, or an integrated thermal shield within the layers. IMLI's layer structure gives it unique capabilities, such as an embedded conductive, sealed thermal barrier. 

In this Phase I program, an ACS-IMLI system would be modeled, analyzed, designed, fabricated, installed on a cryotank, and tested for structural strength and thermal performance.  Advanced Cooled Shield &amp;#150; IMLI (ACS-IMLI) could provide a lower mass, single insulation system, operable in both passive (vapor cooled) and active (cryocooled) modes, with 3 &amp;#150; 4X lower heat flux than IMLI alone. ACS-IMLI could help meet NASA's cryogenic fluid management requirements such as Zero Boil Off for cryogenic propellant storage and transfer.
We propose to build an electrostatically focused klystron that exploits recent breakthroughs in scandate cathode technology.  We have built cathodes with greater than 100 Amps/cm2 emission.  This project offers an opportunity to test those cathodes in real world devices.  Because of their small size (.050 inch diameter) and low power dissipation (under 1.2 watts), they are ideal for long-range space missions.  Also, their low beam convergence makes electrostatic focusing feasible.  This, in turn, provides a dramatic reduction in amplifier size and mass.  Without magnets, traveling wave tubes and klystrons will be lighter and smaller, a further enhancement for space missions.  Phase I develops cathodes, pierce guns and focusing stacks.  Phase II will see construction of a working klystron or TWT.  Scandate cathodes also provide longer life than conventional cathodes.  Their small size allows amplifiers to reach much higher frequencies, bandwidth, and data rates than current art.
The availability of low AC loss magnesium diboride (MgB2) superconducting wires enables much lighter weight superconducting stator coils than with any other metal or ceramic superconductor. This, together with Hyper Tech's capability to fabricate long piece-length (potentially 60 km) wires, in turn enables lighter superconducting motors/generators, essential components in the turboelectric aircraft propulsion system envisioned in next generation Air Vehicle Technologies. To that end, this proposed SBIR Phase I program focuses on developing MgB2 multifilament wires with the smallest practical filament size achievable (10 ??m or less) as a means to reducing AC losses due to hysteresis, eddy current, and coupling losses. Two recent advancements at Hyper Tech greatly increase the odds of success: 1) The emergence of a novel MgB2 wire manufacturing method that incorporates a magnesium-infiltration process (precursor materials are magnesium wire and powder boron) that has produced a 10-fold enhancement in critical current density over that of present state-of-the-art wires made by the conventional method involving magnesium-boron powder mixtures, and 2) Improved capability in wire drawing to fabricate fine multifilament strands.
The capacity of coherent LIDAR systems to produce a continuous, real-time, 3D scan of wind velocities via detection of backscatter of atmospheric aerosols in clear-air conditions gives this technology a clear advantage over other atmospheric monitoring technologies. LIDAR has proven its value in a number of applications, including the detection of clear-air turbulence, wind shear, and aircraft wake vortices.
Of particular interest under this NASA sub-topic is the development of an airborne Lidar system capable of detecting and measuring aircraft wake vortices and turbulence out ahead of the aircraft in order to improve aviation safety. To perform this task well a Lidar must have certain characteristics and be paired with a highly optimized wake and turbulence processing algorithm. The key development area for detection of turbulence at cruising altitude is Lidar transmit energy and pulsewidth. High energy output on the order of 1.0 mJ for low flying manned or unmanned aircraft (10,000 ft) and 10 mJ for commercial aircraft (30,000 ft) is required. Aerosol density decreases rapidly as a function of altitude and the backscatter coefficient at 30,000 ft is only 4x10-10 as opposed to 2x10-7 at sea-level. Furthermore, commercial airliner crews will need at least 30 seconds reaction time after turbulence is detected in order to take action, requiring the Lidar system to see 6.67 km ahead (assuming an average flight speed of 500 mph). 
Other key requirements of an airborne Lidar system involve the size and power consumption of the system.  The limited space and available electrical power on an aircraft necessitate that a Lidar system be compact and efficient.  In addition, the system must be able to be integrated onto the aircraft without inhibiting other flight systems.
SIBELLOPTICS proposes a Phase 1 SBIR to develop and test an Er-doped polarization maintaining (PM), large mode area (LMA) fiber amplifier to boost transmitted Lidar power to greater than 1 mJ per pulse.
The overall technical objective of the proposed Phase II NASA program is to demonstrate the ability of the WaMM&amp;#153;-based static vapor feed electrolyzer to generate enough low moisture content oxygen to support the life of 5 astronauts (9.0 lbs/day).  To achieve this, the stack must be designed for risk mitigation and operation in the simplified Giner system.  Stack size must also increase five fold in comparison to the fifteen cell stack designed, assembled, and operated in the Phase I program.  In addition GES will provide a prototype system to our Subcontractor for external testing and preparation for building a test flight article.
Fault Management (FM) is one of the key components of system autonomy.  In order to guarantee FM effectiveness and control the cost, tools are required to automate fault-tree generation and updates based on design models specified in standardized design languages such as AADL.  Accordingly, we propose a fault tree generation and augmentation environment (FTGA).  Equipped by a fault class model and an FM method catalog, FTGA evaluates not only failure behavior in the application under analysis but also FM's capability and adequacy for failure mitigation.  Moreover, when an inadequacy in FM is revealed during fault tree generation or analysis, the fault tree will be allowed for augmentation through FM method insertion and be followed by a quantitative evaluation for FM effectiveness validation.  Therefore, unlike traditional fault tree analysis which plays a passive role in FM, the automated FTGA environment actively and explicitly influence system design and updates, enabling "fault-tree-in-the-loop" for a system's life cycle.  Further, by separating its generic functions (which we collectively call "shared package") from design-language-specific functions (which we collectively call "interface package"), FTGA will be an extensible modeling environment.  The anticipated results from the Phase I project will be a preliminary prototype of FTGA and a demonstration for concept validation.
Optical communication links provide higher data transfer rates with lower mass, power, and volume than conventional radio-frequency links. For deep space applications at long operational ranges, high performance stabilization of the space terminal data link is required. To meet this need, CDI proposes a novel application of our free-floating isolation platform. Based upon a Shuttle-proven technology, this approach yields 6-DOF isolation from the disturbances of the host vehicle while providing high-bandwidth active stabilization to attenuate both payload disturbances as well as any residual disturbances transferred from the base across the power/data umbilical. The proposed approach is designed to achieve better than 0.5microradian-rms stabilization for all frequencies above 0.1Hz when operating in a space environment.

Phase I develops the proposed design concept, performs architecture trade studies, and predicts performance to establish the feasibility of the approach. Using an available free-floating isolation platform and a 2-axis low-g testbed, the design concept is prototyped and demonstrated on hardware in a simulated low-g environment (TRL-5).

Phase II proceeds with the development of a prototype system that will be space qualified through comprehensive ground testing (TRL-6). Technology demonstration flight tests will be proposed on sRLVs and/or ISS platforms (e.g., WORF, OPALS upgrade), achieving a TRL-7 maturity by the end of Phase II.
To address the NASA need for an EVA information display device, Physical Optics Corporation (POC) proposes to develop a new Projection/Reflection Heads-up Display (Pro/Ref-HUD) based on innovative integration of laser projectors and optics. This approach incorporates miniature full-color laser light sources and low-profile narrowband reflective, see-through toroid-shaped optics, which enable us to meet NASA EVA requirements for displays that are completely decoupled from the user's head and achieving full sunlight readability with automated rapid ambient light response. The Pro/Ref-HUD offers full-color, high-resolution collimated images, with large fields of view, highly suited to the space and weight constraints inside an astronaut's suit. POC plans to demonstrate the feasibility of the Pro/Ref-HUD system by building and testing a preliminary prototype to TRL-4 by the end of Phase I. POC plans to develop in Phase II a fully functional prototype to demonstrate sunlight readability and SXGA  resolution, investigate thermal and radiation issues, and analyze ignition safety due to a 100&#37; oxygen operating environment and vacuum and extreme temperature storage environments. The results demonstrated will offer NASA capabilities to perform EVAs with heads-up displays internal to the helmet to improve crew safety and comfort and prevent misalignment of the display.
This proposal describes development of a new type of quantum-cascade laser for use as a local oscillator at frequencies above 2 THz.  The THz source described is a single chip solution that operates at room temperature.  In addition, a mechanism for wide tuning (2-4.7 THz) is described that requires no moving parts.
Propellant densification systems for LH2 require compression systems that develop significant head.  In the past this has required multiple stages of compressors running at high speed on grease-packed ball bearings with very limited life, large heat leak and questionable rotordynamic stability.  This project will utilize foil bearings with an innovative feature that will greatly increase bearing life/rotordynamic stability, drastically reduce number of stages and cost while increasing efficiency.
An all electric aircraft test bed is proposed to provide a dedicated development environment for the rigorous study and advancement of electrically powered aircraft.  The new test bed aircraft will be developed from an existing conventional airframe and provide a dedicated platform to study, design, and test electrically powered propulsion systems for use in commercial, military, and general aviation vehicles and UAV systems.  The test bed aircraft will allow various electrical propulsion system technologies to be tested to determine performance, reliability, safety, and cost.  These include various motors, motor controllers, batteries, fuel cells, super capacitors, and propeller technologies.  Additionally, the platform could be used to investigate performance characteristics unique to electric propulsion, determine the most accurate methods for measuring energy used and remaining, research redundancy possibilities unique to electric aircraft, and possible hybrid-electric power plant systems.  An electric aircraft has several significant advantages over a conventional internal combustion driven aircraft.  These include zero, or near zero emissions, increased reliability and safety with only one moving part, reduced noise and vibration, increased comfort, and reduced maintenance.  RHRC and the University of Illinois propose to develop an all electric test bed aircraft able to systematically evaluate new and existing technologies, which will make these systems, safe, reliable, and cost effective.
An Advanced Microgravity Compatible, Integrated laundry System (AMCILS) is proposed that uses a two phase water / water vapor system to allow good agitation of clothing during the wash &amp; rinse cycle.  Drying will be accomplished utilizing microwave energy addition and "jet" air flow to fluff and move clothing in the washing chamber.  Operation in a two phase water / water vapor system precludes the formation of sustainable foam in the wash effluent while allowing adequate volume for agitation of clothing in a weightless environment while using a minimum amount of water.  Drying using air "jets" and microwave addition was proven during micro-gravity testing performed in the Single Phase Space Laundry Phase II program (NASA contract No. NAS9-18362, Jan. 1993) The Phase II effort will build upon the successful Phase I feasibility demonstration of the AMCIL concept and result in delivery of a working AMCIL prototype whose performance will be thoroughly characterized and delivered to NASA for independent testing.  
	The AMCIL promises a reduction in ESM associated with crew clothing on long duration missions through the reduction of expendables.  Clothing can be re-used which minimizes ESM associated with storage of new clothing, and waste storage associated with used clothing.
Future manned spacecraft and lunar or Mars outposts will need a condensing heat exchanger (CHX) to control humidity in the cabin atmosphere.  Condensing surfaces must be hydrophilic to control the condensate flow and ensure efficient operation, and biocidal to prevent growth of microbes and formation of biofilms on condensing surfaces.  Coatings must be extremely stable, adhere to the condensing surface, and maintain hydrophilic and biocidal properties for many years.  We propose to develop a zeolite coating system that incorporates two key innovations: (1) modifications to the coating chemistry to enable much longer life than prior coatings, and (2) an in situ cleaning process that can decontaminate the surface and renew hydrophilic properties.  In Phase I we will prove the feasibility of our approach by developing preliminary cleaning formulations, developing chemical analysis models to predict coating lifetime, producing trial coatings, and demonstrating coating performance and the effects of cleaning.  In Phase II we will scale up and refine the coating process, produce sample coupons and heat exchanger cores, and measure the coating performance after long-term exposure to prototypical environments.  We will also develop and demonstrate a coating regeneration process and associated hardware suitable for ground testing and eventual demonstration on the International Space Station (ISS).
Proposed is the development of a manufacturing technology that will increase feasible large optics design options and significantly reduce the manufacturing time, cost and risk involved in manufacturing large optic components.  Specifically addressed are cutting and light weighting of glass and ceramic optical components. 
While milling and cutting materials such as ULE or SiC is often performed at Ormond using a novel technology, there is a need to develop this technology to a point where the risk of machining large optics made from these materials is acceptably low and NASA and its contractors understand the technical and cost performance.  Development is needed to address engineering requirements of large optics and to advance production readiness.
In Phase I, proprietary glass and ceramic cutting and milling technologies will be adapted to space optics requirements through software, process and tool development.  Performance data will be immediately available to support ongoing NASA programs and to set the groundwork for Phase II.  Key risk reduction methods will be identified.
The Phase I workscope will involve NASA primes to demonstrate and prove the feasibility of implementing the proposed technology in large optics manufacturing.  Phase II will result in a commercial ready means of cutting and milling large optics.
NanoSonic has developed a candidate state-of-the-art inflatable as a novel bladder material for life critical, space habitats that maintains low air permeability (&lt; 0.0017 cc/100in2/day/atm) upon the triple fold cold flex test conducted at -50 ?C.  The multifunctional Thoraeus Rubber&amp;#153; (TR) films are comprised of a low glass transition temperature (Tg), - 100 ?C, copolymer matrix resin modified with alternating layers of ultra-thin, uniform layers of proprietary nanoparticles for radiation resistance.  NanoSonic's unique molecular level deposition technique yields pinhole-free nanocomposites with that maintain radiation and EMI shielding (up to -100 dB) upon severe (50 &#37; elongation) and repeated mechanical strain, a property that few if any inflatable exhibit.  NanoSonic proposes to produce a triply redundant bladder assembly comprised of several layers of TR&amp;#153; films bonded with our low areal density self-healing foam, for a total areal density of less than 6 oz/yd2.  To substantiate long-term use in space, the down-selected, puncture resistant assemblies shall be exposed to gamma, electron, and heavy ions at the NASA Space Radiation Laboratory (NSRL) at Brookhaven National Laboratory via our partner, Colorado State University (CSU).  Low air permeability and flammability resistance would be verified after simulated Galactic Cosmic Radiation (GCR) exposure and cryogenic flex testing.  NanoSonic has teamed with seaming and space systems experts who will conduct leak and adhesion testing, and assist with habitat construction.  In support of NASA's goals for a robust space exploration program, it is anticipated that NanoSonic's lightweight, low permeable bladders shall enable space inflatable modules that exhibit long-term, 5 year, radiation resistance upon inflation, minimize launch mass, repair/maintenance, size and costs.
Advanced x-ray observatories such as IXO and GenX will require thousands of thin shell mirror segments produced by replication using convex mandrels. Quality and cost effective manufacturing of these segments is proportional to the speed and effectiveness of the metrology we use in manufacturing and the ability to use accurate measurements to enable deterministic fabrication. AOS proposes development of an efficient and accurate metrology system to enable the manufacturing of sements with performance of 0.5 arc-second or better. A curent  method to test such mandrels is to stitch multiple meridional profiles acquired using a large aperture plano interferometer and an air-bearing actuated partholder. AOS will advance this method, by building an automated platform, driven by custom developed software, and implementing improvements that will enhance both the accuracy and efficiency of the test.
Optical Air Data Systems (OADS) L.L.C. proposes a LIDAR based remote measurement sensor suite capable of satisfying a significant number of the desired sensing requirements in a compact, lightweight, and extremely power efficient form factor.  OADS all-fiber optic LIDAR and Laser Doppler Velocimetry (LDV) technology is capable of measuring precise height above ground, ground speed, ground drift, range-gated relative winds, ambient temperature, as well as ambient pressure through the entire entry and descent phase of the spacecraft.  Unlike other LIDAR solutions that would require imaging around or through the aeroshell, OADS patented LDV solutions can directly measure a range map of the terrain while simultaneously providing surface relative velocity information for navigation near the ground.   OAD LDV solutions include a remote wind sensor capable of measuring wind information at multiple distances ahead of the spacecraft during the entry and descent phases.  Once descent is complete, the sensor can be used on the ground to collect local environmental data (including surface winds) as advance information for the fetch rover, the planetary ascent vehicle, and for future missions.
Mass and volume efficient solar arrays are sought by NASA, DoD and commercial space to enable high power missions from 20-30 kW up to 300 kW. Flexible substrate arrays can have higher specific power (W/kg) and specific volume (kW/m3) than conventional arrays. Typical designs for flexible substrate arrays require a stiff boom mechanism to deploy the array and provide the deployed structure.  Graphite composite slit-tube booms are thermally stable and can enable next-generation flexible arrays by improving mass, volume, and cost. CTD has developed and demonstrated a 5cm diameter graphite composite slit-tube boom and canister designed for a 23m tether-stiffened solar array. The Stable Tubular Extendible Lock-Out Composite (STELOC) boom proposed here will feature two innovations to the composite slit-tube design that enhance stiffness. Slit-Lock interlocks the edges of the slit and Root-Lock eliminates the open section at the root of the boom when fully deployed. Combined, these innovations enable a 10cm STELOC boom that is much simpler, lighter, and stiffer than a 25cm diameter coilable longeron boom. This Phase I program will demonstrate a full length, 10cm STELOC boom including all innovative features to enhance stiffness. The program will also develop a conceptual design that meets all boom requirements provided by an identified spacecraft prime contractor for their flexible substrate array.
The rotation sensitivity of a conventional optical Inertial Navigation System (INS)depends on the area enclosed by a circular optical path.  Hence, it is impossible to significantly reduce the device size without sacrificing its sensitivity.  Recent work showed that certain non-linear optical effects (fast light) can be used to increase the sensitivity of a ring laser gyro of a given size by orders of magnitude.  We propose a portable high-performance all-fiber laser gyroscope.  The device will utilize fast light produced by the Stimulated Brillouin Scattering in single-mode fibers.  Fast light enhancement will enable reduction of the device size without decreasing its performance level.  The fast light enhanced gyroscope will empower a rugged, compact, low-cost high-sensitivity INS ideal for precision guiding of UAVs, and other aircrafts.
Optimal Synthesis Inc.(OSI) proposes to develop an aiding tool for user interface design that is based on mathematical formalism of hybrid system theory. The correctness of information content of a user interface is ensured by a special observability test that takes into account of human cognition and psychology. A possible mismatch between an operational mode perceived by a human operator and the one active in a machine is detected via an algorithm that infers the intent of the human operator and generates an alert if a discrepancy from the mode of the machine is found. The developed tool is evaluated by considering standard operations in the national air space in the absence and the presence of a system fault.
Renewed interest in missions to explore other planets has created a need for higher performance thermal protection systems (TPS) capable of shielding spacecraft from the severe heating encountered during hypersonic flight through planetary atmospheres.  Additional advances in the robustness, reliability, and survivability of single and dual heating exposures are desired while maintaining mass and thickness requirements. The ability to decelerate high-mass entry vehicles relies on flexible or deployable aeroshells which offer an approach for achieving larger aeroshell surface areas than otherwise attainable.    A flexible TPS is required that is capable of surviving reasonably high heat flux and durable enough to survive the rigors of construction, handling, and deployment.  Aspen Aerogels proposes to develop improved flexible ablative reinforced polymeric aerogels to meet this challenge.  During Phase I we will optimize the preparation methods to reduce thermal conductivity and increase flexibility and conduct a complete study of the aerogels' properties and capabilities.  The technology readiness level will progress from 2 to 3 during Phase 1.  Successful completion of a Phase II program will result in an optimized and scalable formulation for the aerogel component of flexible TPS and performance data which will be available for further commercialization efforts for the aerospace industry.
The Nitrous Oxide Ethane-Ethylene (NEE) engine is a proposed technology designed to provide spacecraft with non-toxic non-cryogenic high-performance propulsion.  With the NEE engine, nitrous oxide is used as an autogenously pressurizing oxidizer, and a mixture of ethane and ethylene is used in the same manner as fuel.  Initially, the ethane and ethylene mixture have the same vapor pressure as the nitrous oxide.   By utilizing the autogenous pressurization capabilities of these propellants instead of an additional pressurization system greater system simplicity and reliability can be attained.  Achievable specific impulse with pure N2O is about 315 s, which can be raised above 325 s by dissolving some O2 in the N2O.  Catalytic ignition can be achieved by using a ruthenium reactor to exothermically dissociate N2O. Since both propellants can exist as a liquid in the same temperature range, no thermal separation is required, and the two propellants can be stored together in compact common bulkhead tanks, and freezing is not an issue down to -90C. Pioneer Astronautics has demonstrated monopropellant nitrous oxide thrusters with a specific impulse of 190 s.  Using such nitrous oxide monopropellant engines for low thrust RCS together with the NEE for ??V and larger thrust reaction control propulsion, it will be possible to build spacecraft propulsion systems that are completely storable and non-toxic, with only two propellant fluids required. In the proposed program, we will demonstrate a NEE engine.
NASA has proposed several missions to land a craft on an asteroid and potentially to return samples from it.  While large asteroids in the asteroid belt can exhibit a significant amount of gravity, most near-earth asteroids are small and show a surface gravity of less than 0.1&#37; of earth.  Landing, and staying on the surface of such a small object is a challenge, especially for manned missions.  Just the movement of an astronaut in and out of the lander during excursions would most likely dislodge the vehicle.  Similarly, drilling for a sample return mission requires the ability to exert force onto the surface without pushing the lander off the surface.  A solid anchoring system is required, but made difficult due to the potentially rubble-like consistency of small asteroids, which makes classic mechanical anchoring difficult.
Adherent Technologies, Inc. (ATI) has developed innovative materials for space use for over a decade.  These include inflatable structures, self-sealing membranes, coatings for satellites and solar sails, and vacuum-deployable foams.  The proposed program will combine these technologies to produce an anchoring system that deploys either a sticky screen that can attach to a solid rock formation or a foam injection anchor that can bind a large amount of rubble as an anchoring point.  The system is modular, and a decision which anchoring method to use only needs to be made on location.
Roccor, LLC, propose the development of a highly novel and structurally efficient outrigger strut design feature that efficiently integrates with a large deployable starshade or, occulter, currently under development by NASA-JPL.  The starshade acts as an external occulter to suppress the incoming starlight sufficiently for detecting and characterizing exoplanets.  Key to the performance of the occulter is achieving sufficiently high out-of-plane stiffness to withstand maneuvering loads as well as meet the shape-tolerance requirement.  Roccor's proposed effort utilizes a highly novel deployable outrigger system that seamlessly integrates into the current deployable occulter design.  Further, Roccor's approach leverages our considerable background in elastically stowed and deployed composite structures.
We propose a comprehensive and systematic contingency plan generation framework to deal with lost communication in UAVs. ATC regulations are explicitly incorporated into our system. Our proposed framework was motivated by our recent work for the Naval Air Station at Patuxent River. In should be noted that our earlier framework was very general, as we have designed a system which can deal with many types of pop-up threats such as enemy attacks, internal system faults, external interferences, etc. Currently, we have been focusing on generating contingency plans for engine out problems for the Navy. In this NASA Phase 1, we will focus on generating contingency plans for lost communication. Our proposed approach has one key component known as Risk Management Plan (RMP), which assesses mission risk of a given air task order (ATO) and provides solutions for known or unknown threats throughout the course of the mission. Four sub-plans are used to support RMP:  Situation Analysis (SA), Preparedness &amp; Prevention Plan (PPP), Incident Response Plan (IRP), and Rescue &amp; Recovery Plan (RRP).  We propose to apply case based reasoning (CBR) in two modules (PPP and IRP) to generate contingency flight paths, contingency points, safe points, and incident response rules. In CBR, we can easily incorporate ATC regulations, which can be formulated as used cases in the CBR.
Thorleaf Research, Inc. proposes to develop a miniaturized in situ atmospheric probe sampling inlet system for measuring chemical and isotopic composition of the atmospheres of the giant planets, with special emphasis on NASA needs for missions to Uranus and Saturn. Our innovative design will provide a constant flow rate of sample to the inlet of a mass spectrometer (MS) in spite of more than a hundred-fold variation in external atmospheric pressure, allowing the detection sensitivity of the MS to be optimized over the full descent profile of the atmospheric probe, unlike previous sampling systems that depended on fixed leaks. This addresses a key technology gap for planetary studies, mainly how to acquire and prepare samples for in situ analysis while meeting challenging mass, volume and power constraints. Based on our analysis, we project a system mass on the order of 0.5 kg and an average power consumption of &lt;0.5 watt, depending on materials and the configuration selected. The goal of our proposed SBIR Phase I effort is to demonstrate feasibility for a miniaturized in situ atmospheric probe sampling inlet system for Uranus and Saturn, and to develop a detailed design for fabricating prototype instrumentation in Phase II.
In situ production of methane as propellant and oxygen as life support consumables from the atmospheric CO2 and water on Mars is a key enabling technology required for sustainable and affordable human exploration of Mars. Sabatier reaction for catalytic methanation of CO2 with H2 is a commercially well known process achieving conversions in excess of 99&#37; at temperature of ~350?C. However, application of this technology for Mars missions requires significant improvements in terms of mass and durability of the Sabatier reactor. Conventional catalytic approaches are insufficient to address the catalyst durability issues and its tolerance to impurities such as H2S and halogenated compounds, which may be present in small quantities in Martian CO2. Lynntech proposes a novel low power, low temperature, impurity tolerant non thermal plasma assisted catalysis for the methanation of CO2. Lynntech will develop a multi-channel reactor design based on parametric study in Phase I. The Phase II of the project will build a full scale Sabatier reactor for NASA application.
Invocon has devised a method to determine the location of lightning 
strikes on structures to as close as 1" by combining simple sensors 
with highly capable electronics.  This method measures a strike from
multiple transducers to triangulate its location.  Initial testing on metallic and composite structures has provided good results.  The next step is to extend the wireless nature of the system to the transducers in order to simplify installation and use of the system.

The proposed development is based on nearly 10 years of successfully development and flight testing of high-speed impact detection and evaluation systems combined with lightning detection and location research. It will also take advantage of Invocon's successful 20 year history of deploying highly synchronized wireless networks on aerospace vehicles.
The Space Micro-Arizona State University (ASU) team will develop an all-digitally controlled, wide temperature range point-of-load switch-mode DC-DC regulator core with built-in self-test (BIST) functionality which meets space radiation requirements. In Phase II we will complete a design and fabricate into silicon at Tower-Jazz foundry and demonstrate the electrical, thermal, and radiation performance to meet NASA mission needs.  This R&amp;D translates into substantial benefits to NASA in extreme temperature (and radiation) environments.
NASA/JPL thermopile detector linear arrays, wire bonded to Black Forest Engineering (BFE) CMOS readout integrated circuits (ROICs), have been utilized in NASA missions such as the Mars Climate Sounder and the Diviner Lunar Radiometer Experiment. Linear array thermopile detectors are fabricated by bulk micro-machining. Surface micro-machined thermopiles are desirable for area array thermopiles because the architecture provides both high detector fill factor and circuit fill factor in the pixel. The Phase I effort designs an area array ROIC compatible with surface micro-machined thermopile detectors to meet requirements of future NASA thermal instruments requiring D-Star &gt; 4 x 109 Jones. Radiation hard-by-design will be utilized with 180 nm CMOS for low 1/f noise readout, operating temp 77-300 K, radiation hardness and noise immunity with on-ROIC ADC. Various pixel pitches and binning methods will be investigated to cover a desired wavelength detection range of 20 ?m &amp;#150; 100 &amp;#956;m. The Phase I ROIC array design, in a 128x128 or larger format, will be fabricated on Phase II.
The NASA objective of expanding the human experience into the far reaches of space requires the development of regenerable life support systems.  This proposal addresses the development of an integrated air-revitalization system for the space suit used in Extravehicular Activities (EVAs).  The proposed innovations are: (1) a single CO2, H2O, and trace-contaminant management unit; (2) a single sorbent possessing the capability to remove CO2, H2O, and trace contaminants; (3) monolithic sorption unit to provide the following functions: (a) CO2 sorbent; (b) H2O sorbent; (c) trace-contaminants sorbent; (d) low pressure drop; (e) good thermal management (heat transfer and low heat of adsorption); (f) resistance to dusty environments; and (4) regenerable operation.  The overall objective is to develop a CO2/H2O/trace-contaminant removal system that is regenerable and that possesses weight, size, and power-requirement advantages over the current state of the art. The Phase 1 objectives are: (1) to demonstrate the technical feasibility of using a novel CO2 sorbent; and (2) to demonstrate effective CO2, H2O, and ammonia sorption and regeneration.  This will be accomplished in three tasks: (1) Sorbent Preparation and Characterization;  (2) Sorbent Testing; and (3) Product Assessment.
With the increasing demands placed on extravehicular activities (EVA) for International Space Station (ISS) maintenance, there is a critical need for oxygen delivery for EVA's from on-station sources.  Since mechanical compressors have significant lifetime issues, NASA is evaluating high pressure PEM electrolyzer technology to generate and compress oxygen on the ISS.  State-of-the-art electrolyzers use Nafion&amp;#174; and similar perfluorosulfonic acid membranes which have significant hydrogen (H2) permeation issues.  To achieve the efficiencies desired, NASA requires a 50&#37; or more reduction in H2 permeation with less than 10&#37; reduction in ionic conductivity.  Lynntech proposes to manufacture nanocomposite membranes with significantly reduced H2 permeation while maintaining high ionic conductivity.  Preliminary results showed an unprecedented reduction in H2 permeation with minimal reduction in ionic conductivity (which have not been demonstrated before), no acid generation, and increased water transfer capability.  In Phase I, Lynntech will further optimize the membrane microstructure to achieve a target 60 to 70&#37; reduction in H2 permeation with less than 10&#37; reduction in ionic conductivity.  The anticipated Technology Readiness Level at the beginning and ending of Phase II will be 3 and 4, respectively.
The proposed SBIR project will provide a pathway to dramatically reduce the cost of multi-junction solar cells.  The project leverages a TRL6 micropackaging process with ~100&#37; yield for cell assembly.  Cost savings are critical as space-qualified multi-junction cells render large panel applications prohibitive.  The proposed project aims to develop a greatly-simplified manufacturing process that can be performed by most compound semiconductor foundries.  Thus, cost savings can be derived from increased competition and scaling by leveraging low-cost high volume manufacturers for wireless components and LED lighting devices.  

The preliminary 3-subcell systems has &gt;30&#37; efficiency at 60C-100C. For higher efficiency, a 5-subcell system has &gt;57&#37; efficiency.  

For CPV applications, LCOE of the 3-subcell system at 630 suns is 20.96 cents/kWh (real)/27.20 cents/kWh (nominal).
Sierra Lobo proposes to develop a technology that can provide both cooling and electric power generation using heat.  When coupled with a radioisotope heat source, the technology is ideally suited to the needs of a long-lived Venus lander.  The heat source powers Sierra Lobo's Thermoacoustic Stirling Heat Engine (TASHE), which is directly coupled to a Pulse Tube Refrigerator (PTR) in a duplex configuration.  A linear alternator, also directly coupled, generates electricity.  This configuration reduces the number of energy conversion processes and thus maximizes efficiency.  The PTR cools a space called the coldbay that houses the linear alternator and scientific instruments.  The only moving parts in the system are free pistons that tune the resonant frequency, which operate at Venus-ambient temperature, and the linear alternators that operate near Earth-ambient temperature.
The system can potentially be used with the gas from the atmosphere of Venus, which is primarily composed of CO2, as a working fluid.  This provides two key advantages:  (1) The system can make the transit to Venus in a low-pressure state, which significantly decreases system mass, and (2) the effect of leakage during operation is minimized, providing confidence in long mission lifetime.
Advanced lithium-ion (Li-ion) batteries are currently under development for Extravehicular Activity Suits, Altair Lunar Landers, and Lunar Mobility Systems.  However, low voltage operation and low capacity cathode of current Li-ion batteries limits both volumetric and gravimetric energy density. High capacity cathode materials with high voltage operation are needed to offer the required gains at the integrated cell level to meet NASA's goal. Lynntech proposes to develop advanced cathode that can work at high potential and provide high capacity, long cycle life, and high rate capability. During Phase I project, Lynntech will synthesize the cathode materials, optimize the compositions and structures, evaluate the cathode's properties, and determine the performance of cathodes in half cell and full cell containing high voltage electrolyte and silicon-carbon composite anode. The technology is currently estimated at TRL 3 and is expected to result in TRL 4 at the end of the Phase II project. The advanced cathode can enable ultra energy density Li-ion batteries which can provide significant mass and volume savings and operational flexibility for NASA near-term exploration missions.
The Energy Efficiency Management Platform (E2MP) is a power-aware, "Green" computing technology for managing energy consumption on High End Computing (HEC) systems while still achieving performance targets.

The E2MP dynamically controls processor clock frequencies and voltages in a way as to minimize the energy required to complete the application run.

The platform functions by running predictive analytics on application trace data and developing a customized frequency &amp; voltage management scheme based on characteristics of the application and input set.

The Phase I objective is to construct a technology demonstration of the platform using a computer server and workload (application) profile representative of NASA's HEC environment.  The demonstration, based on an application of interest to NASA (OVERFLOW) will prove the feasibility of handling arbitrary input data sets and conducting statistical power modeling, laying the groundwork for further commercialization activities in Phase II.
Acute challenges are faced by the designers of fluid systems for spacecraft because of the persistently unfamiliar and unforgiving low-g environment. For example, most fluid systems aboard spacecraft are impacted by the presence of capillary forces&amp;#151;a poor understanding of which has led to poorly performing life support equipment. Despite an increasing number of flight investigations concerning capillary phenomena, no broad re-assessment and re-design of low-g fluids systems has been undertaken. We propose a fundamental change to spacecraft fluid systems design. In this Phase I research, concurrent with a modern review of all candidate spacecraft fluid systems, we will design and demonstrate two new geometric flow components for the critically and persistently problematic unit operations of in-line bubble and liquid rivulet separations. The new components can be exploited across a variety of spacecraft fluids systems to markedly increase system reliability and performance. Many other components are envisioned as inspired by recent results from space experiments and the application of novel geometries. Such components offer the advantages of no power, no moving parts, and little to no pressure loss as they passively separate fluid phases using capillary forces and motive fluid streams.
ATA Engineering, Inc., (ATA) proposes a Phase II SBIR program to demonstrate an innovative engine air-brake (EAB) technology that uses a deployable swirl vane mechanism to switch the operation of a turbofan engine nozzle from a conventional mode to a "drag management" mode. Equivalent drag (via thrust reduction) results from the strong radial pressure gradient created by swirl vanes that are aerodynamically "invisible" during conventional operation and introduced during a drag management maneuver. Such "drag on demand" enables operational benefits such as slower, steeper, and/or aeroacoustically cleaner flight on approach, addressing NASA's need for active and passive control of aeroacoustic noise sources for conventional and advanced aircraft configurations. In Phase I ATA successfully designed an integrated vane-nozzle for a NASA high bypass ratio nozzle. To advance the technology readiness level (TRL) , ATA has formed a partnership with Williams International (WI), a manufacturer of small jet engines and industry leader in the small business jet market. The ATA/WI team will apply the Phase I design approach to the WI FJ44-4 mixed flow turbofan which is selected as a demonstration test article to move the TRL to 5&amp;#150;6 by the end Phase II.
Remote Sensing Solutions proposes to develop the Network-based Parallel Retrieval Onboard Computing Environment for Sensor Systems (nPROCESS) for deployment on NASA's unmanned aircraft systems (UAS).  The nPROCESS will provide a compact, efficient, reconfigurable computing environment that will achieve unparalleled real-time data processing, acquisition and distribution to provide new observations and improved sensitivity; provide a test-bed for measurement and algorithm development and testing for future mission risk reduction and demonstration; produce critical information for real-time decision making; and facilitate a path to reduce risks and installation / operational costs for deployment of new and existing sensors on NASA UAS platforms.  The proposed innovations to realize nPROCESS are: (1) reconfigurable, object orientated system architecture that will provides far greater customization and expansion, (2) modularity at the hardware, firmware and software levels to adapt to the sensors needs at minimum cost and (3) high fidelity parallel processing and data distribution capabilities. Deployed with the HIWRAP on the NASA Global Hawk, nPROCESS will provide higher quality and real-time mapping of the three-dimensional wind profiles, ocean vector surface maps and precipitation winds within tropical cyclones.
Fault Management (FM) is a key requirement for safety, efficient onboard and ground operations, maintenance, and repair. QSI's TEAMS Software suite is a leading facilitator diagnostic and FM modeling, and performing various FM-related functions. Through this effort, QSI proposes to introduce capabilities to TEAMS that would significantly Reduce diagnostic model development cost and time, Enhance analytic capabilities for aiding model evaluation, and,  Improve FMECA Process. These issues are of critical importance in developing and maintaining diagnostic models in a cost and time efficient manner and utilizing those for analyses related to diagnostic designs, models and overall scheme evaluation. The capabilities and features targeted in this effort are of high importance to develop and mature diagnostic schemes for systems in design phase as well as fielded systems. High-value assets such as NASA's space vehicles; Department of Defense's vehicles (Military aircraft, ships, and ground vehicles) whose underlying systems are designed with the philosophy to serve multiple types of mission involving different phases (or regimes) of operation. From that perspective, the outcome capabilities of this effort could also aid in developing diagnostic models and schemes for large and complex industrial installations.
In this SBIR Phase 1 we propose to develop a novel microscope by integrating Fourier phase contrast microscopy (FPCM) and epi-fluorescence microscopy.  In FPCM, the high degree coherence of low power laser source provides well resolved spatial frequency bands in the Fourier plane and the retardation is generated by photo-thermally induced phase transitions in a liquid crystal by varying the intensity of the laser. Further the controlled phase shift induced by the liquid crystal cell will be utilized for quantitative phase imaging. On the whole, the system offers simultaneous recording of Fourier phase contrast and epi-fluorescence images shot at the same time (at the speed of the camera). Similarly it is also possible to perform simultaneous quantitative phase and epi-fluorescence imaging in real time. The proposed microscope offers several unique advantages over the commercially available state-of-the-art technology. Our system is physically robust, user friendly, maintenance free, with no moving parts and frequent alignment, consuming minimum power. The modular system built with inexpensive optical components is versatile. It will be extremely useful in the biological and biomedical research labs. The system can be conveniently installed in International Space Station for high throughput live cell imaging.
Icing is a significant aviation hazard, and icing conditions continue to be difficult to  precisely forecast or locate in real time.  An in-situ sensor, which can be flown coupled with a radiosonde, is needed which can both measure supercooled liquid water content in clouds as well as characterize the droplet sizes.  This sensor will support the calibration and validation of remote-sensing methods used to detect icing conditions, and can also be used on its own to support operational meteorology applications.
Anasphere, Inc. proposes to develop a sizing supercooled liquid water content (SSLWC) sonde which will meet this need.  It will be based on proven vibrating-wire technology which has been used for total water content measurements, but with an altogether different physical implementation that will enable droplet sizing.
Phase I will involve the aerodynamic design of the SSLWC sonde, icing tunnel tests demonstrating key elements of its function, and a live flight test to gather information on the sonde's aerodynamic characteristics.  Phase II will involve further tunnel tests, laboratory calibration development, design for manufacturability, and flight tests in icing conditions.
State-of-the-art additive manufacturing technologies for metal parts have evolved around powder metallurgy and fusion welding-based processes.  Both of these processing methodologies yield parts with inferior mechanical and physical properties as compared to wrought metal of the same composition.  Additionally, the production rates for even the fastest processes are relatively low (~40 lbs/hr for Ti) and the part envelopes are limited to a few cubic feet.  Aeroprobe proposes a highly scalable process for additive manufacturing of wrought metal structures based on their additive friction stir (AFS) process which provides high-strength coatings and welds (strengths comparable to the base metal UTS) while retaining a wrought microstructure.  AFS has successfully deposited materials ranging from light metals, such as Al and Mg alloys, to high-temperature metals, such as Inconel 625 and oxide dispersion strengthened steels.  Initial additive manufacturing demonstrations with AFS were highly successful and produced fully dense structures with wrought mechanical properties.  The overall objective of this project is to further develop AFS technology into an additive manufacturing process to enable full-density, near net-shape fabrication of airframe structures.  An initial process-structure-property relationship study will be conducted to demonstrate the physical and mechanical properties achievable in Al alloys via AFS.  Finally, Aeroprobe will demonstrate the feasibility of AFS to produce complex 3D structures by fabricating an aluminum demonstration part of a relevant geometry.
NASA missions for planetary exploration require high power, long-life Hall thrusters.  However, thruster power and lifetime are limited by the erosion of plasma channel walls.  Current plasma channel insulator materials, such as BN or Borosil, have the required low secondary electron emission (SEE) but are susceptible to xenon plasma erosion.  New plasma channel insulator materials with low SEE yield and high xenon plasma erosion resistance are needed to increase the efficiency and the lifetime of Hall thrusters.  AlN has an exceptionally high plasma erosion resistance but suffers from a high SEE yield.  AlN can be a "revolutionary" replacement for BN channel insulator since it provides high plasma erosion resistance with structural robustness and high thermal conductivity if it's SEE yield can be reduced.
This SBIR Phase I program will develop a revolutionary AlN plasma channel insulator with lower SEE yield and higher erosion resistance than BN and BN-SiO2 for high power, long-life Hall thrusters.  In Phase I we will (i) reduce the SEE yield of AlN by microstructural engineering, and (ii) fabricate fully functional plasma channel insulators for thruster testing at NASA-GRC to determine if the reduction of SEE yield of AlN channel insulator leads to better thruster performance than BN channels.
Energid Technologies proposes a software tool to predict robotic mission performance and support supervision of robotic missions even when environments and situations are profoundly unknown. It transcends common Monte Carlo simulations by supporting input parameters for which probability distributions are not available. Stochastic optimization is combined with randomized simulation to bound statistical measures of performance and convey the parameters giving the extreme scenarios.  It also provides 3D immersive presentation of those scenarios. The act of performing multiple simulation runs in real time is enabled by the fast simulation capability provided by Energid Technologies' existing software combined with the development of new algorithms and software. The new algorithms cover path planning, scene rendering, sensor modeling, and robot-terrain interaction modeling.  In the new software, automatic path planning is calculated using a combination of static and dynamic techniques.  Scene rendering for sensor modeling is implemented using fast ray tracing for low-update-rate sensors and ray-tracing-validated rasterization for fast-update-rate sensors.  Robot-terrain interaction is calculated through particle simulations implemented on graphics cards.  For maximum performance, the new software allows distribution of randomized simulation runs over multiple networked PCs and cloud-based clusters.  This combination of fast algorithms and statistical optimization offers a tool that provides new engineering insights and data. The software will be demonstrated on the example mission of searching for ice near near the southern lunar pole, giving evidence of the ability of the tool to support challenging relevant missions.
Energy storage devices in many aerospace applications are facing unique challenges. Most of such applications, including remote surveillance, satellites, reusable launch vehicles, etc. depend on high-performance, highly specialized batteries. NASA desires high specific energy batteries that are safe for human exploration missions. Since none exist today, they must be developed. Storagenergy Technologies Inc. and its team members propose to develop a novel core-shell structured sulfur-carbon nanocomposite and novel electrolyte systems for high performance rechargeable lithium-sulfur batteries. In Phase I, the composite materials will be synthesized and characterized. The composite's electrochemical performance along with novel electrolyte systems will be evaluated in full cells. Cells with with a minimum capacity of at least 200 mAh will be fabricated and evaluated. During the Phase II, the composite's composition will be optimized further, its performance in cells with 1Ah will be evaluated, and a low-cost large-scale material production process will be developed.
In Sub-topic O3.04, NASA has identified a need for control of material degradation to extend the life and reduce the life-cycle costs of piping systems subject to microbial influenced corrosion in the presence of untreated or brackish water.  The corrosion mechanisms of greatest interest are salt and acid attack due to exposure to brackish and untreated waters.  International Scientific Technologies, Inc., in conjunction with Ferrum College, proposes the development of a protective barrier conversion coating to prevent corrosion cell formation in steel substrates.
In this SBIR program we will develop, design and build new scanning based micro-ladar sensors with unprecedented small size, weight, and power (SWaP), thereby enabling scanning ladar deployment on previously inaccessible platforms such as satellites.  The system will range out to &gt; 1 km, have high frame rates, high resolution (up to 1000 x 1000), high range accuracy (&lt; 15 cm), weigh only tens of grams, be constructed from space deployable technologies with no-moving parts.  The enabling technology for the proposed Micro-LADAR system is a combination of two new electro-optic laser scanning technologies: high speed refractive continuous scanners with a 60o?15o field of view (FOV) and diffractive-waveplate discrete or step-wise scanners to boost the total FOV up to 120o?120o. The results will be a very low-power, long-life (no moving parts), radiation hard, micro-LADAR.
This work directly addresses a technology of interest listed in Section 9, sub-section H1.01 In-Situ Resource Utilization, specifically "Highly efficient reactors for carbon monoxide/carbon dioxide (CO/CO2) conversion into methane (CH4)."

The proposal will investigate combining recent work that demonstrates outstanding CO2 sorption by third generation ionic liquids (ILs) without an increase in viscosity (even in the presence of water) with adaptations of recently developed methodology for electrochemically reducing and polymerizing CO2 in an aqueous IL to polyethylene. The intention is to demonstrate that this methodology is an excellent candidate for creating a highly efficient reactor for carbon dioxide conversion to methane. Unlike conventional electrolytes, ILs generally have very low vapor pressures.  This will make it possible for them to be used in the much lower pressure Martian atmosphere without the problem of evaporation.

Our goal is to build on the results achieved by other research groups by using our own knowledge and years of experience working with ILs, including electrochemistry, to efficiently reduce CO2.  We will prepare the task-specific 3rd generation ILs and then measure their electrochemical properties; i.e., conductivity, electrochemical window, etc.  These are currently unknown but are important in order to ascertain whether these ILs are suitable for this application.   Anticipating this will be the case, we will then test various electrodes, including TiO2 and silver cathodes, to determine which gives the most selective reduction of CO2 to methane.  The efficiency of the process (including power requirements) will be quantified and compared to the Sebatier and Fischer-Tropsch processes.
In the Phase I program, Busek Co. Inc. tested an existing Hall thruster, the BHT-8000, on iodine propellant.  The thruster was fed by a high flow iodine feed system, and supported by an existing Busek hollow cathode flowing xenon gas.  The Phase I propellant feed system was evolved from a previously demonstrated laboratory feed system.  Throttling of the thruster between 2 and 11 kW at 200-600V was demonstrated.  Testing has shown that the efficiency of iodine fueled BHT-8000 is the same as with xenon, with iodine delivering slightly higher thrust to power (T/P).  

Plume current was also measured at a variety of operating conditions.  Preliminary design work for a new thruster to be built in Phase II was also completed.
  
In Phase II a complete iodine fueled system will be developed including the thruster, hollow cathode, and iodine propellant feed system.  The nominal power of the Phase II system is 8 kW.  However, it can be deeply throttled as well as clustered to much higher power levels.  The technology can also be scaled to &gt;100 kW per thruster to support MW-class missions.  The target thruster efficiency for the full scale system is 65&#37; at high Isp (~3000 s) and 60&#37; at high thrust (Isp~2000 s).  These projections are based on Phase I testing and prior testing of higher power thrusters.
  
Iodine enables dramatic mass and cost savings for lunar and Mars cargo missions, including Earth escape and near-Earth space maneuvers.  High purity iodine is available commercially in large quantities at much lower cost than xenon.  Iodine stores at 2 to 3 times greater density than xenon and at approximately one thousandth of the pressure and may be stored in low mass, low cost propellant tanks instead.  Passive, long term storage of a fully fueled system is feasible including storage in conformal tanks which may be used to shield internal components against some types of space radiation.
The proposed innovation is for enhanced sensor performance and high resolution imaging for Long Wave InfraRed (LWIR) and Medium Wave IR (MWIR) camera systems used in aerial imaging applications through integration with KeyW's advanced EO/IR Imaging eGimbal&amp;#153; (IeG) system.  Increases in pixel densities with the advent of large format monolithic focal plane arrays (FPAs), as well as new detector materials, has led to the development of faster frame rate cameras in these long-wave spectral bands.  These next generation systems have enabled the transition of applications and operational CONOPs more traditionally used with high resolution Electro-Optical (EO) camera systems to long wave sensors.  Specifically, the SBIR team of GIA and KeyW propose to 1) design an integration plan for a more robust version of IeG, three-axis gimbal system developed from a previous SBIR with NASA Goddard, to small format, high-sensitivity, MWIR/LWIR cameras, including the development of a sensor model to perform the coordinate transformations to geo-register the long-wave imagery; 2) design a geometric and radiometric calibration approach to ensure accurate projection and image quality of the MWIR/LWIR data; 3) design the command and control software to ensure accurate targeting of the proposed MWIR/LWIR sensors; and 4) study/design techniques and operational parameters that will allow the MWIR/LWIR sensors to meet the requirements of selected target applications and products.
Cryogenic engines for in-space propulsion require innovative technologies to provide long-life, lightweight, and reliable turbopump designs.  One area open for improvement is seals for rotating-to-static hardware.  Florida Turbine Technologies, Inc. (FTT) is proposing the use of a floating seal for turbopump applications.  The floating seal would allow lower leakages than current state-of-the-art seals, such as labyrinth seals.  The floating seal also has the added benefit of maintaining low leakages throughout transients and rotor displacements, since the floating seal's clearance tracks with the rotor axial movement and is independent of radial movement.  Plus, the floating seal is a non-contacting seal with high pressure and speed capability; this increases its reliability relative to contacting face seals or labyrinth seals operating at the same conditions and leakages.  The floating seal is proposed to work with the cryogenic liquid propellants used in upper stage engines, liquid hydrogen and liquid oxygen.  The feasibility of the floating seal for turbopump applications will be determined through detailed 3D computational fluid dynamics (CFD) analyses.  1D parametric studies to vary the seal geometry and boundary conditions will also be performed.  The concerns of axial instability and increased turbopump axial length will be addressed during Phase I.
Energy Storage is a critical component of space-based platforms across the full spectrum of exploration, scientific experimentation, defense, communications and monitoring missions.  NASA has set targets of 265 Wh/kg of 675 Wh/l for batteries for near-term energy storage applications. Li-ion battery technology has the highest energy density among rechargeable battery technologies. However, achieving the near-term goals require implementation of next-generation active materials. We propose to develop Li-ion cells that meet NASA's near term targets by combining our CAM-7 cathode material, the highest energy content market-ready cathode material available with market-ready Si-based anode materials.  Because of its high reversible capacity (&gt; 205 mAh/g), high discharge voltage (average 3.85 V vs. Li) and high density (4.8 g/cc), CAM-7 can yield higher energy Li-ion cells than any other market-ready cathode material.  A version of CAM-7 targeting portable power and vehicle applications has been fully developed and, as part of its commercialization, is currently being transitioned to a 50 ton per year plant in Massachusetts. In the proposed Phase I program, TIAX will optimize the CAM-7 composition to yield the highest possible cell energy while still meeting the life targets, and simultaneously optimize an anode electrode incorporating a market-ready Si-based material.  TIAX will then combine them in Li-ion cells that demonstrate the resulting system's ability to meet all NASA near-term energy, performance and life targets.  The Phase I program will demonstrate, at the 200 mAh cell level, performance and cycling of electrode designs projected to meet and exceed NASA's near-term targets when they are incorporated in 18650 cells.  A successful Phase I program will be followed by a Phase II program in which such 18650 cells are developed, assembled, and rigorously tested against NASA requirements.
The overall objective of this multi-phase project is to explore, develop, integrate, and test several innovative structural design concepts and new material possibilities that will fully leverage the expertise of the ZONA/Boeing Team for enhancing the current state-of-the-art of aircraft design. The technical objectives specific to the Phase I of this effort are threefold. First, a suitable anisotropic composite material will be identified and further studied for its suitability to the design objectives of this research. A baseline SUGAR aircraft configuration will be thoroughly studied for exploring design possibilities as well as to provide a benchmark for comparing performance improvements achieved by optimization studies performed during later stages. Secondly, the skin of the baseline SUGAR wings will then be modified to comprise of the anisotropic composite material, and the FE model will be modified to comprise of (1) distributed multiple control surfaces for AAW-type optimization in Design Route 1, and (2) variable camber continuous trailing edge flaps (VCCTEF) for control output optimization in Design Route 2. The updated FE models will then be used to further optimize the composite layup sequence as well as skin thicknesses. Thirdly, the distributed control surfaces and the VCCTEF on SUGAR high aspect ratio wing will be separately optimized for control input to achieve load alleviation and drag reduction. These two separate optimization processes of Design Route 1 and Design Route 2 will be performed iteratively to achieve an optimum low-drag low-weight design. Finally, once the optimum designs are obtained, a detailed performance review will be conducted to quantify the benefits of the non-conventional design technologies explored. A material fabrication feasibility study will also be performed.
The proposed innovation is a low-cost, retrievable and reusable, autonomously guided dropsonde capable of in-situ atmospheric measurements.  The proposed effort will focus on the engineering work involved with the retrieval of volcanic ash plume samples.  This work will build upon a previous NASA SBIR Phase I project Latitude Engineering completed in 2011: the development of an Advanced Guided Dropsonde (AGD).   Though the tested prototype received favorable reviews, funding restructuring of the SBIR program within NASA prevented funding for Phase II.  To keep the momentum behind this innovative airborne platform, Latitude Engineering is proposing to build upon this accomplishment: refine the current dropsonde design and develop a sampling system for atmospheric particulates that will be integrated into this 4 cm diameter research vessel.  Miniaturized particulate sampling equipment for airborne missions is not commercially available.  Even for full scale systems, many research programs develop their own collection and sensor systems.  With the small size limitations of the AGD, a multi-stage particulate sampler can be developed that can collect size segregated particulate including aerosols.  With the significant need for atmospheric particulate sampling, the AGD can offer unprecedented access to atmospheric samples including those at high altitudes.
The key goals of this Phase I proposal are to demonstrate the capability of the AGD to be released from a host manned aircraft, collect an atmospheric particulate sample from a pre-programmed altitude and location, and deliver the protected sample to a pre-programmed recovery area. This system, engineered to be cost compatible with existing dropsonde launch systems, is recoverable and re-useable.
The goal of this program is to demonstrate the use of UAM to additively build reinforcement structures to reinforce cut outs in larger aluminum structural components. The team will work with NASA to scope a 'generic' opening in an aerospace aluminum structure. UAM will be used to perform two reinforcing activities. Firstly, UAM will be used to thicken the cross section of the aluminum component in a selective manner. This will provide additional stiffness through geometric effects without starting with a large billet of material. Secondly, UAM will be used to embed reinforcing materials (such as SiC fibers, steel wire, carbon fiber) in and around the opening to create a true MMC in the region(s) around the opening. Smalll channels will be machined to receive wire reinforcements. UAM will be used to create an embedded layered structure of embedded fiber around the opening. Mechanical testing of windows will be performed to quantify the increase in mechanical performance.
The project will prototype a specification editing and discovery tool (SPEEDY) for C/C++ that will assist software developers with modular formal verification tasks by
- providing active user interface guidance in writing and editing software specifications, integrated into a common, open IDE (Eclipse) and
- providing automated suggestions of specifications for given contexts, 
- built on an architecture that will unify source and machine code verification.
The innovation is significant because
- having machine-checkable specifications enables more automation of sound verification and less approximation in heuristic problem detection,
- user interface features and underlying automation will aid all developers in generating, editing and checking specifications, and
- the architecture will apply to both source code analysis alone and also to unified source and machine code verification for embedded systems.

The prototype will be an extension and integration of (a) current specification languages, (b) previous Eclipse plug-ins GrammaTech has created, (c) recent research on UI aids to developers in writing specifications, (d) existing automated algorithms for suggesting specifications based on code analysis, and (e) existing tools and techniques for automatically checking logical encodings of C/C++ code and specifications. The tool will be packaged as a plug-in to Eclipse's C/C++ development environment.

The result will be a tool that facilitates using formal methods by all software developers, improving efficiency and accuracy. The resulting specifications will also serve as machine-readable documentation of the software, simplifying and accelerating the task of independent V&amp;V.
Ferrite control components including circulators and isolators are fundamental building blocks of Transmit/Receive modules (TRM) utilized in high data rate active space transceivers and transponders for both long-range (LR) and low earth orbit (LEO) systems. These components are utilized to protect high power amplifiers (HPA) during the transmit cycle from destabilizing, and potentially harmful, power reflections from the antenna element. During receive cycle these components are utilized to direct lower power received signals with minimal attenuation to the low noise amplifiers (LNA). As such, performance specifications of these ferrite control components, such as bandwidth, insertion loss, isolation, power handling, temperature stability, radiation hardness, and linearity impose strict limitations on the overall system performance.
Over the course of the proposed Ph1 SBIR program self-biased ferrite control components based on highly textured hexagonal ferrite compacts which have the potential to eliminate biasing magnets and significantly reduce the size, cost, and weight of the TRM while concurrently increasing power handling capability, and improving temperature stability and radiation hardness will be investigated. Specifically, a research and development path to realizing high performance self-biased ferrite materials and device designs for operation in space based environments at Ka-band (&gt;27 GHz, 31.5 - 34 GHz targeted) is outlined.
This SBIR project delivers an On-orbit Validation System (OVS) that provides performance and durability data for Macro Fiber Composite (MFC) active piezocomposite materials operating in the space environment. Our NASA customer is the Macro Fiber Composite Actuator Experiment (MFCX), which uses the Materials International Space Station Experiment-X (MISSE-X) platform. MISSE-X will expand ISS utilization by advancing the Technology Readiness Level of new materials, devices, and subsystems. OVS uses the impedance method to validate both MFCs and in situ self-health monitoring methods.
Implications of the innovation:
MFC piezocomposites have been flown, but only in a shielded enclosure for a short duration. MFC materials will need to operate continuously with minimal thermal protection to enable active composite reflector structures, large solar array active control, and structural self-health monitoring. Data is needed on the viability of MFC materials for long-duration space applications.
Technical objectives:
OVS leverages our previous NASA SBIR research. Our initial impedance method prototype exists as a TRL 5 unit. We have demonstrated both analog and digital MFC operation. However, it is not clear which approach (analog or digital) is best for OVS. Each approach has different power, mechanical, electrical, and computational needs&amp;#151;it is not clear which is the best match for MISSE-X. Indeed, a new configuration may be required. Phase I addresses these concerns and establishes feasibility through validation tests and experiments.
Research description:
We have already developed an impedance-based electronics package and validated it under simulated launch conditions. Phase I transforms this implementation for MISSE-X compatibility and produces a Phase II road map.
Anticipated results:
Phase I addresses the main barrier to MISSE-X operation, and completes a TRL 5 prototype that is MFCX compatible. Phase II delivers a fully operational TRL 7 unit.
Rice is an important crop globally that influences food security and the Earth system. Rice is the predominant food staple in many regions with approximately 700 million tons of production annually across the globe. Rice is sensitive to a variety of drivers that can adversely impact production and efficiency including weather variability and inter-seasonal volatility, water resources, and risk management decisions (e.g., pests). Futures are a tool used to manage or hedge risk, reduce volatility, improve food security, and maximize efficiency and profit on the open market. Currently, the rice futures market has little high quality and timely information available to make strategic or application specific decisions to reduce risk and maximize profit. The global rice futures market is thinly traded causing extreme price fluctuation orders of magnitude. This innovation gap has created an opportunity to build an operational Rice Decision Support System to support the rice futures market. The overarching goal of this NASA Phase I SBIR is to evaluate the feasibility of a Rice Decision Support System (RiceDSS) to Support Global Food Security and Commodity Markets.  RiceDSS brings together operational remotely sensed mapping of rice, crop production modeling, and weather forecasts to seamlessly generate near real time information on rice extent, growth stages, yield forecasts and statistical uncertainty. RiceDSS uses state-of-the-art web-GIS and mobile technologies to support visualization and delivery of information to futures markets and food security programs.
The overall objective of this research project is to investigate autonomous control architectures for spacecraft power systems. Such techniques will be critical for deep space missions that face inhospitable environments, unpredictable operating conditions, and communication delays. The distributed nature of agent-based control will also support plug-and-play capabilities for modular power systems. The first main focus of the Phase II effort is to expand and refine the International Space Station (ISS) model library created in the Phase I. This will enable advanced energy management studies by supporting the interconnection of multiple channels. In addition, hardware validation of both component and system models will be pursued. Finally, Distributed Heterogeneous Simulation will be applied to the system models to accelerate simulation speed. The second main focus of the Phase II will be to utilize the simulation environment to investigate agent-based autonomous controls. In particular, the ability of agent-based controls to perform in scenarios that stress conventional controls will be analyzed. This ability will also be examined when communication constraints (such as sample rates and latencies) and packet loss are present. Lastly, the ISS system model will be integrated with hardware agent emulators setting the stage for hardware experimentation in future efforts.
To advance the effectiveness of exercise activities performed to counteract bone and muscle deterioration under microgravity conditions, Aurora Flight Sciences and the Massachusetts Institute of Technology propose to develop a self-contained, enhanced dynamic load sensor that can be integrated into the existing exercise equipment onboard the International Space Station.  These sensors will allow the collection of crewmember biomechanical while they are exercising on-orbit.  These data can be used to validate the effectiveness of the countermeasures and improve their impact to mitigate bone and muscle loss during long duration spaceflight missions.
High performance LWIR detectors are highly needed. In order to image from long distance, it is important that imagers have high sensitivity, high resolution, and very low dark currents. This leads to technical goals of having low noise, low dark current in small size pixels in large arrays. While saturated performance levels of traditional systems based on bulk semiconductors have not quite met the requirement of applications, it is expected that novel quantum systems will bring new development stage for infrared imagers.

In recent years, Type-II InAs/GaSb superlattice (T2SL) has experienced significant development, from theoretical modeling, material growth to device processing and packaging. Performance of LWIR detector based on T2SL has become comparable, even better than that of HgCdTe. However, LWIR T2SL devices have been shown to be limited by surface leakage, especially at lower operating temperature.

This proposed effort will investigate gating of Type-II photodiodes as a means to suppress this bottle neck of T2SL technology. The ultimate goal of this project is to develop an effective method to completely suppress the surface leakage current in LWIR type-II superlattice photodiodes that is compatible with the development of high performance gated FPAs in Phase II.
We propose to develop a highly sensitive and compact monitor to measure light absorption from particulate matters. The fundamental of the proposed device is based on differential photoacoustic absorption spectroscopy (DPAS). It will be able to be remotely controlled and operated at high altitude. Background interference from NO2 absorption and acoustic noise of aircraft engines will be significantly reduced due to a specific acoustic cell design.

    The Phase I project will provide a proof-of-concept demonstration. The ultimate goal of this study is to design and construct a portable PM absorption monitor for NASA's airborne measurement programs. The tasks of the proposal will include:
   1)	Construction of a laboratory prototype DPAS PM absorption monitor;
   2)	Development of an absorption calibration scheme;
   3)	Comparative study on optical absorption of laboratory soot      
        particles with multi-angle absorption photometer (MAAP); and
   4)	Performance evaluation at a variety of sampling pressure. 

    This SBIR Phase study will be performed by Aerodyne Research, Inc., in collaboration with United Technologies Research Center (UTRC). Both companies have been major participants in past NASA/FAA-sponsored aircraft emissions programs with extensive experiences in the study of PM optical absorption as well as soot formation and evolution in the atmosphere.
The objective of this proposal is to demonstrate a set of methods for automatically extracting metadata from diverse data sets to serve as a common vocabulary by which data can easily be queried, retrieved and combined for visualization in a geobrowser. We propose extracting keyword tags from both structured and unstructured data sets by applying natural language processing (NLP) to metadata and unstructured content. The extracted tags will be associated with each data set as supplementary metadata to assist with data discovery, categorization and spatial-temporal location. We combine manually-generated tags, based on domains of interest or specific decision support activities, with automatically generated tags from NLP, and to develop hierarchical clusters of the combined tags to serve as a common set of descriptors by which different data sets can be discovered and combined. If proven successful, our approach will be useful for the management and fusion of very large and diverse data sets not only for applied science and decision support, but also for emergency management and related security operations, for business intelligence, and for other application involving large quantities of diverse data, both structured and unstructured.
Processor speed has traditionally grown at a rate faster than that of
communication speed in computer and supercomputer networks, and it is
expected that this trend will continue even stronger, as we move into the
exascale age in the upcoming decade. This has resulted in what is known as
the "communication gap" for communication-bound HPC applications: their
communication-to-computation time-ratio is so large, that the processors
remain mostly sub-utilized, with lots of "disposable" FLOPS available. In
the last few years, scientists have proposed to use these disposable FLOPS
(which otherwise would be wasted idling) to compress and decompress the
communicated data so to effectively speed up the underlying application.
Although the idea bears tremendous potential, efforts in this direction have
consistently rendered very poor results, with typical resulting speedups
averaging below 1.5x. In this project, we identify the strongest reasons why
traditional data compression has fallen short in terms of speedup
performance for HPC, and propose novel techniques particularly crafted for
groundbreaking performance within the HPC framework. Preliminary results
show that these techniques break the 10x speedup markup consistently for a
wide class of HPC applications of primary importance to NASA. We propose to
develop the theory and methods behind these techniques, which ultimately
will result into a library product for transparent acceleration of HPC
communication platforms, such as MPI. Accelogic has already secured Phase
III private capital in the amount of $1 million for the deployment of such
potentially revolutionary product, following a successful Phase II.
The overall scope of this Phase I/II effort is the development of a high efficiency 15kW (nominal) Hall thruster discharge converter.  In Phase I, Busek Co. Inc. will design, fabricate and test a nominal 7.5kW breadboard discharge converter module.  Busek proposes a converter topolgy called the Leading Edge Auxiliary Phase Shifted (LEAPS) Bridge, which is a modification of the standard phase shifted bridge that uses an energy-recovering auxiliary circuit to force the transition from output inductor freewheel to power flowing through the main transformer.  Based on preliminary measurements with this topology the converter module demonstrated &gt;97&#37; efficiency at reduced power.  
A 300V line input and 300-400V output range are the benchmark for the discharge converter in Phase 1.  The most reasonable path with higher input voltage for higher power converters involves the use Wide Band Gap FETs.  MOSFETS represent the greatest payoff in terms of efficiency improvements and are a primary focus for a discharge converter to achieve an efficiency of 98&#37; or greater.  With the design maturity gained from the Phase I breadboard, the Phase II objective will be the production of a 15kW brassboard PPU in a flight-like form factor that incorporates conductive cooling.
NASA requires new instrumentation technologies that can be applied to measure dynamic quantities such as acceleration and flow velocity under extreme temperatures where traditional sensing methodologies cannot be applied.  The proposed Phase I SBIR research effort will seek to create accelerometers and flow sensors that can be applied to measure signals at temperatures in excess of 900F.  In order to accomplished this proposed task we will develop new sensor modalities built on vertically aligned ZnO nanowires.  ZnO is a piezoelectric materials that is not ferroelectric and thus it has an intrinsic polarization and no Curie temperature where traditional piezoelectric materials cease to function.  The proposed objective of this program is to advance the field of sensing through the development of a novel nanostructured sensor for the measurement of acceleration and wall shear-stress at high temperature.  The proposed sensor will provide the ability to make measurements at spatial resolutions previously unrealized through the patterned growth of the nanowire arrays thus providing a smaller footprint and an opportunity for numerous sensors on a single chip.  The nanowire synthesis process is solution based and scalable allowing sensors to be built for a fraction of the cost of the complex lithography based methods of current MEMS technologies.  These advances will allow researchers to study complex flows and dynamics such as those in turbomachinery under operational temperatures not conducive to current sensing technologies.  Our results will seek devices with previously unrealized dimensions and properties that will impact numerous fields of science including the efficiency of turbomachinery.
Spacecraft charging and subsequent vacuum arcing poses a significant threat to satellites in LEO and GEO plasma conditions. Localized arc discharges can cause a flashover plasma expansion, that can lead to further discharge of charge stored on dielectric surfaces such as solar panel arrays, which can cause catastrophic events over large areas of the panel array surfaces. While spacecraft charging has been studied for a long time, the dynamics of flashover currents and propagation of the expanding plasma have not be well-characterized, although they are key in order to understand how to mitigate damage to solar panel arrays during discharge events. This project will improve the understanding of arc discharges and expanding plasma effects on dielectric structures such as solar panel arrays so that NASA will better be able to protect satellites from damaging vacuum arc discharges. We will develop accurate numerical simulations that model localized arcs, plasma expansion, and dielectric charging and discharging, under both simulated LEO and GEO plasma conditions. We also plan to extend our models to include the effects of non-uniform ambient plasma densities, secondary electron emission effects, and photo-electron effects.  In Phase I, we will validate our numerical models against the theoretically known problem of expansion of a plasma into a vacuum, and will develop detailed simulations of a new AFRL round-robin experiment to test plasma propagation speeds in the presence of a charged dielectric material.  We also plan to develop easy-to-use GUI interfaces so that NASA scientists will be able to use high-performance computing resources to examine the parameter space for these types of problems without having to dive deep into the code infrastructure and numerics of the simulations.  At the conclusion of Phase II we plan to provide NASA and AFRL scientists with tools that they can use to better understand discharges on satellites and mitigate damage to solar arrays.
In previous work for NASA, Ultramet and ARA Ablatives Laboratory developed and demonstrated advanced foam-reinforced carbon/phenolic ablators that offer substantially increased performance under high heat flux conditions and reduced weight relative to conventional ablators. The two-piece structure consisted of an ablative-filled foam front surface backed by Ultramet's previously established and highly insulating aerogel-filled foam. Arcjet testing was performed at NASA Ames Research Center to heat flux levels exceeding 1000 W/cm2, with the results showing a significantly reduced ablation rate compared to conventional chopped fiber ablators, and ablation behavior comparable to FM5055 at just one-third the density. It is apparent that the foam helps retain the char layer by physical reinforcement and/or that the network of interconnected passages allows pyrolysis gases to escape with less disruption of the char layer. In this project, Ultramet will team with ARA Ablatives for ablative infiltration of Ultramet foams and Materials Research and Design for ablation analysis, to continue optimization of foam-reinforced ablatives by focusing on two primary areas. The ablator formulation infiltrated into the foam will be modified to maximize heat flux capability consistent with NASA Earth return requirements (1500-2500 W/cm2), and a single-piece foam TPS structure will be developed rather than separate ablative- and aerogel-filled foam sections. Preliminary mechanical and thermal testing will be performed to support design and analysis and, depending on availability, initial ablation tests may be conducted at the Sandia Solar Tower Facility. High heat flux testing at the Air Force LHMEL facility or alternative would be performed in Phase II.
In this proposal, we propose to demonstrate and build a 1.55 micron single frequency high energy and high peak power fiber amplifier by developing an innovative Er-doped gain fiber with large core diameter and high gain per unit length. 1.55 micron single frequency high energy and high peak power fiber amplifier is needed for coherent lidar and sensing. In Phase II, we will further optimize the Er-doped glasses and fibers based upon Phase I results, further increase the pulse energy and peak power, and build a prototype with peak power of 15kW. The output laser beam is diffraction limited. Successful demonstration of such a fiber amplifier will enable many new NASA and commercial applications.
The main goal of this work is to design, implement, and demonstrate a guidance and mission planning toolbox for air-launched, unmanned systems, such as guided dropsondes, sonobuoys, or surveillance aircraft, with the primary goal of enabling users to more effectively achieve mission goals by enabling multi-agent interaction and cooperation. Typical missions that will benefit from the MAMS include those where multiple unmanned vehicles are launched from one or more mother aircraft: for example atmospheric research missions making use of many guided dropsondes, missions distributing a fleet of sonobuoys, or surveillance missions requiring multiple UAVs to patrol a given area. As new vehicles are introduced to the environment (launched from the mother aircraft), or as new areas of interest arise, the MAMS will utilize a distributed network method for adjusting the fleet vehicles' trajectories to maximize the mission effectiveness.
We propose a high quantum efficiency (QE) 1024x1024 longwave infrared focal plane array (LWIR FPA) and CAMERA with ~ 12 micron cutoff wavelength made from bandgap-engineered Type-II InAs/GaSb strained layer superlattice (SLS) photodiodes.  FPA/camera performance goals include QE &gt; 50&#37; and temporal noise equivalent difference in temperature (NEDT) &lt; 30 mK while operating at a temperature &gt; 60K with a fast integration time &lt; 0.5 ms and F/4 optics.  In Phase I, we developed and delivered a high-performance 640x512 SLS FPA as proof of concept, clearly demonstrating the viability of bandgap-engineered Group III-V InAs/GaSb/AlSb materials as a real cost-effective alternative to mercury cadmium telluride (MCT) for NASA's requirements for high-QE LWIR FPAs.  Phase II will build on Phase I by expanding array format, shrinking pixel pitch, improving QE, and packaging and delivering the FPA in a camera that NASA can field-test to evaluate this novel sensor technology.  The 12 micron cutoff, high QE, and relatively high operating temperature of SLS are expected to be of particular benefit to NASA's LANDSAT and HyspIRI projects.
nLight proposes the development of high efficiency, high average power 1550-nm laser transmitter system that is based on Er-doped fiber amplifier resonantly pumped by high efficiency 1532-nm fiber-coupled diode laser pumps.  To meet the efficiency requirement for space communication, nLight proposes to improve overall laser transmitter efficiency by (1) optimizing diode laser and fiber coupling for maximum efficiency of 1532-nm pumps, (2) developing resonant pumping of the fiber amplifier for minimum quantum defect, and (3) design and development of Er-doped fiber amplifier capable of achieving high optical-to-optical efficiency.  Under the proposed program, nLight will design and develop high efficiency 1532-nm diode lasers in conjunction with highly efficient fiber coupling techniques to achieve &gt;40&#37; conversion efficiency of the pump modules.  By developing and utilizing novel fiber laser amplifier technologies, nLight anticipates achieving &gt; 70&#37; optical-to-optical efficiency for resonantly pumped Er-doped fiber amplifier.  It is estimated that a high efficiency 1550-nm fiber laser transmitter will be developed to demonstrate &gt;23 W average power and &gt;23&#37; WPE, the highest efficiency among eye-safe solid-state lasers.
It is increasingly recognized that the Arctic is a bellwether for climate change. As the Arctic region responds to climate forcings, monitoring how aerosol distributions respond and modify their impact on radiative transfer will become increasingly important in refining climate models and predictions. NASA, along with other agencies, has launched several programs such as ARCTAS to increase observations of the region and incorporate findings into large scale climate models. In order to supplement satellite observations and given the difficulty of ground-based observations in the Arctic, instrumented Unmanned Aircraft Systems (UASs) represent one means to efficiently monitor large areas. Measurement of the vertical profile of atmospheric aerosol optical properties can provide new data crucial to understanding climate change in the Arctic. New instrumentation is required to enable routine, widespread measurements with good precision from unmanned aircraft. These new observations will have important implications for global climate change modeling and, ultimately, international energy policy making. In the Phase I program, we will develop a complete conceptual design for a flight-worthy, compact, eye safe lidar that will enable vertical profiling of aerosol optical extinction and scattering and that will be deployable on a compact unmanned aircraft system like the SIERRA or ScanEagle. In the Phase II program, we will fabricate, test, and field demonstrate a prototype sensor.
The Phase I verified ADS-B-ER feasibility-based on compatibility with the ADS-B operational standards and design specs, bandwidth and the iPAD EFB capability for performing the trajectory computations for avoiding hazardous weather, terrain, traffic and restricted airspace. We then assured that the &amp;#150;ER software can interface these waypoints to large variety of existing GA analog and digital auto pilots (approximately 100,000 GA airplanes are equipped with autopilots). The Phase I work demonstrated feasibility by carefully evaluating candidate hardware options. The overall target is a decisive enabler for GA NextGen ops as well as for improved levels of GA safety.
Radiation-hardened non volatile memory is needed to store the golden copy of the image(s) has not kept pace with the advances in FPGAs. Consider that a single image of a Xilinx V5 typically is roughly 50 Mb large. If a designer wants to store several such images in a satellite, then a sizable amount of highly reliable, radiation-hardened memory is needed. As a consequence, there exists a clear need and market opportunity for highly reliable NVM for storing program code, calibration tables and images of reprogrammable FPGAs. 

The goal of this SBIR project is to develop a highly reliable and fault-tolerant, radiation-hardened Memory System-In-a-Package (Memory SIP) which can be used to configure and scrub reconfigurable FPGAs. The Memory SIP will contain a simple radiation-hardened microcontroller and a reasonable amount of commercial flash nonvolatile memory (NVM). It will support the needed standard interfaces that are commonly used for reconfiguring FPGAs, including Xilinx SelectMAP and JTAG.
Busek Co. Inc. proposes to develop a high throughput, nominal 100 W Hall Effect Thruster (HET).  This HET will be sized for small spacecraft (&lt; 180 kg), including nano-spacecraft (&lt;20 kg).  An Edison small satellite demonstration mission could feature this thruster fueled by iodine or xenon.
The Phase I program has five technical tasks.   In the first task, we will determine the throttling capabilities of an improved version of our flight model 200 W thruster.  The improved thruster includes permanent magnets and a modified magnetic circuit. Based upon test results, the basic dimensions of the new 100 W thruster will be determined.  In the second task, the mechanical design will be created.  In the third task, the magnetic circuit will be modeled using Commercial Off-The-Shelf (COTS) tools.  In the fourth task, the plasma discharge will be modeled using existing simulation tools.  In the final technical task, the design will be modeled thermally using COTS tools.  The third, fourth, and fifth tasks will feed back into the design, which will be tailored to balance efficiency against lifetime, operating temperature, mass, volume, and other considerations.
In Phase II, the high throughput low power thruster will be manufactured, tested, and improved.  Performance, lifetime, and plume properties will be evaluated.  Testing will include both xenon and iodine.  Recent testing of a BHT-200 fueled by iodine vapor yielded stability and performance comparable to that observed with xenon, along with lower beam divergence.  Iodine also offers many system level benefits including much higher stored density and much lower stored pressure than xenon.
This proposal responds to topic S3.03, "Propulsion Systems."  Both the "Electric Propulsion" and "Micro-Propulsion" sub-topics are relevant.  The proposal also addresses several of NASA's Grand Challenges, including Efficient In-Space Transportation, Space Debris Hazard Mitigation, and Economical Space Access.
We propose to develope a 64x64 far infrared germanium focal-plane array with the following key design features:

1-	Four top-illuminated, 32x32 germanium sub-arrays will be tiled together to form a 64x64 mosaic array.  Germanium offers very low noise and proven performance in the 50-140?m range.

2-	The array will use four SB349 CTIA readout multiplexers which are manufactured using advanced cryo-CMOS process.  The unit-cell design is optimized for far IR detectors, eliminates detector debiasing, and improves pixel uniformity.  The readout is operational down to at least 1.6K.

3-	A novel, layered-hybrid design using planar bump-bond technology will be employed to assemble the focal plane.  This integrated design offers superior noise performance and effectively addresses the readout glow, detector heating, and thermal mismatch between the detector and the readout.  In addition to the large format, this is the key discriminator of this project.

This is by far the largest far IR photodetecor array produced with projected sensitivity of &amp;#8804; 1x10E&amp;#150;18 W/&amp;#8730;Hz.  This effort fits well within the scope of the SBIR Subtopic S4.01 and will be a benefit to advanced instrumentation of NASA's astronomical missions, in particular SOFIA.
The proposed research effort explores the use of a nanosecond pulse driven offset semiconducting surface dielectric barrier discharge (SSDBD) device for the control of high speed, near surface air flows and the reduction of skin friction drag.  With the nanosecond discharge, very high field strengths are applied and then the field is turned off before glow-to-filamentary transition occurs.  The semiconducting surface array suppresses the backward breakdown that has previously been shown to produce a cancelling backward jet leading to very little thrust for conventional nanosecond driven devices.  The embedded semiconductors achieve this by conducting the backward current through the surface and thus eliminating the backward breakdown. This allows all the momentum produced in the forward direction to be delivered to the surrounding boundary layer flow field.  Conventional sinusoidal driven Surface DBD's are capable of generating surface jets with velocities up to ~10 meter per second, limited by glow-to-filamentary transition of the discharge.  The proposed SBIR work will explore the possibility of increasing the surface jet velocity by more than a factor of five.  In addition, the SSDBD can be driven at a very high repetition rate, producing high repetition sequential surface jets and total thrust that are expected to be orders of magnitude higher than possible with conventional sinusoidal DBD configurations.  These surface jets are expected to provide new methods for the control of boundary layer interactions including separation, transition to turbulence, and drag through the introduction of time varying momentum at selected locations close to the surface.
Tunable filters based on electro-optic effect have shown great potential in detecting gas concentration through obtaining its absorption spectrum. In filter-based technologies, the x-y 2D imaging is usually taken at once, while the wavelength dimension is performed by tunable filters that are mounted in front of a monochrome IR camera. Several types of tunable filters are currently available, including mechanically tuned Fabry-Perot etalon (FP filter), liquid-crystal Lyot-Ohman filters and acousto-optic filters. However, these EO tuning technologies have some shortages, such as slow tuning speed, bulky design, limited working band and small aperture. Boston Applied Technologies, Inc. (BATi) proposes a unique remote sensing system which is based on a tunable filter with under millisecond tuning time for high speed detection of gas concentration. The core part, tunable filter, of the proposed system is made of patented OptoCeramic&amp;#174; material. The system features high speed, wide spectral range from visible to MWIR, low cost, light weight, big aperture, and robust.
Gamma-ray and neutron spectroscopy are well established techniques for determining the chemical composition of planetary surfaces, and small cosmic bodies such as asteroids and comets; however, new technologies with the potential to significantly improve the performance of planetary nuclear spectroscopy are emerging.  We propose to develop new gamma-ray and neutron detectors based on wide-band-gap (WBG) solid-state photomultiplier (SSPM) photodetectors coupled to emerging scintillation materials such as Cs2YLiCl6:Ce (CLYC), and CeBr3 for gamma and neutron spectroscopic studies of planet surfaces and small cosmic bodies. The proposed SSPM photodetector for scintillation readout is based on AlGaAs, a WBG compound semiconductor with aluminum concentration of 60&#37; to 90&#37;. The ~2-eV band-gap energy of this material is engineered to match the emission spectrum of both CLYC and CeBr3. The high band-gap of AlGaAs also provides much lower dark noise and better radiation tolerance than Si-based detectors. Compared to conventional PMTs, the compact size, low voltage operation, and lighter weight of AlGaAs SSPM is ideal for spaced-based instruments. The advantages of AlGaAs SSPMs and the excellent detection properties of CLYC and CeBr3 scintillation materials make them a perfect match in the development of new gamma and neutron spectrometers for planetary science.
OPTRA proposes the development of an imaging spectrometer for greenhouse gas and volcanic gas imaging based on matched spectral filtering and compressive imaging.  The matched spectral filter compressive imager (MSF-CI) system will be capable of simultaneously imaging and quantifying a series of compounds of interest via passive IR spectroscopy from an airborne or space-based platform.The MSF-CI operates in the 3-5.5 micron spectral range and employs two digital micromirror devices (DMDs) &amp;#150; one to encode the spatial information and a second to encode the spectral information &amp;#150; a dispersive spectrometer, and a single element thermoelectrically cooled mercury cadmium telluride detector.  The proposed system offers a significant cost advantage relative to both imagers and hyperspectral imagers presently available in this spectral range as it does not require a costly infrared focal plane array (FPA).  Moreover, the MSF-CI makes efficient use of compressive sensing and matched spectral filtering, resulting in minimized data bandwidth while preserving the information of interest.  In addition, the use of the DMD in place of a conventional FPA offers significantly better image uniformity, pixel operability, signal to noise at low light levels, and dynamic range.  The overall package is expected to be compact and rugged, making it ideal for airborne/space based applications.  The proposed Phase I effort will produce a breadboard MSF-CI system which will be characterized and used for a carbon dioxide imaging demonstration.
There are significant logistical barriers to entry-level high performance computing (HPC) modeling and simulation (M&amp;S) users. Performing large-scale, massively parallel computations on modern supercomputing platforms is a very challenging task in and of itself. It requires huge amounts of analyst resources to construct datasets, transfer files, build codes, submit and monitor jobs, and analyze and archive results. This workflow requires significant attention to detail, and it is easy to miss steps, set up incorrect file or directory structures for datasets, spend inordinate effort to understand each computing platform and its unique job submission requirements, and decide how and where to archive potentially terabytes of simulation results. Collaboration among engineers is hampered by non-centralized storage of results, permission issues, and the sheer size of simulation result sets. Even for seasoned, veteran HPC users, the complexity of the overall HPC use process can be a barrier to daily use. 

We propose a system to streamline this workflow, provide audit trails for data used in simulations, code versions used, and storage locations of results, as well as integrating tools for file transfer, job submission, batch visualization, and other tasks that require engineer's time that is better spent considering the simulation itself. Further, the proposed SLMIR application (Simulation Lifecycle Management &amp;#150; IllinoisRocstar) sets up the infrastructure for collecting simulation data across an organization or organizations, so that engineers and scientists may discover information generated by others in their research areas, potentially saving time and money by leveraging previous work and avoiding duplication. The envisioned system targets users of HPC tools in the field, rather than developers writing those tools, since engineers and scientists in manufacturing and engineering industries are heavily invested in the results of using the tools.
Thorleaf Research, Inc. proposes to develop a miniaturized high flow, low dead-volume pre-concentrator for monitoring trace levels of contaminants in water under microgravity conditions. Our innovative design for the pre-concentrator assembly combines high water sampling flow rates with low dead volume in the device, enhancing pre-concentration while avoiding
cavitation effects. This will help meet monitoring needs for NASA's Spacecraft Water Exposure Guidelines (SWEGs). Although miniaturized mass spectrometers and other detectors are under development by NASA, the potential of such instrumentation to meet NASA needs will not be realized without complementary developments in the technology for collecting and
preparing samples for in situ measurements. Based on our analysis, we project that it will be possible to develop a miniaturized water pre-concentrator module with a mass on the order of 0.5 kg and an average power consumption of &lt;1 watt, depending on the configuration selected. Our
goal in the proposed SBIR Phase I effort is to demonstrate feasibility for such a system and to develop a detailed design for fabricating and demonstrating prototypes in Phase II.
The presence of  energetic ions, that appear under high cathode current operation, stand as a showstopper to the realization of high power electric propulsion.  Physical barriers such as the use of carbon electrodes (e.g. NEXT) are no longer sufficient as ion energies measured greatly exceed the sputter threshold of even carbon.  Unless this problem is addressed, the prospect of inadequate life looms. The benefits of high power electric propulsion missions supporting human operations in particular would be left unfulfilled.   

This effort aims to fully characterize the conditions under which energy ions occur by documenting ion energy spectra over a range of representative operating conditions.   At these conditions, the effort will implement two novel methods of essentially defeating the energetic ion production mechanism: 1) magnetic shorting and 2) gas injection.  While the concept of injecting gas to quench energetic ion production has been demonstrated in the past, we take the approach a step further by 1) elucidating the mechanism by which gas injection actually quenches energetic ion production and 2) implementing a novel gas applicator that would conserve propellant thereby allowing for gas implementation without a significant efficiency sacrifice.  Past studies have shown that energetic ions form under conditions of high current.  No satisfactory understanding of how these are formed or how to mitigate has been communicated. This effort aims to address both issues.   The focus of the proposed effort directly addresses a problem that stands in the critical path for the development of high power electric propulsion.  Without a solution to the energetic ion lifetime issue, it is difficult to imagine the actual implementation of high power electric propulsion for actual missions.  This proposed effort aims to generate a methodology and apparatus for the elimination of energy ions in high current cathodes.
Sample return missions, by nature, require high levels of spacecraft autonomy.  Developments in hardware avionics have led to more capable real-time onboard computing platforms, which allow for the implementation of more sophisticated algorithms.  A real-time convex optimizer named COARSE (Convex Optimizer for Asteroid Rendezvous and Sampling Return) is proposed in order to efficiently guide path planning operations as well as spacecraft guidance and control.  COARSE consists of a series of high level goals with specific set of execution steps, rather than complex interaction with ground control.  This proposal plans to develop and simulate a basic optimizer for the purpose of a robotic spacecraft in proximity operations to an asteroid for a sample return mission, and implement in a spacecraft avionics software environment.  If follow on Phase II work is awarded, the optimizer can be matured to expand higher levels of system complexity and constraints, potentially dealing with tasking multiple spacecraft working in coordination.
CU Aerospace proposes the ground test validation of a nanosat primary propulsion subsystem using non-toxic propellant with 3-axis ACS for orbit change and/or de-orbit capability, precision maneuvering, and drag makeup. Our approach, called the CubeSat High Impulse Propulsion System (CHIPS), leverages the existing Micro Propulsion System (MiPS) thruster technology development by our team partner VACCO Industries and enhances it with the CU Aerospace very high efficiency warm gas variant of an innovative resistojet that significantly boosts the performance of standard cold-gas systems. The MiPS system has been tested to 200,000 cycles without any technical issues, demonstrating excellent reliability. The 1.5U CHIPS subsystem, using non-toxic proprietary EP-76 propellant, is a compact thruster system having a total impulse of 602 N-s and a fully throttleable thrust of 50 mN. The subsystem also includes an EP-76 3-axis cold-gas attitude control system.  Approximately 25 W of primary power is required from a battery included in the 1.5U package. The value of this technology is that this low cost subsystem demonstration will pioneer a family of nanosat propulsion systems, based upon an innovative warm gas system and propellant, which will become available to the CubeSat and nanosatellite community for a broad range of propulsion needs.
NASA's future science missions to investigate the structure and evolution of the universe require efficient, very low temperature coolers for low noise detector systems.  We propose to develop a highly efficient, lightweight Active Magnetic Regenerative Refrigeration (AMRR) system that can continuously provide remote/distributed cooling at temperatures of about 2 K with a heat sink at about 15 K.  The AMRR system uses three novel design features to achieve a large cooling capacity and very high thermal efficiency: a vibration-free, reversible cryogenic circulator; innovative micromachined regenerators; and lightweight superconducting magnets.  The superconducting magnet uses low-current superconducting YBCO tapes and a unique winding arrangement to enable an AMRR to achieve high thermal efficiency. In Phase I, we will develop a design for the superconducting magnet and its electrical, thermal, and structural support subsystems.  Based on the performance characteristics of the magnet system, we will optimize the magnetic field in the AMRR to minimize the overall system size and mass.  In Phase II, we will build a superconducting magnet and demonstrate the performance of a magnetic regenerator driven by this magnet under prototypical conditions.  In Phase III, we will assemble an integrated AMRR system and demonstrate its performance.
The most promising propellant subcooling  systems for LH2 require compression systems that involve development of significant head.  The inlet pressure for these systems is typically on the order of 1.4 psia with a discharge pressure requirement above atmospheric pressure.  In the past this has required multiple stages of compression by machines operating at high speeds on ball bearings.  The bearing life in these machines was at most a few hundred hours.  While this is feasible to use for a proof of concept test system, it is not acceptable for the H2 compressors in application at the launch pad.  It is desired to replace these grease-packed ball bearings with foil bearings to greatly increase compressor life.  Additionally higher speed can eliminate several stages thus reducing complexity and cost of the system.  If this technology proves feasible it could finally make densified LH2 propellant a reality for future launch and space applications.
Methods to reduce the turbulent viscous skin friction stand out as paramount to increasing the energy efficiency, and therefore the aerodynamic efficiency of supersonic aircraft. Eagle Harbor Technology (EHT) proposes to develop and optimize a MHD plasma injector, which will be used to efficiently reduce the viscous skin friction in supersonic aircraft.  EHT has developed similar MHD plasma injection technologies, which have been applied to a number of different fusion energy science, aerospace thruster, and basic research investigations. Here, we aim to computationally investigate and verify the dominant physical mechanisms for MHD plasma drag reduction; develop a proof of concept plasma injector demo, which conforms to necessary power and efficiency requirements for an onboard flight-relevant system; and use insights gained through our computational investigations to optimize the performance of our MHD plasma injector for maximum aerodynamic efficiency. This investigation will focus on flight-relevant Reynolds and magnetic Reynolds numbers at low supersonic (M&lt;~3) speeds. Phase II research will couple the plasma injector to a scale model airframe for detailed in-situ supersonic wind tunnel testing. The phase II research will produce a fully realized working plasma injector prototype that conform to power requirements of an on-board power system.
Speaking to the cockpit as a method of system management in flight can become an effective interaction method, since voice communication is very efficient. Automated Speech Recognition in general, and aided and abetted now by Southern Air Aviation's Voice Activated Cockpit Management Systems including the innovative heuristic technology Voice-Flight NexGen (VFNG) has advanced significantly in recent years and is now ideally suited to this application.  VFNG is speaker-independent, achieves a word recognition rate of 98&#37; in high noise and up to 120Db, and permits the chaining of up to four commands in a single utterance and a correction of a misspoken command in the same utterance.  All of these performance requirements are met within a 2&#37; time-slice of a 1.2GHz Power PC processor and within 1 GB of memory.  VFNG includes the following unique key capabilities, Grammar Development, Dictionary Development, Automated Batch Grammar Testing, Grammar Coverage Query, Phonetic Distance Analysis, and Co&amp;#8208;articulation Handling, Command Based Confidence Algorithm, Accent Tolerability Handling, State Based Dynamic Grammar, and Clipped Audio Recovery Processing.  VFNG incorporates proprietary Julius based grammar and vocabulary of advanced performance and reduced recognition error together with an acoustic model derived from the VoxForge acoustic model.  The VFNG-Emergency Failures (VFNG-E) system is used as the sole human/machine interface in flight in real emergency situations, in addition to the system having applications for simulator and ground training. This training system is remarkable in that it achieves very high recognition rates (98&#37;) with a very large command set (131,000 unique words and thousands of word combinations) in challenging environmental conditions and operator profiles providing much added safety and efficiency to the pilot in the cockpit.
The team of Prime Photonics, Virginia Tech, and Utron Kinetics propose to develop a fabrication technology that will result in drop-in replacements for a diminishing supply of NASA fluxgate magnetometer ring cores.  Specifically, we plan to capitalize on trends observed during the Phase I effort in terms of control over material properties in bulk, cobalt-rich metallic glass materials with increased permeability, tunable Curie temperature, highly controlled coercivity and saturation inductance, all without the introduction of magnetostrictive-based excess noise. The bulk nature of the material will provide an unprecedented degree of freedom in core geometry design over existing ribbon-form amorphous alloys, allowing for net shape, drop-in fluxgate cores that can compete with, or exceed noise levels observed in the 6-81.3 permalloy family.  The Phase I effort brought the technology from observed trends in materials, a TRL of 1, to a level wherein analytical obersevations and proofs of concept have been carried out, a TRL of 3.  During the Phase II effort, we projection a minimum TRL of 4 at the completion of the effort.
Aurora will develop a novel composite sandwich structure that is capable of providing a coupled bending-torsional stiffness with nonlinear elastic effects, capable of achieving a tailored aeroelastic response over a wide range of flight conditions.  Such a structure will make use of an additive manufactured core with highly tailored and optimized cellular substructure. The cellular structure will be functionally graded in the spanwise and chordwise directions to provide a coupled bending-torsional stiffness response.  Fiber reinforced composite facesheets will provide strength. Utilizing the core structure to couple the bending-torsional stiffness of the composite may allow the composite to remain balanced and symmetric, thus avoiding induced stresses and/or warping during manufacturing.
MicroLink and its subcontractor Magnolia Solar will develop and demonstrate advanced anti-reflection coating (ARC) designs that will provide a better broadband and angular response than that of current coatings.  Advanced coatings of this nature are needed to realize the full potential forthcoming generation of multi-junction solar cells that will contain four or more junctions.  We will undertake several approaches to this problem:

* investigate new dielectric materials that will allow a refractive index intermediate between those of the materials that are currently in common use as ARCs; 
* investigate a dielectric codeposition processes that will allow the fabrication of materials with a wide range of refractive indices; and 
* investigate oxidation of Al-containing III-V semiconductor compounds as a mechanism for forming a more transparent window layer.  

Based on the results of these investigations, we will fabricate and test on III-V triple-junction solar cells the best-identified candidates for improved anti-reflection coating.  If successful, the new coating designs will have a reflectance less than 5&#37; over the spectral range 300 nm to 1800 nm and over a wide range of incident angles.  The coatings will be completely compatible with inverted metamorphic (IMM) multi-junction solar cell technology and will be optically matched to IMM solar cells.  We expect the new coatings will enable a relative efficiency increase of at least 7&#37;, corresponding to a 2.5&#37; absolute efficiency increase.
The National Research Council (NRC) has identified the need for motors and actuators that can operate in extreme high and low temperature environments as a technical gap to exploring deeper into our solar systems.  The need for high temperature motors and actuators for robotic mechanisms is critical to explore the surface and atmosphere of Venus, Jupiter and/or Saturn.  

Bear Technologies, LLC (Bear) proposes to create environmentally tolerant motors for robotic missions.  As identified by NRC and NASA there are no commercial actuators or motors that can work in wide variation and high temperature environments (-50 degrees Centigrade to 500 degrees Centigrade).  The current approach has been to shield or isolate the environment from these systems. The problem with this approach is that it limits the ability to explore on surface, increases the bulk and is expensive with temperature control systems.  The need is to create tolerant technologies that can operate in the extreme environment. 

Bear Technologies has been exploring motor design for more than 5 years.  Currently, Bear is working on a high torque direct drive electric motor under a Phase II award.   The concept proposed uses new design concepts coupled with tolerant material to create a temperature tolerant motor (TTM). The proposed motor concept has a fundamentally different design that offers offers higher torque and lower speed than traditional motor design.  This novel design will help minimize failure risks at extreme temperatures.  By combining certain extreme temperature materials with no ball bearing or lubrication, the Principle Investigator (PI) believes the motor concept has the potential to function for an increased period of time in extreme environments. Motor and actuator technologies that are capable of operating in the high-temperature (460 degrees C) and high-pressure (90 bars) Venus surface environment are needed for multiple robotic systems.
Hybrid-Electric distributed propulsion (HEDP) is becoming widely accepted and new tools will be required for future development with validation and demonstrations during ground and eventually flight testing.  To monitor the overall HEDP system health in real time, a virtual requirement to flight qualify any architecture hardware components, reliability centered maintenance (RCM) applied to prognostics and health management (PHM) will yield significant improvement in HEDP system reliability, availability, safety and cost.  This work will identify the tools and create a generic methodology for the PHM of a HEDP system based on RCM and failure mode data of likely HEDP architecture components.  The proposed work will notionally design a PHM system into a HEDP system architecture, with feedback systems from each component within the stated architecture, as well as potential mitigation strategies for component failure modes.  Specific attention will be applied to understanding of the reliability, availability, and safety for the HEDP components.  Heating, arching, unexpected voltage drop, and other potential electronic pitfalls will be identified and mitigated.  ESAero will leverage their component databases, experience with HEDP component architectures, aircraft design, and vendor relationships while General Atomics (GA) will provide expertise in PHM with their HealthMap software.
The objective of this project is to demonstrate the feasibility of a miniature, MEMS IMU based, accurate isolation and stabilization system for beam pointing of a laser designator. Inertial stabilization and relative attitude control are the two key elements constituting the proposed accurate pointing control. Inertial stabilization allows isolation from interference and vibration. Relative attitude control is used for target tracking and to compensate pointing drift caused by gyro drift and the Earth's rotation. In Phase I of this project, first, using the simulation tools and experimental systems of AGNC, modeling and implementation evaluation of the proposed MEMS-based inertial pointing system are performed. Through the modeling and simulation of the closed loop system, the implementation method and the specification of the MEMS devices and pointing system will be further investigated. Then, an inertial motion measurement device test and tuning are performed. MEMS gyros for pointing stabilization are integrated into the platform structure. Next, system integration of the MEMS stabilization platform is investigated. An accuracy evaluation of the pointing stabilization system is performed. Finally, the mechanical structure of the stabilization platform and the integration of the MEMS with the system's mechanical and electronic components is proposed and investigated.
Historically, radar systems have tended to be either large, complex, power-hungry, purpose-built systems, or extremely simple systems of limited capability. More recently, miniaturization of high-performance programmable integrated circuit technologies as embodied in field-programmable gate arrays (FPGAs), as well as rapid advances in high-speed data conversion technologies at a gigasample per second and beyond, have enabled the implementation of direct-conversion radio frequency (RF) systems, including radar, that operate almost completely in the digital domain. In addition, solid-state high-power RF device technologies have improved in efficiency and speed to the point where highly efficient pulsed transmit sources are possible. As these device technologies have matured, their application in space environments has accelerated to the point where extremely flexible programmable radar systems can be implemented in a very small size, weight, and power footprint. Trident Systems has developed a powerful radar architecture called RAPTOR, validating it through flight testing on a number of Department of Defense programs. In Phase I of this effort, Trident Systems developed and validated a design concept for a flexible, programmable space-qualifiable digital radar transceiver (SQDRT) based on RAPTOR.  This was accomplished through a comprehensive development process consisting of mission and requirements analysis, component trade studies, design analysis and simulation, and interface &amp; form factor trade studies.  The objective of the Phase II effort is to successfully produce a functioning form-factor prototype of the SQDRT, through a comprehensive program of system modeling and simulation, detailed digital &amp; RF electronic design, FPGA firmware development, mechanical design, fabrication, integration, and testing, culminating in a prototype demonstration.  By basing the solution on proven RAPTOR technology, the system will rapidly achieve a high TRL.
The proposed innovation is a propulsion technology that will help achieve NASA's Fundamental Aeronautics Program (FAP) goals of reducing emissions and increasing fuel efficiency for high speed flight.  NASA's objective to achieve increase the specific power of high efficiency electric components to make a 10 mega-watt onboard power generation and/or utilization feasible for propulsion requires the development of sub-scale technologies to support the development and validation of newer turbo-electric aircraft and embedded boundary layer electric propulsion systems.  Compact and lightweight generators scaling from the kW to MW class are needed to transition high speed aircraft to hybrid electric propulsion systems. Metis Design Corp is developing a lightweight, small-scale, gas turbine generator that draws on recent innovations in the fields of permanent magnet generators and turbomachinery, which has a target power density over twice the state-of-the-art and the potential to scale to 100's of kW.  The proposed turbine engine uses a lightweight, two-spool configuration that eliminates the need for the heavy reduction gearbox required by state-of-the-art systems.  Phase I of this SBIR will develop a preliminary design of the turbine generator sub-system and develop a detailed design, fabricate and test the innovative generator hardware.  A follow-on phase II effort will develop a detailed design, fabricate and test the complete turbine generator sub-system.
This proposal addresses NASA SBIR topic S1.07 In Situ Sensors for Lunar and Planetary Science, particularly the need for measuring isotopic ratios of the key elements associated with the signs of life (H, C, N, O). We propose a non-contact optical instrument similar to ChemCam that will be capable of measuring not only complete elemental compositions but also isotopic abundances of the key elements in surface materials. We intend to utilize and further develop our recently published technology: Laser Ablation Molecular Isotopic Spectrometry (LAMIS). Our concept is simple, scientifically proven and already endorsed by two innovation awards we received. In Phase I, we concentrate on demonstrating the resolution and sensitivity required to determine these isotopes in synthetic samples and natural minerals relevant to Mars. The immediate focus is on Mars but our concept is also highly germane to future landing missions to the Moon, other planets and their moons, asteroids, and to a broad range of applications in ecology, agronomy, nuclear industry, radio-chemotherapy, forensics, security and other fields. We will advance the development to TRL4 by the end of Phase II with the further aim of integrating our LAMIS detector with a ChemCam-like instrument. The proposed instrument leverages and advances the technology developed for ChemCam. The added strength of measuring isotopes will greatly expand the capabilities of the ChemCam, which is now the most frequently used instrument onboard "Curiosity." In Phase II, we will develop a breadboard prototype of the instrument that can be amended to measure other key isotopes (B, Cl, Mg, Ca, Sr, etc.). We plan further infusion in NASA missions and commercialization in Phases II-Ex and III. Our instrument can be used for stand-alone landing missions or for in situ sample characterization prior to sample return.
The technical innovation proposed here is the continued functional evolution and concept refinement of an incremental series of test vehicles that will ultimately provide dedicated, low-cost, reliable, on-demand routine space access for the emerging nano and micro satellite markets.  Initial orbital operational capability for delivering 10 kg to a 250 km circular LEO is achieved with a two-stage, pressure-fed "10/250" Nanosat Launch Vehicle (NLV) that will pathfind performance, production, regulatory and operational challenges.  This NLV will then be followed by a clustered "20/450" Nano/Micro Satellite Launch Vehicle (NMSLV) that addresses this topic's primary objective of providing a capability to place nano and micro satellites weighing up to 20 kg into 450 km circular LEO.
Aggressive leveraging of our team's existing NLV development initiative enables significant hardware development and the start of static fire testing during Phase I, followed by actual flight testing in Phase II for TRL-7 technology evaluations.  These tests have incrementally introduced state of the art capabilities like advanced propellants (LOX/propylene) and structures (composite cryogenic tanks).  The Phase I effort focuses on the development of the next class of test vehicle &amp;#150; a high altitude suborbital single booster stage (the "P-K") that features closed-loop thrust vector control (TVC) and candidate avionics technologies for guidance and navigation, as well as eventual autonomous flight termination systems (AFTS) for range safety, TRDRSS-based telemetry and tracking functions.  In addition, it will incorporate features needed to implement the clustered first stage configuration and second stage separation method associated with the 20/450 NMSLV. The Phase II effort will then focus on the further development of an NMSLV-type first stage with two additional  core boosters, for a total of three, and the conducting of a high-altitude demonstration flight.
Space Micro proposes to develop a radiation hardened, monolithic, heterogeneous processor for space imaging and radar systems.  High performance processors are needed because many space systems generate copious amounts of sensor data at high data rates. The extraction of information from such data streams requires high speed data reduction. Parallel processing may be required to keep pace with the data stream, and that processing often requires application of sophisticated digital filtering or compression algorithms. The results of the signal processing then require aggregation and additional processing to produce actionable information to be used either on the satellite or downloaded to the mission controller.
The proposed Phase I investigation will focus on the development of spacecraft systems required to obtain a sample from the nucleus of a comet, hermetically seal the sample within a capsule, and return the sealed sample to an orbiting spacecraft which can return the sample to Earth. A preliminary systems level concept has been developed. This concept will be refined during the proposed Phase I investigation, including proof-of-concept breadboards and analyses of critical subsystems.
SVT Associates proposes an novel type II superlattice structure to extend the cutoff wavelength and CBIRD SL photo diode structure with unipolar barriers to suppress dark current of SL detectors grown on GaSb substrate. This InAs/GaSb superlattice material system is capable of infrared detection in MWIR/LWIR spectral range, depending on layer thickness of each superlattice period. The goal of this program is to develop high performance type II SL based FPA for 5-14 um detection. Photodetector arrays using this material are of great interest to the NASA for various applications including, in particular, imaging and optical detection, and object discrimination when tracking targets in space or performing astronomical observations. These LWIR photo detectors can also find application to infrared-based chemical identification systems and terrestrial mapping. Applying the dark current suppression and cutoff wavelength extension process to the type-II superlattice detectors should result in higher operating temperature, extended cutoff wavelength, and improved quantum efficiency, all important factors that should significantly enhance FPA operation.  We intend to characterize the positive effects of proposed techniques in Phase I.  In Phase II we will refine the techniques to realize passive-cooled high-performance LWIR FPAs with quantum efficiency larger than 60&#37;.
ORBITEC proposes to develop and demonstrate an Integrated Composite Rocket Nozzle Extension (ICRNE) for use in rocket thrust chambers. The ICRNE will utilize an innovative bonding approach to join a high-temperature composite nozzle extension to a regeneratively cooled metallic nozzle. The ICRNE technology will allow high-temperature composite materials to be directly integrated into a regeneratively-cooled nozzle section or thrust chamber made out of high-strength metallic alloys, thereby eliminating the heavy bolted flange joint that is currently used to attach high-temperature nozzle extensions. The resulting weight reduction will increase the thrust-to-weight ratio of the rocket engine. The ICRNE will also eliminate the need for multiple seals in the bolted flange joints, thus increasing reliability. The focus of the proposed Phase 1 effort will be to demonstrate the ICRNE technology by manufacturing and evaluating test specimens. A prototype ICRNE will also be designed and analyzed. In Phase 2, a prototype ICRNE unit will be fabricated, installed, and hot fire tested on an existing rocket engine. This proposal responds to Subtopic H2.02 In-Space Propulsion Systems, specifically "high temperature materials, coatings and/or ablatives or injectors, combustion chambers, nozzles, and nozzle extensions" for non-toxic, cryogenic, and nuclear thermal propulsion systems.
Area-I, Incorporated personnel have led the design, fabrication, and flight testing of twelve unmanned aircraft and one manned aircraft. Partnered with NASA and Boeing, Area-I has developed the unmanned Prototype-Technology Evaluator and Research Aircraft or PTERA ("ptera" being Greek for wing/wing-like). The PTERA, a high-quality flight research testbed, bridges the gap between wind tunnel and manned flight testing with low-cost, low-risk flight-based evaluation of high-risk technologies. In Phase I, the PTERA was enhanced by integrating modularity and design flexibility and culminated in the design of a representative 16&#37;-scale CRJ-700, named the PTERA-RJM for Regional Jet Model.  For Phase II, the team proposes to finalize the design, fabricate, and deliver a 17ft, 278lb PTERA-RJM that is tailored for use within NASA's Aviation Safety Program to enable experiments in vehicle health monitoring, in loss of control prevention, mitigation, and recovery, in atmospheric hazard sensing and mitigation, etc.  
The Boeing Company supports the proposed work, as they have great interest in the PTERA platform given its following core capabilities:
1)	A large, low-cost airframe that minimizes scaling and Reynolds number effects, yet is easily disassembled and transported
2)	A modular, reconfigurable fuselage design that enables the fabrication and assembly of fuselage configurations that maintain near geometric similitude with a wide array of "tube-and-wing" aircraft using existing tooling
3)	Modular wing design that facilitates the integration of advanced aerodynamic treatments, split control surfaces, and aeroelastic and damage emulation mechanisms
4)	Integrated ballast system and movable payload/avionics racks to enable the tuning of mass/inertial properties
5)	Large payload capacity, voluminous payload bays, and large clamshell doors that facilitate the integration of avionics systems and provide access during flight testing
It is often difficult to create autonomous robotic capabilities that match what can be achieved via teleoperation. Even though it is mechanically possible for a humanoid robot such as Robonaut 2 to perform complex coordinated tasks such as tying a knot, exchanging objects between end effectors, plugging in connectors, unscrewing a cap, opening a door, or grasping large objects with two hands, our lack of planning algorithms makes it difficult to control these behaviors autonomously. The lack of planning and control algorithms also impedes human-robot interaction as it is difficult for manipulation robots to plan arm trajectories in real-time using active sensing to avoid collisions with humans. This proposal is to develop a suite of planning and control algorithms that will enable NASA robots to perform complex manipulation behaviors in a coordinated way. This work would benefit NASA by making NASA robots more capable and useful during autonomous tasks, by enabling remote supervisors to command more complex tasks, and by enabling NASA robots to operate safely alongside humans during shared tasks.
The ability to integrate a sensor platform with a cell phone for health monitoring and disease diagnosis for astronauts in space has the potential to be cost effective and space saving. In this proposal, Intelligent Optical Systems (IOS) builds upon its expertise in lateral flow test strip (LFTS) assays by integrating an LFTS with a cell phone for the quantitative measurement of blood-based biomarkers. Our innovative and extremely cost-effective multi-analyte LFTS approach is eminently suited for space travel. Taking advantage of the built-in flash and high resolution camera, in Phase I we have modified a commercially available cell phone with optical filters, lenses, a UV LED excitation source, and a cassette holder for LFTS image capture. In Phase II, we will expand the capability of cell phone-based LFTS for an antibody-antigen sandwich binding assay to include blood gas measurements by developing sensitive indicator films to be integrated with our cell phone-based detector. Furthermore, we will develop cell phone-based software for on-cell phone detection and data processing with an expanded panel of biomarkers, advancing the TRL from 5 to 7.
Deployable Space Systems, Inc. (DSS) will focus the proposed SBIR program on the creation and development of an automated robotic manufacturing infrastructure designed to mass-produce DSS's Integrated Modular Blanket Assembly (IMBA) common photovoltaic Standard Power Modules (SPM's). The proposed development will implement automated manufacturing processes for CIC-ing, glassing, stringing, laydown, and acceptance testing of interconnected photovoltaic devices onto an ultra-lightweight IMBA/SPM modular flexible blanket assembly through simple and commercially available pick-and-place robotic manufacturing techniques / infrastructure. Automated manufacturing of IMBA/SPM photovoltaic panel assemblies will provide an industry paradigm shift for affordability / cost-savings when compared to current labor intensive manufacturing processes.  Unlike the current industry approach which is only focused on increasing the device area that only minimally reduces panel assembly costs, the proposed automated manufacturing will attack the highest cost and most labor intensive components of manufacturing a panel assembly, namely; CICing, glassing, stringing, panel laydown, and acceptance testing.   By incorporating automated manufacturing the proposed IMBA/SPM photovoltaic flexible blanket assembly promises to provide ultra-affordable high-performance and repeatable high-quality modules for future NASA Space Science and Exploration missions, and particularly for ultra-high-power SEP missions.
QuinStar Technology proposes to develop a 4-watt Solid-State Power Amplifier (SSPA) operating at F-band (106-114 GHz) with a power-added efficiency (PAE) of greater than 30&#37;. This will be achieved by employing two major innovations. First, we are employing state-of-the-art wide bandgap GaN (Gallium Nitride) devices. High power density GaN devices have recently been demonstrated at millimeter-wave frequencies with power densities of 5 to 8 times higher than GaAs and drain efficiencies of 50&#37;. Using these devices in a quasi-switching mode, we are proposing to develop a new high-efficiency MMIC operating at F-band with an output power of one watt and an efficiency of greater than 33&#37;. Secondly, we are proposing to utilize a new low loss, H-tee combining approach to combine 4 of these high-efficiency chips to achieve 4 watts. The net result is a unique combination of high performance devices and innovative power combining. We anticipate that this work will result in an order of magnitude increase in the state-of-the-art of SSPA output power and efficiency at F-band. As a result, we believe this work could be very important for NASA's Astrophysics and Earth Science missions and for W-band radar and communications applications.
The innovation is a compact, reliable, light weight, electrically driven pump capable of pumping cryogenic liquids, based on scroll pump technology.  This pump will fulfill several needs stated in SBIR Research Topic, H2.01: Cryogenic Fluid Management Technologies. Zero gravity cryogenic control devices (spray bars and mixers), require cryogenic liquids to be pumped efficiently. Propellant conditioning and densification technologies require compact, efficient pumps. Broad area cooling of cryopropellant shields can be facilitated by the pumping of a cold gas such as helium in a loop from a cryocooler to a shield. Various methods of liquefaction of oxygen such as passive radiative cooling can be enabled by cryogenic pumping. Other aerospace applications such as a fuel pump for liquid hydrogen fueled aircraft.  A compact, reliable, and light weight pump for cryogenic liquids currently does not exist.  Our subcontractor, Ball Aerospace and Technologies, has identified the need for such a pump several years ago, but has not found a suitable available product.

Scroll pumps have several advantages over other pump technology, including being compact, light weight, reliable and efficient.  The pump can be hermetically isolated from the drive motor by the use of a magnetic coupler, allowing the pump to be hermetically sealed. Because of the orbital motion, the scrolls can be placed in a metal bellows that are sealed to the housing which isolates the liquid via a vacuum enclosure for thermal isolation. The bearings can be placed on thermally isolating arms, so they do not need to operate at cryogenic temperatures.

Scroll pumps have considerable technical heritage relevant to this application. Air Squared has developed and successfully tested scroll pumps for liquids and for cryogenic gasses. Air Squared has developed several compact pumps for pumping air which has similar viscosity and compressibility to liquid hydrogen.
The proposed work focuses on implementing fast-response pressure-sensitive paint for measurements of unsteady pressure in rotorcraft applications. Significant rotorcraft problems such as dynamic stall, rotor blade loads in forward flight, and blade-vortex interaction all have significant unsteady pressure oscillations that must be resolved in order to understand the underlying physics. Installation of pressure transducers is difficult and expensive on rotorcraft models, and the resulting data has limited spatial resolution. Application of a fast-responding pressure-sensitive paint should provide unsteady surface pressure distributed over the blade surface. Fast PSP measurements have been demonstrated at NASA Langley on a 2-meter rotor model in hover and in forward flight by the ISSI/OSU team using two single camera systems. More recently, measurements were conducted in forward flight using multiple cameras and lasers at two azimuthal positions. We propose expanding this system for production testing. This will be accomplished by adding remote control of the system interrogation region using remote focus/zoom/aperture lenses and pan/tilt stages combined with Ethernet hardware to control the systems remotely. Motion blur will be addressed using both a rotating mirror and de-convolution software. Data processing software will be customized to allow scripting of repetitive operations to speed up data processing. Finally, a temperature measurement capability will be added to the system to allow temperature corrections to be applied to the PSP data. These modifications to the system will improve accuracy and productivity during testing.
The successful landing of the large Mars rover Curiosity on August 5, 2012 outlined the increasing complexity of safely landing large rovers on the planet. A precise knowledge of the spacecraft speed is required in order to initiate the landing sequence near 900 mph; the present method uses IMUs to determine the position and speed of the craft, which is prone to drift and highly sensitive to initial conditions. The proposed MArs VelocitY sensor (MARVY) is a short range air data sensor based on direct, or incoherent, detection of light scattered by both molecules and aerosols. The instrument operates in the presence or absence of aerosols, thus enabling operation in completely clear atmosphere.  The MARVY design will be based on micro-fabricated optical components to provide an instrument that affords all requirements for planetary exploration. This Phase I will entail modeling and design of the instrument. Critical components will be tested in Phase II.
Solar Electric Propulsion drives down the cost of space missions by using its high propulsion efficiency to step down from one launch class to another.  As launch costs can be up to a third of total mission costs, stepping down to a smaller rocket can be a mission enabling technology in today's budget constrained environment.  

While missions such as Dawn have used this to visit multiple asteroids after launch from a small launch vehicle, ExoTerra's SolRider Direct Drive (DD) SEP module allows interplanetary missions to take the next step down in launch cost to package within standard rideshare envelope and mass contraints.  Our module integrates multiple technologies to provide up to 8.6 km/s within an Atlas Aft Bulkhead Carrier rideshare or 14.6 km/s of delta-V within a standard ESPA.  This can enable launch costs below $5M.

Our integrated DD SEP module uses a combination of SEP technologies to create a highly efficient system to package within the rideshare envelope. We use a 175 W/kg and 60kW/m3 rolled composite tube solar array deployment system to package within the tight volume.  This provides 300 V power to the thruster through a direct drive system, eliminating the cost, mass and electrical losses of the traditional power processing unit. A Hall Thruster uses the high voltage power to efficiently propel the craft with over 1600 s of Isp.  The thruster receives the propellant from a cryogenic Xenon feed system, allowing an order of magnitude drop in tank mass.  When coupled to Microsatellite electronics, the system can deliver up to 5.5 kg of payload instruments to Mars orbit.
Global Technology Connection, Inc. in conjunction with its partner, Vanderbilt University, is proposing to build a Fusion-enhanced Vehicle Diagnostics System (FVDS) framework to combine various information to help make go/no-go decisions from a safety point of view.  Specifically single vehicle will be pursued by looking at each aircraft as a single entity.  The system will ensure that the aircraft will make the next maintenance interval by catching errors in the shop and/or detecting emerging problems to maintain vehicle safety between major inspection intervals with an emphasis on the subsystems of airframe, avionics, and propulsion.  The system will provide condition indicators, using model-based or data-driven approaches, from a subsystems' or components' point of view, and these will be fused, using the hybrid modeling based on Bayesian theory and/or graph theory, to provide overall safety from a system point of view.   

FVDS approach consists of a multi-level processing architecture that includes three levels of reasoners: 
1. Individual Components and Line Replaceable Units that provide BIT test, sensor measurements and control commands to track the behavior of the particular component, and report faulty and abnormal conditions; 
2. Subsystem reasoners to monitor the state of health of the airframe subsystem; and
3. System or Vehicle level reasoner to combine diagnostic and prognostic information from the individual subsystems, puts them on a time line, and also analyzes cascades of faults.
Deployable Space Systems, Inc. (DSS), in partnership with Mark O'Neill LLC (MOLLC) will focus the proposed NASA Phase 1 effort on the development of our innovative SOLAROSA technology.  SOLAROSA, named for Stretched Optical Lens Architecture on Roll-Out Solar Array, is a new lightweight, high performance space solar array that enables missions through low cost, lightweight, compact stowage volume, radiation hardness, high voltage capability, scalability to ultra-high power, and LILT/HIHT environment operability.  SOLAROSA is a fusion of ENTECH's proven Stretched Lens Array (SLA) concentrator technology with DSS's innovative ultra-lightweight Roll-Out Solar Array deployable structural platform.  The proposed Phase 1 program is uniquely focused on SOLAROSA development that provides multi-A.U. operability and large beta axis off-pointing operational capability.  SOLAROSA promises to provide NASA/industry a near-term and low-risk solar array system that provides revolutionary performance in terms of high specific power (&gt;400-500 W/kg BOL at wing level), affordability (&gt;50&#37; projected cost savings at the array level), lightweight, high deployed stiffness, high deployed strength, compact stowage volume (&gt;60-80 kW/m3 BOL), reliability, high radiation tolerance, high voltage operation capability, scalability, and LILT &amp; HIHT operation capability (LILT &amp;#150; Low Intensity Low Temperature, HIHT &amp;#150; High Intensity High Temperature).
A high performance, inexpensive, airborne simulator that will serve as the prototype for a small satellite based imaging system capable of mapping thermal anomalies on the surface of the earth with a high revisit rate and high spatial resolution is proposed. The Thermal Mapping Airborne Simulator for Small Satellite Sensor (TMAS) will be developed to a TRL 8 in the Phase II and the space-qualified system will be developed and built in Phase III. The proposed system will deliver high spatial resolution (133 urad), high signal to noise performance, three spectral bands, and onboard processing to extract the information of greatest value, orthorectify the imagery, and reduce the size of the data for transmission. This sensor system is designed to fit within the size, weight, and power (SWaP) envelopes of typical remote sensing aircraft and small satellites. The proposed design incorporates a step stare scanning mirror, a two band (LWIR 8 to 9 um and MWIR 4 &amp;#150; 5 um) Quantum Well Infrared Photodetector (QWIP), a short wave IR sensor (1.6 um), and an FPGA based image processing and orthorectification processing module.
DyMA-FM (Dynamic Multivariate Assessment for Fault Management) is a software architecture for real-time fault management. Designed to run in a distributed environment, DyMA-FM enables model-based reasoning and predictive modeling for FM applications. With the appropriate hardware, DyMA-FM can respond to signals at the device level while still placing each signals in context with the larger system and the overall mission objective. This functionality is enabled by a layered software architecture and decision-making hierarchy where each level receives signals from the level below and context from the level above. The contextual processing reduces false alarms and increases fault coverage. The distributed architecture, meanwhile, speeds processing time and reduces the burden on the communication system, enabling faster and more robust response to fault conditions. 

Building on our current and past experience with distributed system management and mathematical modeling, we will implement and test a prototype of the proposed software. Test data will be provided by Boeing Corporation and will consist of a representative set of signals from an actual spacecraft, collected either under actual use conditions or during a system test. Implementation will require the development of mathematical models that represent the relationships between the test signals, and this portion of the Phase I tasks will result in an analysis of the model's ability to support fault detection and management. Testing will focus on the software's fault coverage, the speed of the system responses, and the system's sensitivity to timing issues such as message lag and message collision. Results from initial tests will be reviewed, and suggested changes to the software will be documented. 

The final output from the project will include the system prototype, test results, and an analysis of the DyMA-FM's ability to produce superior fault coverage.
NASA space missions utilizing application-specific integrated circuits (ASICs) under extreme conditions have a critical need for high performance analog cell libraries to support the mission requirements. With the introduction of silicon germanium (SiGe) processes, there is an opportunity to provide resilient analog circuit designs that handle both temperature and radiation hardening requirements. Our experience has indicated that meeting extreme temperature requirements is as challenging as meeting the radiation-hardening requirements and innovation in this area is warranted. Maintaining key operating specifications such as linearity and dynamic range while under both extreme temperature and radiation exposure conditions is a difficult problem requiring an innovative solution.
Ridgetop Group will build a cell library of key "building block" analog cells needed for pipeline, flash and successive approximation register (SAR) ADCs; and capacitor array DACs. We will develop transistor-level designs and simulate these blocks to prove feasibility and demonstrate the effectiveness of the minimal temperature response (MTR) design techniques. After achieving desired MTR, rad-hard by design (RHBD) methods will be employed to meet the radiation specs. In Phase 2 of this SBIR program Ridgetop will fabricate and test a 12-bit ADC based on this library to validate its efficacy.
Aerospace structures are often subjected to a broad spectrum of mechanical and/or aerodynamic excitations and, therefore, there is a real need for the development of a modeling technique which can be used for the vibroacoustic analysis, with high fidelity and adequate spatial and spectral resolutions, of complex systems over the entire frequency range. A dynamic system typically exhibits distinctively different response characteristics as frequency increases. In recognizing the complicated behavior of a structure, the modeling methods in dynamic analysis are usually classified into low, mid, and high frequency models.  A substructure-based modeling technique, based on enhanced Fourier Spectral Element Method (FSEM), that is applicable all frequencies, is proposed for the modeling of complex dynamic systems. This method also does not require meshing as is traditionally used in discretization methods such as finite and boundary element methods.
In this proposal, Tyvak Nano-Satellite Systems LLC (Tyvak) will develop nano-launch vehicle avionics solutions based on the latest commercial electronics products and protocols. These systems will address the unique avionic challenges of dedicated NanoSatellite launch vehicles (NLV). Tyvak will utilized heritage and lessons learned from its CubeSat avionic systems to modify and optimize its current products for use with this new class of launch vehicles. The major technical objectives will be:

- Provide compatibility with the all NLV systems in development

- Determine and provide appropriate performance and reliability metrics while maintaining the low-cost/low-mass made possible by commercial electronics systems

- Determine the feasibility of the latest network protocols (in particular wireless systems) in the NLV environment

- Demonstrate the reliability of low-cost/low-mass/low-power GPS based automatic flight termination system (AFTS) by combining the latest generation of commercial miniature GPS systems with high performance computer systems based on mobile computer technology
The increasing frequency of International Space Station (ISS) egress operations results in chemical contamination of the spacecraft environment.  Among the most important contaminants are propellant residues (such as hydrazine) and their decomposition by-products, as well as coolants such as ammonia and Freon.  Ammonia has a 24 hour Spacecraft Maximum Allowable Concentration (SMAC) of 7 ppm (Perry, 2010) and hydrazine has a 24 hour SMAC of 0.3 ppm (NASA/JSC 20584, March, 2001).  These highly alkaline chemicals rapidly penetrate skin and coagulate proteins.  Furthermore, a hydrazine fuel leak onto any hot surfaces may cause fire.  

TDA Research Inc. proposes to develop a new adsorbent that can remove these contaminants to sub ppmv concentrations.  In the Phase I, we will develop the adsorbent media and design a cartridge that will be incorporated into a first response crew mask.  We will demonstrate the efficacy of the cartridge in removing these contaminants at full-scale in an environmental chamber (TRL 4).  We will also complete the detailed design of a general purpose first response mask, including additional adsorbents and ambient temperature oxidation catalyst that will provide complete protection against all contaminants (in addition to NH3 and hydrazine, CO, volatile organic compounds and combustion by-products, such as sulfur oxides will all be removed).  In Phase II, we will work with Gentex, a leading supplier of personal protection systems in fabricating the mask and cartridges. We will complete high fidelity demonstrations in an environmental chamber to fully demonstrate its capability (non-human testing at TRL 6).
In this STTR Phase 1 program, Fibertek successfully developed and demonstrated a breadboard version of a pulsed fiber laser capable of high-spectral resolution lidar (HSRL) measurements. This was installed in the Lidar Lab. at the Univ. of Maryland, Baltimore county (UMBC). Lidar integration, calibration and validation was successfully performed, leading to the demonstration of direct backscatter measurements up to 10km atmospheric height, and HSRL measurement of the atmospheric boundary layer aerosol. Such measurements compared very well to the co-located lidar measurements conducted via the ELF and MPLNET lidar systems. 

For the STTR Phase 2 program, Fibertek and UMBC propose to mature this technology platform, to develop, test, deliver and demonstrate a completed standalone HSRL lidar system capable continuos lidar measurement. The HSRL lidar transmitter sub-system can be also used for airborne HSRL missions, and the design is both power-scalable and compatible with a qualification roadmap, for future space-based HSRL missions.
We propose to design, build, and test a two-stage waste processing reactor for space applications. Our proposed technology converts waste from space missions into hydrogen, water, carbon monoxide, carbon dioxide that can be used for energy production and/or life support. This innovative reactor technology employs a pyrolysis reactor as the first step, followed by a chemical looping gasification reactor as the second step. The two-stage process is more suitable than the traditional one-step gasification process, because solid residues associated with the waste, such as ash and tar, are contained in the pyrolysis unit. The utilization of metal oxides that can be readily obtained at the site of exploration as an oxidizer in the gasification (second) step instead of traditional oxidizers such as oxygen or steam further saves the valuable resources that can be used for life support systems or other space applications. If successful, our innovation can fully utilize natural (metal oxides) and discarded (wastes from space missions) materials that may exist during space exploration, thus saving the valuable oxygen or water that can be used for life support systems or other space applications.
Scandate cathodes are proposed as a way to boost performance and life for electric space propulsion systems.  This company has recently demonstrated breakthrough performance on these cathodes in other formats.  We have demonstrated emission of 5 Amps/cm2 at 850 degrees CB, which is 200 degrees C below that of conventional cathodes.  At this temperature they should live at least 100,000 hours.  This makes scandate cathodes a candidate for use in deep space missions.  
In Phase I we propose construction and testing of several hollow scandate cathodes.  We propose to do both vacuum and ion environment characterization on them.  In Phase II we will begin active collaboration with NASA to test these cathodes in complete ion thrusters.
NASA's future X-ray astronomy missions will require X-ray optics that have large effective areas, are lightweight, and cost effective. Recent X-ray telescopes, such as the Chandra Observatory, utilized reflectors made from zerodur which were up to 20mm thick. The thickness of the reflector as well as the mass limited the number of nested optics that could be implemented. The current state of the art reflectors are made from electroformed nickel/cobalt which is on the order of 1mm thick. The implementation of these thin optics have greatly increased the number of nested reflectors possible. XMM-Newton uses such optics and consists of 58 nested reflectors compared to 4 for Chandra.
Aside from the manufacturing cost of the reflectors themselves, the mass of the telescope is a large factor that determines the overall cost of the mission, mainly due to the requirements of the launch vehicle. The proposed innovation seeks to improve upon the current state of the art by replacing much of the NiCo with a stiff, lightweight ceramic material. A thermal spray process will be developed to allow for the deposition of porosity graded alumina onto the rear surface of the reflector. Several diagnostic techniques will be used to adjust the inflight particle state as well as the resulting residual stress of the coating as to not adversely affect the figure accuracy of the optic. The gradation of the alumina layer will allow for CTE matching with the electroformed shell as well as optimization of the ceramic stiffness.
By reducing the NiCo layer from 1mm to less than 100um and adding a 200um alumina layer as the support structure the overall mass of the telescope can be greatly reduced and thus reduce the overall cost of the mission. Additionally the overall thinner optic would allow a greater packing density and increase the capabilities of such X-ray telescopes.
We propose a radical new approach for to the design and fabrication of a fiber-less Interferometric Optical Gyroscope (IOG) that enables the production of a very small IMU with better performance, higher reliability, high level of robustness and lower cost. Gener8 and InFiber Technology estimate that an order-of-magnitude better cost and size to performance ratio of IOG sensors and their corresponding assemblies can be achieved when compared to the conventional IFOG implementations.
NASA has a need to develop higher energy density battery systems to meet the power requirements of future energy devices.  In this proposed Phase I program, PSI will develop an advanced cathode electrode structure that allows for the construction of lithium ion cells with long life (&gt;250 cycles) and energy densities &amp;#61619;265Wh/kg.  The novel cathode electrode will reduce detrimental reactions with the electrolyte at high voltages that result in inefficient cycling and enhance performance fade.  Initially, PSI will demonstrate the feasibility of the proposed approach by constructing and performing steady state cycling of lab sized silicon/cathode cells.  This testing will highlight the ability to construct cells that can maintain their performance over hundreds of cycles.  Scale-up of the optimized processes will then be carried out to support construction of prototype Ah sized cells and demonstrate MRL and TRLs of 4.  Phase II efforts would focus on construction of larger cells, demonstrating the cycling performance, and the readiness of the technology for integration into prototype battery packs for initial field testing.
Longhurst Engineering, PLC, and Vanderbilt University propose an in-space friction stir welding (FSW) machine for joining complex structural aluminum components.  The proposed FSW machine is innovative because it can be deployed by 2 people and be used to weld complex surfaces that extend beyond linear welding applications.  The in-space FSW machine is a 3 axis system that can be mounted to work pieces of varying geometry, position, and orientation through the use of a high performance vacuum system or mechanical clamps.  The key enabler of the proposed FSW machine is a self adjusting and self aligning FSW (SAA-FSW) tool that eliminates the need for automated actuators.  In addition, a collection of force reduction techniques will be included as part of the system.  When combined together, it is theorized that the effect will be significant and will lead to the advancement of FSW by reducing structural rigidity requirements of FSW machines.

Our work plan begins by determining the net effect of the combined force reduction techniques.  Substantial effort is given to the development of a preliminary SAA-FSW tool which includes experimental welding.  Lastly, a preliminary set of engineering plans will be delivered based upon the results from the development of the SAA-FSW tool and force reduction techniques.
The Phase I project will develop a suite of diagnostic sensors using Direct Write technology to measure temperature, surface recession depth, and heat flux of an ablative thermal protection system (TPS) in real time, which can be integrated to support TPS evaluation and in-situ diagnostics during planetary entry.  Standalone heat flux sensors and those fabricated by direct deposition will be developed and demonstrated for integration within TPS materials for use in extreme re-entry conditions.  The intent is to use the sensors for real time heat flux measurements to validate new materials and systems, as well as for flight structures where space and accessibility are limited.  Methods for incorporating thermocouples, heat flux and recession sensors using Direct Write technology will be developed to provide accurate sensing capabilities.  Notably, recession tolerant heat flux sensors will be designed and fabricated to demonstrate feasibility of this new heat flux sensor technology and subsequent instrumentation capability for TPS.
NASA seeks Unmanned Aircraft Systems (UASs) for Earth science data collection for missions with variable durations, operating proximities, altitudes, and environmental conditions. Of particular interest is the Ice Bridge mission, which takes observations in support of Arctic and Antarctic research by identifying ice sheet motion, three-dimensional ice features, and other atmospheric and surface effects. These UAS aircraft may be equipped with a variety of sensors, with each aircraft potentially completing a unique set of objectives, only some of which take advantage of or require distributed sensing. Such a flexible system demands that vehicles be capable of seamless entry and exit of aircraft from any distributed sensing task. The approach proposed here satisfies these needs through a distributed sensing architecture that allows cluster sensor information to interface with and influence a multi-aircraft, high-precision, closed-loop path planning and control system. In addition, the UAS path planner is capable of managing dynamic flight regimes, including high winds and turbulence, while ensuring proper target tracking. This combination of features maximizes mission utility and path repeatability.
An improved efficiency amplifier for high power pulse applications at P-Band will be investigated that will support space based RADAR systems.  Current P-Band pulsed amplifier technologies use Silicon Bi-polar and LDMOS device technologies that have increased internal device parasitic characteristics that lead to lower gain and more difficult power matching over GaN technologies.  Integra Technologies has experience with all three device technologies.  Integra also has the design and manufacturing processes in place to optimize transistor design and amplifier design for P-Band pulsed applications.
   The preliminary effort will investigate GaN devices at 150W (TBD) levels to determine the overall gain and efficiency at UHF frequencies using Class AB bias and Switch Mode matching techniques to achieve greater than 70&#37; efficiency for a pulsed amplifier application.     Longer term device investigation will include geometry modifications to optimize the chip size and cell dimensions for the P-Band RADAR application.
   Ultimately, the GaN device will be scaled into a target 1kWatt output stage with an appropriate driver device to enable a greater than 40dB gain amplifier.  The final amplifier module will include bias modulation techniques for efficiency.  The amplifier will include material selections and layout techniques for reliability under high RF energy signal levels and low pressure environments.
Capitalizing on a potent confluence of expertise in III-Nitride epitaxy, GaN-Si power device designs, and wide-bandgap power electronics, researchers at GeneSiC Semiconductor and Cornell University jointly propose a SBIR program focused on the development of 15 kW/300 ?C-rated power converters using AlGaN/GaN-Si MOS-HFETs and Schottky rectifiers. The proposed AlGaN/GaN-Si power converters to be developed in this program will usher in a new generation of high-efficiency, low-cost, and radiation-hard power conversion units on-board future NASA spacecraft. Phase I of this proposed work will focus on the optimization of the design and fabrication of the AlGaN/GaN-Si MOS-HFET and NSJ SBR devices. Phase II will be focused on the design and integration of Si/GaN gate-drive circuitry with the power SBRs and transistors to create high-power integrated circuits. Another major objective during Phase II will be the construction of Rad-Hard packaging for the power ICs. At the end of Phase II of this program, a fully-functional 15 kW/300?C rated power converter IC equipped with AlGaN/GaN-on-Si  MOS-HFETs, Natural SuperJunction (NSJ) SBRs as free-wheeling diodes and on-chip SiC or III-Nitride gate drive circuitry will be demonstrated at a switching frequency of &amp;#8805; 1 MHz and at a temperature of  &amp;#8805; 300 ?C. As compared to the existing state-of-the-art power electronics technology, the proposed AlGaN/GaN-on-Si power converters will offer (A) Lower on-state losses, 300 ?C operation and 1 MHz switching capability (B) A Lateral device architecture, which is highly desirable for construction for monolithic power integrated circuits (C) Possibility of hybrid interconnection of III-Nitride Power Devices with on-chip Rad-Hard AlGaN/GaN Gate Drive Circuitry (D) Desirable Normally-OFF Power Switches.
We propose to develop an innovative Autonomous Flight Safety Inference Engine (AFSIE) system to autonomously and reliably terminate the flight of an errant launch vehicle. This proposed phase 1 research is innovative in that it combines proven NASA-developed AFS algorithms, real-time hazard assessment algorithms and hazard envelopes generated from Joint Advanced Range Safety System Real Time (JARSS RT)  and an on-board vehicle simulator into a refined onboard software inference engine that monitors navigation states, mission flight rules and onboard anomaly instrumentation.  An autonomous flight safety system must be able to reliably perform accurate and autonomous navigation so as to determine the vehicle position, velocity and attitude states in real time. Reliability requirements for AFS are high due to stringent loss-of-life constraints, often leading to redundant navigation sensors with attendant cost impacts. Our innovative solution proposes to satisfy RCC accuracy and reliability requirements by exploiting the low-cost COTS sensor and processor architectures that are currently being baselined for the Common NanoSat/Launcher Avionics Technology (CNAT) study and a Nano launch vehicle avionics design. This dual use hardware implementation will greatly reduce the recurring costs for the production of an autonomous flight safety system.   This has significant implications for reducing the costs for launch vehicles, particularly Nano and Micro Satellite Launch Vehicles (NMSLV), where range safety costs currently consume a burdensome percentage of the launch cost.  Under this proposed phase 1 effort, we will 1) identify the range requirements and develop a plan for range safety for approval of the system, 2) identify reliable low-cost COTS hardware that satisfies the range accuracy and reliability requirements and, 3) develop an end to end simulation to demonstrate the AFSIE Concept of Operations.
Paragon Space Development Corp (Paragon) and Thin Red Line Aerospace (TRLA) proposes to explore the utilization of inflatable structures by designing a habitation module as an integrated, all-fabric inflatable structural architecture, rather than modifying rigid space structural designs with an inflatable envelope. Paragon and TRLA have developed several concepts with the potential to eliminate the need for hard-material support structure within an inflated habitat. A key feature of the proposed solution is the focus on eliminating the need to connect to or compromise the air-barrier thus creating a structure with highly predictable load performance and minimal leak rate. The proposed activity will address primary and secondary structures in an integrated fashion with consideration of innovative approaches of addressing the assembly, integration, and deployment of all structures to minimize launch volume and mass while providing cost savings and maximizing usable living space. This includes floors, walls, Environmental Control and Life Support System (ECLSS) elements, thermal control fluid loops, insulation, radiation shielding, MMOF protection, and electrical data support, while providing a stable, secure support for interior hard-goods into an all-inflatable design that can be efficiently packaged.

Inflatable structures exhibit the highest specific stiffness of any known structure and can produce significant weight savings over hybrid structural designs. Paragon's multi-pressure vessel concept utilizes nested pressure vessels to form a multiwall structure entirely encapsulated and independent of the outer hull and air barrier material to ensure minimum leak rate. An ECLSS induced pressure differential exists between a central core, the inner habitable volume walls, and the exterior pressure hull and air barrier material. Perforations in the core and inner walls allow continuous airflow providing air revitalization and heat removal.
OPTRA proposes an open-architecture spectral gas sensor based on compressive sensing concepts employed for both spatial and spectral domains.  Our matched spectral filter (MSF) core can be used as a single point detector in either point or standoff configurations or it can be coupled with a compressive imaging module for molecular imaging.  The MSF core employs a digital micromirror device (DMD) to apply reference spectra to a spatially dispersed spectrum; the dot product measured with a single element photodetector is proportional to the probability of the compound corresponding to the reference spectrum being present.  The MSF can also be used for quantification via grayscaling of the DMD.  This approach effectively performs multicomponent spectral analysis in hardware rather than software thereby reducing data bandwidth requirements.  The MFS will be designed for the 3-5.5 micron spectral range enabling detection and quantification of a range of greenhouse gases and other air pollutants.  This solution represents a significant cost and size reduction relative to commercially available spectrometers operating in this spectral range, as it does not require a focal plane array or interferometer.  Under the Phase I effort we will design, build, and test the MSF core configured for point detection.
Invocon's Wireless Intra-vehicle Communication System (WICS) is being designed as an enabling technology for low-cost launch vehicles. It will reduce the cost of these vehicles in primarily three ways:

1. Minimizing vehicle weight by decreasing bulky cables and connectors - this increases the useful payload and decreases the propulsion requirements.
2. Minimizing physical interconnects - this simplifies integration, testing, and launch control and thereby decreases the labor involved in these tasks.
3. Enabling testing at the vehicle or module level - this reduces the total amount of testing at the component level resulting in a smaller required test budget.  It also reduces the mass of enclosures required in the vehicle.

WICS will operate wireless networks as part of the closed-loop Thrust Vector Control (TVC) system and the vehicle's data acquisition system.  The two networks share many characteristics while diverging in a few areas based on their specific constraints.  The TVC network must minimize latency and maximize both throughput and reliability.  The data acquisition network must include paths from many locations througout the vehicle.  In order to maximize the return from Phase I, Invocon will concentrate its effort on developing proof-of-concept hardware and emphasize initial software development for the critical control application.
The availability of an air vehicle to perform missions or generate sorties is negatively impacted by time spent on the ground due to scheduled servicing and maintenance. Condition Based Maintenance (CBM) helps maximize the availability of air assets by servicing the air vehicle based on actual condition as opposed to a fixed number of operating hours. Prognostics and Health Management (PHM) enables improved CBM on air vehicles by comparing in-situ sensor data to prognostic models of components and subsystems to predict wear as it occurs. Integration of these PHM systems with an autonomic logistics infrastructure can lead to even greater increases in sortie generation rates and decreases in maintenance cost and logistics burden by eliminating unnecessary preventative maintenance as well as identifying failures occurring outside the normal scheduled maintenance cycle. Aurora's innovative approach utilizes information from existing sensors (i.e., does not require additional sensors added to the vehicle, hence, 'sensor-free') to determine PHM.
Current implementation of PHM is focused on new designs of manned aircraft to allow co-development of the PHM system and its specific sensors. Unmanned Aerial Systems (UAS) have sensors and subsystems already installed that can provide the capability for a PHM retrofit on in-fleet systems. UAV specific subsystems, such as the autopilot, also provide the opportunity for new PHM capabilities beyond those considered in manned aircraft.

Aurora proposes the Integrated Vehicle Health Management System (IVHMS). Aurora's IVHMS will compare models of the aircraft in different configurations to an estimate of the current state of the aircraft in order to generate a better understanding of the real-time operating condition of the vehicle and its constituent components. The IVHMS uses these capabilities to generate a vehicle-wide identification of systems in order to detect faults as they influence overall performance.
Vesitech, Inc. has developed a totally new class of water treatment technology utilizing novel carbon based electrodes that have been shown to electrochemically produce advanced oxidation (AO) species in-situ in contaminated water.  Depending upon the electrode formulation and configuration, the species produced include ozone, hydrogen peroxide, superoxide, and hydroxyl radicals, all of which are effective in destroying a wide range of toxic chemical compounds and microbial contaminants in potable water.  This technology has been proven effective in the disinfection of NSF Type I and Type II water. The device is very compact, effective, and energy efficient (&lt; 3watts). Residual hydrogen peroxide can be produced in sufficient quantities to provide a residual effect and inhibit the formation of bio-films. These advanced oxidation electrodes represent a new platform technology which will enable effective, inexpensive, and energy efficient treatment designs for point-of-use potable water treatment systems
The overall objective is to demonstrate the concept of Yb:YAG crystalline fiber MOPA laser and investigation the technical feasibility toward 50 mJ single frequency MOPA system in the Phase-II research. Onyx Optics crystalline fiber waveguides are made from true rare-earth doped YAG crystals with Adhesive-Free Bond (AFB&amp;#174;) technology. Compared with silica or phosphate glasses, the YAG crystalline fiber waveguides have the following advantages: (i) YAG crystal has at least one order of magnitude lower Stimulated Brillouin scattering (SBS) gain coefficient than silica or phosphate glasses (10-15 to 10-12 vs 10-11 m/W), which directly leads to the SBS free power being at least one order of magnitude higher than the glass fibers; (ii) YAG crystal has much higher thermal conductivity than glass fibers (10.7 vs 1.38 W/m degree C). Therefore, much shorter fiber length that is only about one tenth of the glass fiber can be used for the same pumping conditions and the SBS threshold can be further increased; (iii) Due to the shortening in the fiber length, straight fiber can be practically used for high power amplification. Therefore, large single mode area (LSMA) can be more easily achieved. Considering the high pulse energy requirement in a future LIST mission, only large mode area (LMA) Yb:YAG fibers with core size &gt;40 mm will be fabricated and investigated in the Phase-I research. The fibers will be double clad to increase the pumping power and efficiency, while maintaining near diffraction limit laser beam quality.
NASA's Science Instruments, Observatories, and Sensor Systems Roadmap calls for instruments capable of in situ mineralogical analysis in support of planetary missions in the coming decades. Such instruments will provide capabilities for surveying and identifying minerals on and beneath planetary surfaces, guided by robotic vehicles.    These instruments should be highly reliable and compact, be remotely operable and require minimal operating resources. To meet this challenge, the goal of the proposed Phase I program is to develop a combined Raman and infrared fiber optically coupled probe head that can be used for mineral analysis by providing a complete vibrational spectroscopic fingerprint for high quality in situ mineral identification that can be used in a variety of NASA platforms.For the Phase I work, the goal will be to prototype a dual excitation Raman/IR fiber optically coupled microscope probe head and demonstrate its utility in the analysis of minerals.The Phase I Work Plan includes:
1. Prototyping of an Integrated Raman/IR probe head
2. Performance Evaluation of the Integrated Raman/IR Probes
3. Acquisition of a preliminary Raman and IR database, in collaboration with Dr. Robert Downs director of the RRUFF mineralogy project at the University of Arizona
Ensuring a safe air environment in manned spacecraft is critical to the success of all missions. Exposure to hazardous chemical species threatens the well-being of the crew and prevents them from fulfilling their tasks.  While a wide variety of sensors currently are available to monitor such chemicals on the ISS, some of these sensors are inadequate.  In particular for one important species, formaldehyde, Southwest Sciences proposes to develop a sensor that can provide continuous, real-time monitoring of this gas, so as to assure that the crew is better protected.
Leveraging TUI's SWIFT software defined radio (SDR) architecture, we propose to develop a 100 Mbps downlink and intersatellite crosslink capability with ranging and timing synchronization capabilities to enable more sophisticated CubeSat and small satellite missions. This effort will focus on designing a Ka-band communications solution including a high-gain patch antenna array and Ka-band RF front end, that can be integrated with TUI's SWIFT software defined radio (SDR) processor running state-of-the art modulation and coding techniques to provide a robust link with adaptive data rates up to 100Mbps. Analyses indicate that a 100 Mbps crosslink can be closed between two CubeSats separated up to 100 kilometers and between a CubeSat in low-Earth orbit and a 12 meter  dish (99&#37; link availability with the ITU-P618 rain model) with the same radio. These links represent nearly two orders of magnitude of data throughput improvement over the rates achieved by CubeSat missions to date. This increased downlink and crosslink data rate will enable nanosatellites and CubeSat constellations to be used for scientific, commercial and operationally relevant remote sensing and earth observation missions. Adaptive modulation and coding makes the link more robust and allows for reduced data rate operations without increasing aperture sizes at greater distances (e.g. Lunar and Martian). The proposed SWIFT-HPX radio technology and resultant product supports the migration of small satellite and CubeSat near-Earth communication downlinks and crosslinks to higher frequency links, which is consistent with Phase 1-3 of NASA'S Space Communication and Navigation (SCaN) Program.
Traditional Extravehicular Activity (EVA) spacesuits incorporate either hard or soft upper torso subassemblies as part of their architecture.  In either case, these components are of a specific, fixed size and lack provisions to make sizing adjustments across the overall envelope of the torso.  This project will further the TRL of the prototype Morphing Upper Torso, an innovative pressure garment that allows for resizing of the torso and precise repositioning of the neck, scye and waist planes.  The concept has seen significant initial development through the research and PhD dissertation of Dr. Shane Jacobs, the PI on this proposed effort.  To date, analytical and experimental models of the full Morphing Upper Torso design (in which the back hatch of a rear-entry torso is interconnected with the waist ring, helmet ring and two scye bearings) have been used to demonstrate the feasibility of this novel space suit concept. The analytical and experimental results demonstrate that the torso could be expanded to facilitate donning and doffing, and then contracted to match different wearer's body dimensions. Using the system of interconnected parallel manipulators, suit components can be accurately repositioned to different desired configurations. The demonstrated feasibility of the Morphing Upper Torso concept makes it an exciting candidate for inclusion in future EVA suit architectures.  The proposed project will further the development from the proven concept in a laboratory setting, focusing on integration and development of wearable mockups and ultimately a useable, wearable, pressurizable prototype.
A launch vehicle and its launch facilities are subjected to intense acoustic loads generated by the vehicle's propulsion system. The vehicle, its payload, and facilities must be designed to withstand these loads to ensure mission safety and success. Accurately accounting for the acoustic environment early in the design phase of a new launch vehicle is a high priority. Governments and aerospace entities expend significant resources investigating launch acoustics using a combination of predictive models, full-scale and subscale tests, and test flights. Sensors that acquire acoustic data are deployed over a limited geometry and do not sample the full three-dimensional volume exposed to the acoustic field. Launch imagery samples that three-dimensional volume. Under appropriate conditions, rapidly varying condensation features are generated by the lift-off acoustic field. A software tool will be developed to determine the three-dimensional structure of the field from imagery of these acoustically-induced features. This unique data will be compared to model predictions and will serve to either validate those models or inspire modifications to those models. Improving predictive models contributes to a more reliable and efficient design process for new launch vehicle propulsion systems, and thus reduces associated design costs.
Fiber reinforced composite materials are used extensively in aerospace applications due to their high stiffness and strength to weight ratio, and superior thermal, mechanical, electromagnetic and fatigue properties. However, given their demanding operational environment, composite aerospace and aircraft structures are prone to damage and manufacturing related flaws. An accurate assessment of composite structural performance and system life management strategies requires quantitative information on the aforementioned damage states of the components. Recent advances in infra-red (IR) sensing and data processing technologies have enabled real-time thermoelastic stress analysis (TSA) methodologies to finally become viable for accurate diagnostics and prognostics of composite structures. The success of these thermography methods, however, depends strongly on the characteristics of the surface of the composite components. Materials Technologies Corporation (MTC) proposes to develop a specialized, spray-on and peel-off coating technique which would facilitate high accuracy quantitative thermoelastic analysis through improved IR response and thus enable on-going in-situ diagnostics and prognostics during component lifecycle without necessitating disassembly and off-line inspection. A major benefit of the product would be to facilitate usage of less expensive inspection systems that can take advantage of the advanced high emissivity coatings.
&lt;p&gt;Goals:&lt;br /&gt;1. Continue development of a flexible facility capable of small scale hybrid propulsion tests. The facility will be able to adapt to new research objectives as questions arise.&lt;br /&gt;2. Enable the inclusion of hybrid propulsion systems in future mission design studies by determining the empirical constants in the regression rate equation for paraffin-based fuels with in situ oxidizers (a combination of O2, CO and CO2).&lt;br /&gt;3. Determine hybrid rocket packaging constraints by testing at different fuel grain L/D&amp;rsquo;s to understand how the combustion efficiency and mixing changes with length.&lt;/p&gt;
&lt;p&gt;The goal of this task is to create a maskless process for sample 500 &amp;micro;m 3-D objects. Specific objectives are to&lt;/p&gt;&lt;p&gt;(1) Develop 3-D CAD computer models and suitable&amp;nbsp; resist processes while working on dry etch techniques to hit the 500 &amp;micro;m goal&lt;/p&gt;&lt;p&gt;(2) Demonstrate optical gray-scale pattern formation and&lt;/p&gt;&lt;p&gt;(3) Test concepts on commercial state of the art maskless machines capable of gray&amp;nbsp; scale lithography.&lt;/p&gt;
&lt;p&gt;In this work we will: 1) develop novel TE materials&amp;nbsp; with a factor of 2x or more improvement in the dimensionless TE figure of merit (ZT) over state-of-the-art materials in cryogenic environments (100K-300K range) ; and 2) validate the novel materials performance using proof-of-concept power generation TE devices to demonstrate their potential to achieve 15 to 25&#37; conversion efficiency (up to 4x state-of-practice systems) when using low grade heat sources, Radioisotope Heater Unit (RHU)-based or single General Purpose Heat sources (GPHS), and rejecting heat at cryogenic temperatures.&lt;/p&gt;
&lt;p&gt;To probe the interior of a comet, we are going to employ Radar Reflection Imager (RRI) Instrument on an orbiting platform. While orbiting around the comet at a safe distance of about 20 kilometers , the RRI will transmit electromagnetic waves and receive returned signals from the comet &amp;#39;s surface and the interior. After operating RRi for about 45 days, we would collect almost a million data sets from all sides of the comet. We will develop a technique which will allow us to process the million data sets altogether in order to construct Computer Aided Tomography-like images of the cometary nucleus.&lt;/p&gt;
&lt;p&gt;This task will enable future planetary mapping missions through a technique called interferometric synthetic aperture radar, using microwave and triangulation to create very high precision maps of extra- terrestrial bodies by orbiting spacecraft. One of the key challenges of any mapping mission is the amount of data generated by the spacecraft, and the difficulty of returning that data to earth. This task will&amp;nbsp; develop new methods to reduce data processing onboard the spacecraft by using self focusing and fully processing the images&amp;nbsp; within the instrument itself, thereby reducing the burden on the spacecraft and the down link network by orders of magnitude. This can significantly reduce&amp;nbsp; mission duration and thus mission cost, enabling these mapping techniques for planetary bodies.&lt;/p&gt;
&lt;p&gt;The innovation relies heavily on a &amp;ldquo;reduced complexity&amp;rdquo; flight terminal with sound functionality yet compact enough to fit within a module of a standard CubeSat. For the optical telescope, which consumes the most volume, we envision use of a recently patented &amp;ldquo;monolithic&amp;nbsp; telescope.&amp;quot; The laser transmitter is based on an advanced miniaturized fiber amplifier. For the modem, a JPL-developed deep-space lasercom modem design will be slightly modified, to remove unrelated features, for use with the CubeSat terminal.&lt;/p&gt;
&lt;p&gt;This work will transition commercial advanced- yet mature- packaging approaches, such as surface mount and system-in-package, into mainstream use at JPL. Starting with an existing Digital Processor Unit (DPU) board that is planned to be used on multiple spacecraft in the next decade, we will apply modern commercial electronics packaging solutions to create a miniature version of the DPU. The DPU has multi I/O communication options (Spacewire, LVDS, 1553, TTE) and will target a 1U board form factor, down from existing 6U layout.&amp;nbsp; Use performance COTS based devices to provide power and size reduction while maintaining performance and universal adaptability.&lt;br /&gt;The DPU hardware will be used to demonstrate in-house manufacturability, cost effectiveness, functionality, performance, and reliability of state of the art electronics manufacturing and assembly for future-focused NASA missions. The implementation of newer packaging technologies will result in large decreases in mass, volume, and power of electronic subsystems.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;A custom multifunctional core substrate scheme comprised of next generation polyimide, ceramic and/or silicon materials will be designed to integrate new 2.5D and 3-D interconnect technologies into producing a significant size and power reduced RF transponder.&amp;nbsp; Development of heterogeneous flip chip attachment to low loss substrates, embedded RF waveguides and passives (R,L,C) and completely plug in/stackable Multichip Modules (MCM) will be required to meet this goal.&lt;/p&gt;
&lt;p&gt;The task will assess the requirements for a testbed to study the retrieval of a Mars sample cache from the Martian surface, or from a Mars caching rover, and subsequent delivery of that cache to the upper stage of a Mars Ascent Vehicle for launch into Mars orbit.&amp;nbsp; The testbed will be implemented and used to develop and demonstrate prototype architectures and technologies for cache retrieval and transfer.&lt;/p&gt;
&lt;p&gt;Given the large volume and additional mass available for scientific use on planned commercial geostationary platforms, we have conceived an alternative drag-free design, which we have named &amp;ldquo;Two-Stage Drag-free&amp;rdquo;. It can be regarded as a modification of the Modular Gravitational Reference Sensor (MGRS) design developed at Stanford University during the past decade.&amp;nbsp; Our two-stage drag-free system works in the following way. A rigid structure containing the MGRS is free-floating within the enclosure cap added to a comsat nadir deck. The free-floating spherical proof mass location, relative to the rigid structure hosting it, is measured through laser metrology; the position of the rigid structure within the enclosing cap is measured instead by a network of sensors. The sensors data is passed on to a set of cold-gas thrusters that act on the comsat to maintain its position relative to the rigid structure to within a few centimeters, while at the same time both measurements are used by a set of actuators that constantly maintain the rigid structure centered on the spherical proof mass. In our two-stage drag-free design the actuators rely on the comsat mass to react against in order to center the rigid structure on the proof-mass, thereby performing the equivalent operation of the &amp;mu;N thrusters in the traditional drag-free design.&lt;/p&gt;
&lt;p&gt;SPECTROMETER:&amp;nbsp; The grating spectrometer uses a curved grating fabricated on a high resistivity silicon wafer. Light will be coupled in via a silicon immersion lens and coupling waveguide. The wafer profile, including the grating facets are defined by photolithography and deep reactive etching (DRIE) and the wafer is metallized on both sides for better light confinement (except in the regions below where the detector antennas will be placed).&amp;nbsp; The grating both focuses and diffracts the light in the plane of the wafer to a focal arc, where the detectors are positioned. QCD DETECTOR ARRAY: The Quantum Capacitance Detector is a mesoscopic superconducting device that exploits its extreme susceptibility to the presence of quasiparticle excitations arising from pair-breaking radiation to enable background limited detection.&amp;nbsp; QCDs have demonstrated photon noise limited performance&amp;nbsp; at 1.5THz for optical loadings 10-20 to 10-17W.&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp; The detector die will be placed directly on top of the spectrometer wafer and will have an array of QCDs with antennas positioned at the focusing spots of each wavelength.&amp;nbsp; Each detector will be coupled to a superconducting resonator with a different resonant frequency to allow for frequency multiplexing with a single feedline coupling the RF signal to all resonators.&amp;nbsp; A&amp;nbsp; prototype with 32 spectral channels will be demonstrated&lt;/p&gt;
&lt;p&gt;Data Science is emerging as a critical area of research and technology to advance scientific discovery, knowledge and decision making through systematic computational approaches to analyzing massive data sets. The sheer volume of data increase, coupled with the highly distributed and heterogeneous nature of scientific data sets, is requiring new approaches for managing, analyzing and understanding data.&amp;nbsp;&amp;nbsp; The technology effort is focused on developing new software architectures, software tools, and computational methodologies which can improve the performance and automate the extraction of key features, anomalies and patterns in the data to support the big data challenges emerging from observational instruments and systems.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Perform systems study to determine driving requirements. Perform LEO V GEO observation scenario study. Develop 60 GHz antenna technology suitable for LEO or GEO temperature sounding.&lt;/p&gt;
&lt;p&gt;There are two overall objectives: 1. Define the spatial resolutions and sensitivities required for the instruments; 2. Mature the technology for the limb sounder and the selected spectrometer. Work in the first year is focused on strengthening the case for the observations and establishing requirements for spatial resolution.&amp;nbsp; The resolution study in turn dictates the preferred implementation route for the short wave infrared (SWIR) and thermal infrared (TIR) observations (interferometer vs. grating spectrometer). Work in the second and third years centers on technology maturation for the infrared and limb microwave sensors.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Millimeter-wave (mm-wave) communications have gained attention in recent years, primarily since the high fractional bandwidth potentially offers multi-Gb/s wireless data-links [1-3]. Recently demonstrated mm-wave transceivers offer impressively high data-rates, however, their range is typically limited to only a few meters, and so non-free space mm-wave communication approaches&amp;nbsp; have been developed to operate over longer distances of up to 10 meters. Dielectric ribbons are one example of this, and allow direct coupling from a transceiver with either an on-chip probe or antenna structure placed nearby the ribbon&amp;rsquo;s end. The simplicity of coupling makes them attractive for aircraft and spacecraft applications as transmission through a dielectric ribbon does not rely on an electrical contact, only a coupled wave. Additionally dielectric ribbons can be much lighter weight than copper interconnects, reducing overall payload weight. Also demonstrated data rates of 3 Gb/s can easily be multiplexed down to several Mb per second allowing replacement of several hundred low speed control cables.&lt;/p&gt;
&lt;p&gt;Ka Band Parabolic Deployable Antenna (KaPDA) for Interplanetary CubeSat Communications allowing moving up from UHF, S or X to get higher gain for a given diameter.&lt;/p&gt;
&lt;p&gt;Under this initiative, a prototype Ka-Band exciter and receiver are under development; suitable FPGAs that are lower power than the Virtex 5 but still compatible with a deep space environment are being surveyed with a goal of a lower power Iris V2 implementation; and a trade study is being conducted to determine under what conditions a CPU is needed and what software would run on it.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;The 20 Watt, 20 Kelvin cryocooler utilizes the reverse turbo-Brayton thermodynamic cycle to cool helium working gas at cryogenic temperatures, circulated through a distributed network for discrete or broad area cooling, having the potential to achieve zero (or near zero) boil-off storage of space-based of liquid hydrogen.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;The focus of this analysis was the development of a complex geometry test fixture and test method for determining solvent cleaning efficiency. AK-225 belongs to a class of chemicals called HCFC and is used for cleaning, drying and lubricant deposition applications. These compounds are regulated by the U.S Clean Air Act and can no longer be produced or imported into the United states.&amp;nbsp; Any alternative solvent must be able to dissolve the soil/contaminant on the part.&lt;/strong&gt;&lt;/p&gt;&lt;p&gt;&lt;strong&gt;The determination of an environmentally safe but reliable quality cleaning solvent is critical to Stennis propulsion test operations.&amp;nbsp; A detailed methodology for determining the replacement solvent was devised and implemented during this project.&amp;nbsp;&amp;nbsp; In reality, parts undergoing cleaning are not able to be inspected internally to determine a cleanliness level.&amp;nbsp; Therefore, a test rig that could be disassembled with complicated internal geometry was made using several computer aided design iterations. The test fixture disassembly allows for the inspection of the internals following the use of the cleaning solvent.&amp;nbsp; The contamination solution is made of various items that are used in the propulsion test environment.&amp;nbsp; Upon &amp;ldquo;dirtying&amp;rdquo; the test rig, a thorough post processing inspection exercise procedure was devised to be used when evaluating alternative solvents.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;The actuation of the hybrids relies on spinning three internal flywheels, which allows all subsystems to be packaged in one sealed enclosure and enables the platforms to be minimalistic, thereby reducing the cost of the mission architecture. The hybrids would be deployed from a mother spacecraft, which would then act as a communication relay to Earth and would aid the in-situ assets with tasks such as localization and navigation.&amp;nbsp;In Phase I, we demonstrated that the bounding assumptions behind our proposed mission architecture are reasonable, and have a sound scientific and engineering basis.&lt;/p&gt;&lt;p&gt;Phase II has two objectives. First, to advance from TRL 2 to TRL 3.5 the mobility subsystem of the hybrids (comprising planning/control and localization/navigation), with the aid of a unique test bed for low-gravity surface mobility and parabolic flight tests on a zero-g airplane. Second, to study at a conceptual level (TRL 2) system engineering aspects for the hybrids, with a focus on power, in the context of a mission to Mars&amp;#39; moon Phobos. Collectively, our study aims to demonstrate that exploration via controlled mobility in low-gravity environments is technically possible, economically feasible, and would enable a focused, yet compelling set of science objectives aligned with NASA&amp;#39;s interests in science and human exploration. Indeed, while controlled mobility in low-gravity environments was identified by the National Research Council in 2012 as one of NASA&amp;#39;s high priorities for technology development, it has never been demonstrated in a high-fidelity low-gravity test bed. Hence, this proposal, if successful, would provide a sought-after and currently unavailable capability for small bodies exploration.&lt;/p&gt;
&lt;p&gt;Lunar sub-surface exploration has been a topic of discussion since the Lunar Reconnaissance Orbiter identified openings (cave skylights) on the surface of the moon in 2009. NASA&amp;#39;s participation in the UK&amp;#39;s MoonLITE mission shows the wide appeal of this phenomenon. NASA has focused internally on two distinct architectures to explore the lunar sub-surface: robotic (rover based) or human (astronaut based). Both are unfortunately beyond the limits of NASA&amp;#39;s conceivable near- and mid-term resource allocation. We present a third option: mapping and characterization of lunar subsurface structures with an orbiting platform performing photon time-of-flight imaging. A tabletop demonstration of the imaging technique, &amp;#39;seeing around corners&amp;#39; was led by one of the authors and we assert that this concept can be extended to a lunar orbiting platform architecture.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;LED light sources are ideal for plant growth systems. However, commercially available multi-color LED illumination panels are designed and manufactured to produce a single particular illumination. These panels have very specific LED colors arranged in a very specific fashion. This limits the amount of color mixing, intensity variation, and spatial arrangement that is possible, precluding passive precision illumination. There is no feedback mechanism to detect spectral shifts caused by LED aging and additionally, there is no mechanism to modulate LEDs. It is also not possible to integrate an imaging system into these panels. Furthermore, these panels are commonly operated using high voltage AC power sources, which is not ideal in a potentially wet environment. Therefore, to address these issues, custom LED illumination panels were designed and developed for this project&amp;rsquo;s plant growth chamber.&lt;/strong&gt;&lt;/p&gt;&lt;p&gt;&lt;strong&gt;A systematic approach was taken to determine the general size, specifications, and shape of a portable plant growth unit. Once the general size and shape were finalized, the detailed design of the support structure, aeroponics, and lighting subsystems were developed. Particular attention was given to heat transfer and the expected LED thermal environment.&amp;nbsp; Additionally, a&amp;nbsp;&lt;/strong&gt;&lt;strong&gt;computational analysis was performed to determine optimal LED nodes placement so that two different uniform illumination fields could be yielded:&amp;nbsp; (1) for germinating plants, lower intensity light, and (2) for larger maturing plants, a brighter one.&amp;nbsp; Also, aeroponic studies were reviewed to identify an efficient and user-friendly system that would require minimal user involvement.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;By tracking those probes, we can estimate the asteroid&amp;rsquo;s gravity field and infer its underlying composition and structure. This approach offers a diverse measurement set, equivalent to planning and executing many independent and unique flyby encounters of a single spacecraft. The resulting dataset can yield a global model of the body&amp;rsquo;s mass distribution and reveal unique aspects of the body&amp;rsquo;s interior structure that are otherwise unobservable. This concept offers the possibility of achieving new scientific measurements that extend our understanding of our solar system, benefit human spaceflight, and support planetary protection.&lt;/p&gt;
&lt;p&gt;The proposed technology development concept is a software application tool developed for use on a mobile device at SSC for use in the component retrieval system (SOCS). The development of a mobile application that provides field access to the component database is a type of technology that has been proven successful in the private sector. The project purpose was to demonstrate feasibility that using a mobile application could provide benefits, cost savings, and could be used across Stennis.&amp;nbsp; With this type of tool, personnel could easily access information within SSC&amp;rsquo;s component retrieval systems instantly, providing the real-time information that is often required for the timeliest decision-making. Additionally, an electronic audit trail would enable the ability to see who performed tasks and help reduce error. The result could be a substantial increase in productivity. The capability could provide a new level of accountability for a wide variety of component monitoring retrieval processes. For this project, initial requirements to develop a mobile application software tool that could be used to retrieve detailed information on components from the SOCS database were compiled.&lt;/p&gt;
&lt;p&gt;The Robonaut 2 Project will focus on advancing the capabilities of the Robonaut series of humanoid robots to perform both IVA and EVA on the ISS including legged mobility with climbing limbs, autonomous task software, and computer vision. R2 will demonstrate its ability to grasp handrails from an angled approach, avoid obstacles covering handrails, climb from one handrail to the next and maneuver within the ISS Lab module. R2 will also demonstrate its ability to stow and un-stow itself without crew assistance. Additionally, R2 will demonstrate its ability to perform a complex IVA task without crew assistance.&amp;nbsp; Software advances in the areas of machine vision, obstacle avoidance/path planning and integrated supervisory control interfaces will be required in order for R2 to achieve these goals.&lt;/p&gt;
&lt;p&gt;Affordable Vehicle Avionics (AVA) is being developed at NASA Ames Research Center and is sponsored by Space Technology Mission Directorate (STMD) Game Changing Development Program (GCDP). &amp;nbsp;AVA technology is currently at TRL 5+. &amp;nbsp;&lt;/p&gt;&lt;p&gt;AVA will achieve desired GN&amp;amp;C precision and capability at order of magnitude lower cost, and will:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Develop Avionics and Software&amp;nbsp; emphasizing cost vs. performance, and exploit Model-Based Development.&lt;/li&gt;&lt;li&gt;Exploit advanced sensor-fusion estimator software to compensate for low commercial-grade sensor accuracy.&lt;/li&gt;&lt;li&gt;Employ an &amp;ldquo;Improve, Test, Fly, Improve&amp;rdquo; iterative design cycle approach.&lt;/li&gt;&lt;li&gt;Identify broadly based, global industries that have achieved adequate levels of quality control and reliability in their products and then design around their expertise and business motivations.&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;Iodine propellant offers many enabling capabilities for both SmallSat application and for high power system level implementation.&amp;nbsp; Some of the highest risk elements of system implementation include long life cathode operation, integrated feed system performance, and thruster material changes for iodine compatibility. &amp;nbsp;The work under this task will leverage an existing NASA Phase II with Busek Inc. for development of 600W iodine Hall thruster technologies based on the existing BHT-600.&amp;nbsp; This work will also be done in parallel with the development of the iodine satellite (iSAT) mission that is funded under the Small Spacecraft Technology Program (SSTP).&amp;nbsp;&amp;nbsp; The iSAT mission will be focused on delivery of a flight system for a 200W iodine Hall thruster propulsion system, including the Hall thruster, power processing unit (PPU), and feed system for use in a 12U demonstration mission.&amp;nbsp; To take advantage of scale efficiency, the iSAT and AISP iodine activities will leverage resources at Busek as the technologies and components will be similar.&amp;nbsp; iSAT activities at Busek will be funded under a separate contract with the United States Air Force.&amp;nbsp; Under AISP, a SBIR Phase III contract will be awarded to Busek Inc. for development of the 600W integrated iodine propulsion systems.&amp;nbsp; The plan will also be to leverage the SBIR Phase II to augment with Phase IIe/x funding.&amp;nbsp; The scope of work will mature the critical propulsion system components (thruster, cathode and PPU) to TRL 6 and perform integrated system testing.&amp;nbsp; The proposed effort also includes&amp;nbsp;NASA cathode development,&amp;nbsp;propellant isolator defevelopment, thermal modeling&amp;nbsp;and integrated propulsion system testing.&lt;/p&gt;
&lt;p&gt;Pioneer Aerospace holds a patent to an existing parachute wireless disreef device (patent number &lt;a href="http://www.google.com/patents/US20070252042"&gt;US20070252042&lt;/a&gt;, &lt;a href="http://www.google.com/patents/US20070252042"&gt;http://www.google.com/patents/US20070252042&lt;/a&gt;). The wireless device weighs approximately 8 oz. and is 6.5&amp;rdquo; in length.&amp;nbsp; A single helicopter drop test will be performed to demonstrate the functionality of the system in a configuration comparable to an anticipated demonstration on an Orion drop test utilizing the Orion test article platform recovery system. The demonstration test configuration will approximate the Orion main parachute trailing distance of ~250&amp;rsquo; to demonstrate wireless communication functionality. The payload weight will be such that the rate of descent is similar to the Orion test article platform. The demonstration parachute will have two reefing stages as the Orion parachutes have two reefing stages. The demonstration parachute is much smaller than the Orion main parachute, 29&amp;rsquo; diameter as compared to 116&amp;rsquo; diameter, respectively.&amp;nbsp; Confirmation of system operation will be via onboard upward looking video, Ground-to-Air Video, and the wireless devices&amp;rsquo; onboard health and status data acquisition.&lt;/p&gt;
&lt;p&gt;Conventional methods of manufacturing automation do not lend themselves to construction of large structures with internal features, especially if various other components (such as reinforcement, pipes, sensors, etc) are to be installed within the structure. This explains why the evolution of construction automation has been slow. While well known in parts manufacturing, a promising new automation approach in construction is layered fabrication, generally known as solid free form fabrication or additive manufacturing. However, most of the current layered fabrication methods are limited by their ability to deliver a wide variety of materials applicable to construction (especially if those materials are local, or in-situ). Additionally, they are severely constrained by the low rates of material deposition which makes them atttractive only for the fabrication of small industrial parts.&lt;/p&gt;&lt;p&gt;The ACME project will utilize additive construction expertise previously developed at MSFC and CCI, automation and robotics expertise from KSC, and fundamental construction knowledge developed by the USACE to develop and expand the knowledge base associated with automated construction of planetary surface structures using in-situ materials. Areas of emphasis will include characterization of typical Lunar and Martian regolith materials (using terrestrially-developed simulant materials), optimization of binder materials for each regolith, development of sub-scale followed by full-scale regolith beneficiation and processing, handling and transport and actual mobilitydeposition hardware, and development of automated cleaning processes.&lt;/p&gt;
The NASA Airspace Systems Program (ASP) uses a large suite of models, simulations, and laboratories to develop and assess new ATM concepts and technologies. Most of these capabilities focus on aircraft movements, evaluating the impact of airport and airspace constraints on traffic flows. Emphasis is placed on the actions and interactions of the flight deck and air traffic controllers, including tactical ATC and traffic flow management at the FAA System Command Center and traffic management units (TMUs). The role of the airline operations center (AOC) in these analyses tends to be limited and recognized primarily as a communications mechanism and not an independent actor with designated legal responsibilities and decision making authority.   In a NextGen environment, the AOC will be a major participant, as it offers greater situation awareness across the entire airline network, with superior access to data, analytical capability, and communications.
Our proposed AOC simulation offers several innovations to support ASP research and the aviation community:
1. Provide a stand-alone simulation for analyzing AOCs and their complex interactions with ATM.
2. Increase the realism with which NASA can evaluate new ATM concepts, technologies, and algorithms that affect airline operations, from flight planning to flight following and re-routing, and gate-to-gate aircraft movement control.
3. Provide airlines with the ability to evaluate the effects of NASA ATM research products on their operations, investment criteria, and internal decision processes.
4. Offer a simulation that can integrate with other NASA models and simulations, expanding NASA's system-wide evaluation, gate-to-gate modeling and simulation  capability.
5. Uses industry-standard inputs for flight schedules, messages, and timekeeping to maximize usability by airlines and NASA.
This program will develop a series of nano-/micro-composite coated nuclear reactor facing components using MesoCoat's CermaCladTM process. This proposed SBIR program will build on MesoCoat's extensive prior experience with high energy density fusion cladding systems for large area applications (pipe, plate, structures) where wear and/or corrosion limit the life of metal structures
Innoflight proposes to implement and perform an on-orbit demonstration of a Secure DTN communications suite on the SCaN Testbed aboard the ISS.  Secure DTN is a combination of the Streamlined Bundle Security Protocol (SBSP) and the NSA's IPMEIR (Internet Protocol Minimum Essential Interoperability Requirements) Suite-B based networking protocol. 
 
The Secure DTN suite will enhance NASA's ability to support missions by expanding SCaN's ability to support heterogeneous communications architectures while protecting mission critical data integrity.  Secure DTN will also enhance SCaN's ability to collaborate with non-government entities and foreign partners while assuring ownership of intellectual property.

The Secure DTN effort will include contribution to the INB (ION NASA Baseline) codebase of the SBSP, with an implementation of Suite-B.  The convergence layer will be upgraded with the IPMEIR security suite for internet protocol over CCSDS.  An innovative PKI (Public Key Infrastructure) based key management and distribution system will be prototyped during the effort.

The Phase II effort will conclude with an on-orbit demonstration of the Secure DTN suite with the SCaN Testbed that is currently mounted on the ISS (International Space Station).  The suite will be demonstrated using both TDRSS and direct space to ground communications links.
Inflight icing of engines and airframe presents a significant hazard to air transport, especially at lower flight elevations during take-off or on approach.  Ice accretions on the wings affect the smooth flow required for proper lift. A thin layer of coarse ice can reduce the lift by 30 percent and increase drag by up to 40 percent.  In addition, accretions can also reduce the air intake in engines and affect readings from a (heated) Pitot tube. Michigan Aerospace Corporation (MAC) proposes to continue the development of an integrated LIDAR instrument capable of identifying icing conditions while also allowing for air data sensing as well as other hazard detection capabilities.  The resulting Raman Icing Detection System (RIDES), when coupled with MAC's optical air data solution, will provide unprecedented situational awareness and aircraft safety. The proposed solution will operate without protrusions into the flow, behind a common flush-mounted window on the skin of the aircraft, mitigating the risk of ice build-up during operation and therefore providing a critical redundancy through dissimilar measurement of air data parameters while greatly enhancing a pilot's awareness of potential icing hazards.  MAC will build on its successful Phase I trade-study and design effort through the fabrication and demonstration of a Phase II prototype in an icing wind tunnel.
We have invented a new class of robotics, called `Pneubotics', that rival current manipulators in payload and reach at 1/10th the weight. Our technology leverages insights into lightweight materials and mass manufacturing to create robots that derive power, structure, and movement from pressurized air. As a result, drive trains, motors, bearings, shafts, sliding surfaces, and excess structural material are eliminated, leading the way for robots that exhibit extremely high strength to weight ratios, inherent human safe operation, and high degrees of freedom at comparatively low part count. 

This transformative new technology has the potential to enable the widespread use of automated material handling on missions beyond low earth orbit. The compliant nature of these robotic systems allows them to robustly grasp arbitrarily shaped objects and make them ideal for operating around sensitive equipment or cooperatively with humans. Similarly, due to their fluidic architecture they can be deflated and stowed for efficient transport.  The work described in this phase I SBIR proposal aims to develop the key technological components that will allow the production of Pneubotic systems, including novel pressure vessel based fabric actuator design, a pneumatic power architecture that exceeds electromagnetic efficiency, and dynamic models of inflated fabric structures. These components will enable the construction of a full prototype manipulation system in phase II.
The aim of this project is the development a large data warehousing and analysis tool for air traffic management (ATM) research that can be accessed by users through intuitive web-based User Interface (UI). DSAT is designed to support requirements of a variety of ATM users, from data handlers interested in maintaining data quality to researchers looking for patterns in acquired data to analysts who need to compute basic metrics on a particular subset of data to managers who need to visualize and report results from a particular analysis. DSAT is a multi-level, multi-objective tool for big data analysis that extracts ATM data from a variety of ATM data stores and prepares it for holistic analysis within an actionable timeline. At this time no turnkey software exists that supports all levels of data handling from storage to reporting for ATM research DSAT serves the purpose of a variety of users through a set of tools customized to handle different types of ATM analysis for different types of users. In particular, DSAT is a (i) data storage tool, (ii) data analysis tool, and (iii) visualization and reporting tool all wrapped into one.
A microgravity-compatible Brine Evaporation and Mineralization System (BEMS) is proposed for 100&#37; water recovery from highly contaminated wastewater as well as water generated from entrained organic contaminant oxidation without concern for precipitation of organic and inorganic solids.  The BEMS utilizes fully regenerable evaporation media, a catalytic oxidizer, and heat exchange technologies, which reduce Equivalent System Mass (ESM) for water recovery by eliminating the nominal brine byproduct, dramatically lowering consumables and reducing long-term waste storage requirements.  The BEMS process will exceed the goal of 95&#37; water recovery by 2017-2022 set forth by NASA in the space technology roadmap.  Highly contaminated wastewater streams such as urine, hygiene water, and RO brines are major wastewater streams for the BEMS.  The Phase I project will focus on development of the evaporation bed capacity and catalytic oxidizer efficiency.  The Phase II will incorporate thermal efficiency and introduce catalytic capability into the evaporation bed to improve efficiency and result in delivery of a prototype system.  These efforts will be the foundation for the design and construction of a flight ready prototype for use on the International Space Station.
As electronics continue to shrink in size, the capabilities of CubeSats continues to expand.  CubeSats can now perform a wide range of sensing and telecommunications applications.  However, CubeSats have been limited in their ability to conduct propulsive maneuvers and to withstand deep space environments.  This limits them to the orbits they are deposited in from their rideshare flight.    ExoTerra's Solar Electric Propulsion CubeSat Bus opens a whole new set of mission opportunities to CubeSats by providing over 1 km/s of dV for CubeSats through its 6U bus.  The bus expands the CubeSat state of the art by implementing 3x higher power solar arrays, high efficiency power distribution and a low power, high efficiency Hall Thruster.  To meet deep space mission requirements, we add guidance and navigation systems, incorporate radiation tolerant electronics and integrate thermal control systems into the bus.  The SEP CubeSat project demonstrates a first of its kind propulsive capability by building, qualifying and flying the SEP CubeSat.  The mission launches from the SLS opportunity in 2017.  After Translunar Injection, the Cubesat uses its SEP system to perform lunar orbit insertion and spiral in, becoming the first Cubesat to successfully perform a capture maneuver at another celestial body.
As part of the FAA's plans for modernization of the Air Traffic Control (ATC) system, Automatic Dependent Surveillance - Broadcast (ADS-B) will be the basis of the future surveillance system in the US, supplemented by the current Radar system. With significantly more frequent updates and higher data quality than radar, ADS-B provides unprecedented access to general aviation operational data. Given this unique opportunity, Aurora proposes to conduct an in-depth analysis of the potential for ADS-B derived operational data to identify operations with a reduced safety margin &amp;#150; similar to the FAA's voluntary Flight Operation Quality Assurance (FOQA) safety program.  Since comprehensive operational data of this quality and magnitude has not been available until now, new and innovative approaches for their analysis are needed. 

Ultimately, the goal of the proposed effort is to provide a "big data" capability for using ADS-B data to identify the underlying causes and pre-cursers for a majority of aviation accidents. The insights from this analysis could then be used to identify approaches for improving aviation safety and lead to recommendations about where to focus educational efforts, recurring training or proficiency checks. These insights may also lead to the re-design or introduction of avionics that specifically address the true underlying causes of accidents.
The proposed innovation will dramatically improve the performance of tritium-powered betavoltaic batteries through the development of a high-aspect ratio, expanded surface area p/n junction composed of indium gallium phosphide.  The enhanced surface area features will be built using reactive ion etch (RIE) modified germanium substrates via metalorganic chemical vapor deposition (MOCVD).  The proposed 3-dimensional betavoltaic p/n junction will provide a cost saving of up to 90&#37;, while increasing energy density to up to ten times that of lithium batteries.  Such an advanced semiconductor device will produce much higher power outputs than are possible with existing state-of-the-art devices.  It will provide the battery a life span in excess of 20 years with the broad-range temperature-insensitivity benefits normally associated with betavoltaics.  This increased power/energy density for tritium betavoltaics will open up pathways for significant advances in power solutions for diminutive sized, low-power microelectronic devices that may be used in Cubesat and in-space power systems.  Example applications include microwatt-to-milliwatt autonomous 20+ year sensors/microelectronics for use in structural monitoring, mesh networks, tagging and tracking wireless sensors, medical device implants, and deep space power where solar is not easily available.  Tritium betavoltaics are capable of addressing this power niche for devices requiring reliable, uninterrupted power through extremes of temperature, longevity and diminutive form factors where traditional batteries cannot operate.
GTL has been developing three transformational technologies that have the capability to disrupt the traditional launch vehicle paradigm.  BHL composite cryotank technology provides a four times improvement over large Al-Li tanks, offering a 6 percentage point improvement in stage PMF.  Superior Stability Engine is an innovative liquid rocket engine configured to maximize combustion stability margin while also maximizing engine performance.  NORPS is a non-helium gas generator system that can be used to pressurize the propellant tanks for 1/3 the mass and 1/10 the volume of a comparable helium based system.
The Advanced Cryogenic Expendable (ACE) Booster design uses these technologies to achieve high performance and low cost in a small vehicle.  When implemented in an optimized design, the ACE technologies offer revolutionary performance.  In the proposed Phase I effort, GTL will perform a conceptual design study to assess the impact of design constraints on the implementation of the ACE technologies.  From this, an optimized design will be developed.  A technology roadmap will be created to show how the capabilities can be achieved in the near term.
This project is directed to the development of low-loss, high power-density Aluminum Nitride (AlN)/Gallium Nitride (GaN) heterostructure based transistors for enabling high-efficiency solid state power amplifiers (SSPA) needed for advancing capabilities of future robotic and human exploration spacecraft. The AlN/GaN heterostructure is a particularly attractive system for switch-mode applications due to the extremely high charge density, high electron mobility, high intrinsic breakdown field, and physical thinness achievable and has seen widespread investigation toward solid-state amplifiers in the recent years. However, very few innovations have been proposed with this heterostructure despite its expansive capacity for various creative device concepts. A new patent-pending multichannel AlN/GaN Field Screening High Electron Mobility Transistor (FS-HEMT) design is described. Preliminary experimental results are presented validating design principles that will eliminate current collapse phenomenon at X- and Ka-band frequencies that has plagues traditional HEMT designs and will ultimately deliver a low-loss switch-mode device.
Advanced robotic systems demand an enhanced vision system and image processing algorithms to reduce the percentage of manual operation required. Unstructured environments, whether man-mad (e.g., International Space Station) or natural (e.g., Mars), present significant challenges to supervised autonomy or fully autonomous systems &amp;#150; advanced perception sensors and associated software are required.  This will be particularly important both for future long duration exploration missions where the transmit (Tx) / receive (Rx) delay will be substantial and a high degree of autonomy will be required to maximize science gain, as well as for telerobotic systems where a human operator is IVA and advanced operations in a short timeline are desired. No solution currently exists for small robotic platforms.  Honeybee Robotics proposes to develop a compact, wide-angle, Light Detection and Ranging (LIDAR) system that is able to detect dynamic changes in the field of view (FOV) and focus the laser scan pattern centered on the area of interest while maintaining a lower-resolution fixed FOV for robotic path planning, navigation, inspection, and identification tasks.
Future human space exploration missions will require advanced life support technology that can operate across a wide range of applications and environments.  Thermal control systems for space suits and spacecraft will need to meet critical requirements for water conservation and adaptability to highly variable thermal environments.  To achieve these goals, we propose an International Space Station (ISS) demonstration program for an innovative Space Evaporator Absorber Radiator (SEAR) technology.  A SEAR system comprises a lithium chloride absorber radiator (LCAR) for heat rejection coupled with a space water membrane evaporator (SWME) for heat acquisition.  SEAR systems provide heat pumping to minimize radiator size, thermal storage to accommodate variable environmental conditions, and water absorption to minimize use of expendables.  In Phase I we will prove the feasibility of our approach by building and testing an LCAR with flight-like internal structures and designing an ISS demonstration experiment.  In Phase II we will design and build a SEAR test module according to ISS flight requirements and demonstrate its operation in ground tests that simulate flight test conditions.
The PMWC Flight Demonstrator Payload is a trash dewatering and volume reduction system that uses heat melt compaction to remove nearly 100&#37; of water from trash while significantly reducing the volume. Recent advances have proven that ORBITEC's HEHO-PMWC is a viable technology for producing 16" square tiles for radiation protection. ORBITEC proposes to enhance the current SOA by repackaging all the components developed under prior SBIR efforts for ISS utilization and to create a test protocol for testing of the system on orbit for radiation effectiveness.  The HEHO-PMWC and other Heat Melt Compactor technology has often been tested piecemeal. The proposed system will contain all systems including the primary processing chamber where the tiles are produced, any necessary avionics, and any necessary support equipment, which includes devices for air removal, contaminant and odor scrubbers, water degassers, and water handling.  Plastic tiles output can be placed within the ISS or within the BEAM (ORBITEC has an excellent working relationship with Bigelow Aerospace). Any and all data gathered during on-orbit testing can be used by NASA to create the next generation of heat melt compaction technology for future manned spaceflight.
TDA Research proposes to develop a computer-controlled lightweight and compact device for aerobic and resistive training (DART) to counteract muscular atrophy and bone loss and to improve the overall wellness of astronauts operating in microgravity.  The DART will be able to provide resistive loads up to 350 lbf and will accurately simulate the load profile of a mass in a 1-g environment. It will also be capable of applying custom load profiles such as eccentric overloading.  In aerobic training mode, the DART will simulate the loads of a rowing machine with loads up to 175. The system will computer-controlled and can automatically calibrate to a user's range of motion. The total weight of the device will be less than 20 lbs and have a compact form factor to enable integration into a small crew module. By using a regenerative energy recovery system, the average power consumption of the DART will be less than 100 W during an exercise session. 

TDA is able to build on previous experience building exercise equipment for NASA and develop the DART in a short timeframe. TDA will prove the feasibility of providing effective aerobic and resistive training with a single device that is lightweight and compact in Phase I. At the end of Phase I a prototype will be delivered to NASA for evaluation. In Phase II we will advance the technology and provide the second generation prototype to NASA for testing on the International Space Station.
Altius Space Machines and MSNW LLC propose the development of a cubesat-scale Multipurpose Interplanetary Deployable Aerocapture System (MIDAS), to provide cubesats with the capability to perform reliable aerocapture and aerobraking missions. The MIDAS system consists of a thin, deployable, Magnetoshell Aerocapture (MAC) electromagnet coil that is deployed outward from the cubesat body using multiple elastically deployed composite STEM booms. The MIDAS system also incorporates into its structure a high-power cubesat-scale roll-out solar array (capable of &gt;5W orbit averaged power even at Jupiter distances), and a high-power burst-mode Loop Yagi antenna for potential deep-space spacecraft-to-Earth ground link communications. While it will not be investigated in the proposed Phase I workplan, previous research at MSNW indicates that the MIDAS technology may also be able to provide shielding against solar flares and planetary radiation belts. The goal is to package this system into 2-3U of a 6U cubesat for missions to Mars, Venus, or Europa. The Phase I workplan will focus on sizing the MAC coil, creating an Active Aerogravity Tour (AATOUR) design tool for sizing MAC hardware for aerocapture missions, designing and sizing the MIDAS structure, analyzing the burst-mode Loop Yagi system to verify it can close a useful data link with Earth (and vice versa), and then designing and prototyping the MIDAS system for packaging and deployment. The Phase I efforts will culminate in the deployment testing of a full-scale MIDAS system. If completed successfully, the Phase I effort will raise the system from a TRL of 2 to 3. Follow-on Phase II efforts will develop and perform development tests on a full Brassboard MIDAS demonstration system, raising the system to a TRL of 4 or 5.
Hyperspectral middlewave infrared and longwave infrared (MWIR/LWIR) imaging systems capable of obtaining hundreds of narrow band (10-15 nm) spectral information of Earth's surface, the atmosphere, and land use in agriculture are of great importance in NASA's Earth remote sensing missions. Existing hyperspectral MWIR/LWIR imaging systems are bulky and heavy and thus not suitable for portable and small satellite applications. This SBIR project aims to develop an on-chip hyerspectral imaging system with integrated narrow-band (15 nm) hyperspectral filers on the pixels of the MWIR/LWIR image array. Successfully developing the proposed innovation will provide an enabling ultra-compact on-chip hyperspectral imaging technology with significantly reduced size, weight, and power consumption suitable for NASA's portable and small satellite earth remote sensing missions. In phase I, the proposed on-chip hyperspctral imaging system will be evaluated and compared with existing technologies. A preliminary MWIR/LWIR photodetector with the integrated plasmonic narrow-band filter will be fabricated and characterized. In Phase II, a prototype of the miniature on-chip mega pixel (1024x1024) MWIR/LWIR hyperspectral imaging system will be developed for laboratory demonstration.
Today, as humans reach beyond the earth to near and deep space, there is obvious and urgent need to augment the capabilities of human astronauts and (ground-) controllers with smarter and more capable automation.  In conventional approaches to human-robot interactions for supervisory control paradigms, coordination often breaks down for a variety of reasons and progress toward interactive goals is often impeded due to the inability of the work system to adapt to context shifts. Hence, human-robot teams can be almost entirely non-adaptive.  To address these complex problems, CHI Systems and the Institute for Human Machine Cognition have teamed to create a human-robot interaction system based on recent theories and tools developed by CHI Systems leveraging cognitive representations of shared context as basis for a fundamentally new approach to human-robotic interaction.   This approach includes a framework for representing context and using it to support decision making and control of automation and will form the core of the proposed solution termed the Context-Augmented Robotic Interaction Layer or CARIL.   CARIL will enable efficient and effective human-robot control-oriented cooperation through the use of adaptive behaviors to mediate cooperation between humans and robots.  Phase I will focus on development and demonstration of the CARIL concept.
The ultimate goal is the automation of a large amount of KSC's planning, scheduling, and execution decision making.  Phase II will result in a complete full-scale implementation of a general framework and its application to several problems at KSC to create several operational systems (e.g., for Ground Processing (GP) and the Cryogenic Test Bed (CTB)) and other systems targeting future, advanced applications (e.g., autonomous cryogenic operations).  During Phase II, delivered applications will improve scheduling of SLS Processing and V&amp;V activity, including reduced scheduler manpower, reduced turnaround time in response to changes and what-ifs, and more optimal schedules; improve CTB Planning and Scheduling; and complete the diagnosis, planning, scheduling, and execution closed loop system for more-automatic ground and autonomous space-based cryogenic operations.  The KSC Engineering Development Lab has substantial development and testing efforts ongoing for automatically diagnosing faults in cryogenic operations.  By interfacing our system to these applications, it effectively completes the closed loop system required for completely autonomous operations.  Our Phase II system will participate in a number of demonstrations during Phase II to prove the capabilities for future advanced more-automatic ground and space-based operations.  Letters of support are included in this proposal from the managers of the groups that would use the operational systems in Phase II and the manager of the project demonstrating future, advanced applications.  This Phase II effort will also improve the ability of SMEs to customize intelligent scheduling systems, capture corporate knowledge, and implement the required interfaces to allow operational use and participation in cryogenic operations demonstrations.
OPTRA proposes the development of a modular, reconfigurable matched spectral filter (RMSF) spectrometer for the monitoring of greenhouse and volcanic gases.  The heart of this spectrometer will be an RMSF core, which can be paired with different fore-optics or detector modules to achieve active point or passive standoff detection of the chemicals of interest.  The RMSF core is comprised of a dispersive spectrometer that images the sample spectrum from 3 &amp;#150; 5.5 micron onto a digital micro-mirror device (DMD) such that different columns correspond to different wavebands.  By applying masks to this DMD, a matched spectral filter can be applied in hardware.  This results in a highly flexible system that can address a wide variety of chemicals by simply updating the DMD masks applied and a wide variety of applications through modular hardware design.  Use of the DMD and a single element detector in place of a conventional FPA results in significantly reduced cost and improved performance in terms of image uniformity, pixel operability, and dynamic range.  The proposed Phase II effort will produce a prototype RMSF core with one set of fore-optic and detector modules for each of the two detection modalities.
Spacecraft for NASA, DoD and commercial missions need higher power than ever before, with lower mass, compact stowage, and lower cost. While high efficiency, space-qualified solar cells are in themselves costly, integrating them into a high performance Photovoltaic Assembly (PVA) using conventional glassing, interconnecting, stringing, tiling and laydown techniques can double their cost in $/Watt. The cost of solar power could be significantly reduced if the design of the Photovoltaic Assembly could be modified, modularized and standardized to be compatible with automated electronic assembly and terrestrial solar panel manufacturing methods. Additional benefits of such an approach include higher quality and consistency, improved qualification traceability, and robustness on thin flexible as well as rigid arrays. During the Phase I effort Vanguard successfully demonstrated automated pick-and-place, electrical interconnection, and adhesive dispensing adapted to our lightweight flexible Thin Integrated Solar (THINS) PVA. THINS uses multi-cell covers and advanced interconnection and encapsulation technology, which enables automated integration of traditional and advanced space qualified solar cells. Engineering economic analysis showed the potential for &gt;30&#37; PVA $/Watt cost reduction, while the encapsulation approach associated with THINS showed enhanced durability in space environments, even at high voltages and extreme thermal cycle environments. During the Phase II Program we will further enhance our automated sub-module manufacturing, and scale the approach to the module level. Automated assembly scale up will be performed while integrating into an existing deployable space structure platform, enhancing the TRL of a high performance high power application of automated cell integration scalable from tens to hundreds of kilowatts, and providing a credible commercialization path, all while reducing solar array costs by more than $150/W.
The proposed research innovation will create a low-cost, intuitive means for people to have multi-fingered interaction with Robonaut 2 and training simulations via tactile shear feedback. This work builds on the PI's prior university research.  Tactile shear feedback imparts friction and shear forces to the user's hand via sliding plates that are built into the handle of the grasped device. These sliding plates rub against the user's skin and induce in-hand friction forces to create perceived force/torque-like sensations despite not being connected to a fixed surface. Translational motions and forces can be portrayed along the length of the handle by moving the sliding plates in unison in the corresponding direction; whereas moving the plates at opposing locations in the handle in opposite directions creates the feeling of the device's handle wrenching within the user's grasp.  

To this novel form of haptic feedback, the PI proposes to add a more intuitive means for a user to interact with virtual and teleoperated environments by allowing the user to open and close his/her grasp as he/she would naturally do when grasping an object.  It is hypothesized that adding the ability for the user to interact by opening and closing his/her grasp will provide improved interaction performance and be preferred by users. The proposed work also creates the ability to individually control the fingers on multi-fingered robot hands like those on Robonaut 2.  

Our developed haptic interface will provide a low-cost means for mission scientists, astronauts, and others to interact with Robonaut 2. The developed interface will also provide greater access for planning and training of EVAs, and could provide a more intuitive interface for ground personnel to operate and supervise robots. Furthermore, the developed system's low cost would also permit it to be used directly in NASA outreach / STEM (Science, Technology, Engineering, &amp; Math) activities.
During the conduct of a NASA Research Announcement (NRA) in 2012 and 2013, the Mosaic ATM team first developed the Strategic Arrivals Recommendation Tool concept, or START. Though this concept was developed in direct response to Miami Center's request to our team to provide a tool that could assist them during the summer convection season, this concept could be applied anywhere in the NAS. Given that the Florida region has some of the most challenging convection to predict, we believe that if START can be successful for ZMA, it can be adapted to support TMUs in other areas of the NAS where convection is an issue.

START is the use of en route weather translation and airspace capacity models to the challenge of strategically planning arrival flows in advance of expected capacity reductions due to convective weather. START provides probabilistic en route capacity estimates for corridors used by arriving flights, models the impact of capacity reductions on traffic, and then provides recommendations for strategic Traffic Management Initiatives that better balance demand and capacity given the uncertainty in the weather.
In Phase I, our objective is to demonstrate the feasibility and potential benefit of the START automated recommendations concept. We intend to accomplish this by developing and testing specific algorithms that will be necessary to achieve this goal and providing a preliminary benefit assessment of the concept.  These include the airspace capacity model and the reroute recommendation optimization model.

Our Phase II objectives are to integrate the algorithms developed in Phase I into the START prototype software. We will continue to work with Miami Center and American Airlines to vet START as the capabilities mature, ensuring that the tool is meeting the needs of the Traffic Management Unit specialists and airspace users. Through the accomplishment of the Phase II activities, START will be ready for full field evaluations to be conducted by NASA.
This project will develop geotechnical measurements, sample extraction and transport equipment for subsurface regolith on NEOs, asteroids, moons and planets, enabling accurate evaluation of subsurface composition and chemistry.  Non-contact measurements can provide preliminary information regarding bulk density and composition; however, more accurate assessment of a bodies' composition and evaluation of potential resources, their abundance and ease of recovery will require physical contact with the surface, and penetration or drilling down to depths that are not subjected to significant space weathering. Such surface-contact and sampling probes will enable physical and chemical characterization of unweathered subsurface material. Inertial and autonomous percussive penetration to depth, along with novel drilling and tailings-transfer approaches, will be developed to both attain the required depth, and to advance semi-autonomous sample-collection/recovery technology so as to minimize the need for operator (or tele-operator) involvement.  Both core- and bulk-regolith sampling methods which minimize loss of volatiles, will be developed. To the extent feasible in the laboratory, this project will approximate key features of reduced-gravity conditions both physically and in particle-scale numerical simulations to ensure that the methods developed will function in realistic environments. The primary aim of this study will be advancement of technologies suitable for use on robotic precursor characterization-missions, with the anticipation that further-improved versions of the same methods will minimize the time and effort of human intervention/involvement during follow-on exploration or prospecting missions. In addition, the feasibility of novel extraction, transport, handling, and storage methods for bulk regolith material, which minimize loss of volatiles, will be developed. Such developments will be especially useful for in-situ resource evaluation and utilization.
The NASA's PATH mission employs a synthetic aperture radiometer that produces 768 IF (10MHz - 500MHz) signals. Digitizing the signals results in 1.536Tb/s (1GS/s, 2-bit) data stream. Within the NASA's SBIR contracts NNX12CE50P and NNX13CP01C, Pacific Microchip Corp. has developed a low power 64x64 cross-correlator ASIC offering the reduction of the amount of data to manageable levels. This ASIC includes an array of 128 digitizers operated at 1GS/s and 2-bit precision. This ASIC is the key component in the proposed cross-correlator system for the PATH mission. The innovation offers to greatly reduce the power consumption, weight and the system's complexity. Phase I will demonstrate the feasibility of implementation of the system based on the developed ASIC. We will design the cross-correlator system's schematic, its behavioral model and will run the simulations proving the requirements of the PATH mission can be met. The PCB will also be designed to prove the feasibility of the system's physical implementation and meeting electrical and thermal requirements. Phase II will result in the complete system's assembly, its electrical and thermal characterization and validation on the PATH's radiometer which is being developed at JPL.
Cubesats require highly compact technologies to maximize their effectiveness.  As cubesats are expected to be low-cost and, relative to the space industry, mass produced, their technologies should be simple to manufacture, yet achieve aerospace quality standards.  This proposal aims to describe a novel high-efficiency (i.e., comparable to solar panels) fabricated power supply for cubesats and other small satellites that has marked advantages over solar photovoltaic cells.
Nanohmics Inc. proposes to develop and test a compact, high efficiency solar thermoelectric generator.  The technology is amenable to mass manufacturing and is based on recent development successes at Nanohmics: thermoelectrics development and coatings to maximize emissivity.  On a space vehicle, the energy generator would be deployable in a number of ways including a folding fan-like unpacking or other compact designs.
Aerobraking and aerocapture have been shown to be mission enabling for deep space orbiters and manned missions, and yield dramatic cost and mass savings for near earth missions. However, high dynamic pressure aerocapture is high risk and requires large, complex, and heavy deflector shells. Magnetoshell Aerocapture (MAC) is a revolutionary technology that has been developed by NASA and MSNW that can enable low-cost, low-risk aerocapture for a range of Earth and deep space missions.

The Magnetoshell deploys a simple dipole magnetic field containing a magnetized plasma. Interaction of neutral particles in the atmosphere with this magnetized plasma produces the desired drag for braking, acting in effect like a plasma parachute. With the aeroshell now being composed of a massless magnetic field, the scale of the shell can be as large as 100 meters with only a gram of plasma and a simple copper magnet. Drag can be dynamically controlled in response to atmospheric conditions, enabling very aggressive aerocapture maneuvers. By providing pulsed power, the thermal and power processing requirements can be kept within the scope of conventional technologies.

In a Phase I NIAC program a 1.6 meter diameter Magnetoshell was demonstrated and increased the drag force of a supersonic flowing neutral jet by 1000X. A wide range of mission studies showed that MAC can enable a Neptune orbiter mission, reduce the cost of a manned Martian mission by $2B, and provide the low-cost drag system for Earth return missions. 
In the following proposal a three year ISS-launched CubeSat demonstration mission paves the way for full scale operation missions. In Phase I a complete system design will be completed and several of the primary technology risks will be mitigated. When demonstrated, Magnetoshell Aerocapture will dramatically reduce cost and risk for applications ranging from nanosatellites, deep space Flagship science missions, and commercial applications such as reusable tankers.
The Robust Analytics air traffic management cost assessment tool provides the comprehensive capability to analyze the impacts of NASA Airspace Systems Program (ASP) air traffic management (ATM) research from individual flight trajectories through airline network operations and airline investments in equipment and training. Our model generates cost-benefit estimates for concept and procedure alternatives for individual airlines. The model also estimates a variety of impacts on industry, including input utilization and productivity, throughput, air transportation industry costs and fares, and broader economic effects such as employment and benefits to other industries.
Existing cost models are typically limited to simple flight cost factors, with occasional added detail on fuel burn and flying time. Assessment of deployment times, the feasibility of obtaining the assumed benefits, and cost risk are typically ignored although always a constant concern of airlines. 
Our model suite overcomes these deficiencies by providing greater fidelity in the cost analysis of flight segments, explicit estimation of training and certification cost, and realistic treatment of deployment time and risk. Our cost analysis is performed using airline-specific data, enabling more realistic assessment of airline investment decisions and identification of disparate effects and willingness to invest among airlines. Robust Analytics expect to leverage the current body of knowledge by our partner Sabre Airline Solutions and two U.S. airlines to provide input and validate the model. An important use of the proposed model for the airline industry is that potentially this tool could help them make decisions in real time to improve their decision making during irregular operations and during severe weather events.
Aether Industries proposes the development of a novel, primary plasma propulsion system that is well suited for small spacecraft. This technology, called the CubeSat Ambipolar Thruster (CAT), would provide CubeSats and other micro- and nano-satellites with the propulsive capability to make meaningful orbital plane and altitude changes &amp;#151; capability that does not currently exist with state-of-the-art micropropulsion technologies. As such, the CAT engine is an enabling technology that supports NASA, commercial, university, and military CubeSat needs from constellation deployment to lunar orbit insertion and beyond. In the CAT engine, a high-power  RF plasma discharge is expanded adiabatically along a magnetic nozzle topology established by permanent magnets. A resultant ambipolar electric field accelerates the ions to high energies to generate thrust while retaining high propellant utilization. The CAT engine offers a means of providing efficient and high thrust-to-power primary propulsion for CubeSats and microsatellites. The CAT engine promises to change the CubeSat paradigm from passive sensor carriers to fully capable mission-completing spacecraft. Successful implementation by our team will result in the transition of technology developed  into the commercial sector by a small business, the engagement of the next generation of the space sector workforce, and the infusion of an advanced in-space propulsion technology for future NASA, commercial, and government missions.
Motivated by the anticipation of pilot shortage in the future and the quest of cost reduction in airline operations, the single-pilot operation (SPO) concept emerges as a promising alternative of the current-day multi-pilot operations. This proposal addresses the feasibility of constructing a spoken language understanding system for decoding voice communications in Air Traffic Control. In particular, we address the issue of developing a voice communication understanding system (VCUS) that would serve as one key component in both cockpit automation and ground-based automation for supporting the SPO concept. Leveraged from our prior development on noise-robust speech recognition system for the Navy and virtual agents for NASA to support human-in-the-loop simulations, an infrastructure of VCUS in Air Traffic Control of commercial flights will be developed. A feasibility demonstration of the VCUS that extracts out semantic information for persistent display of clearance message within the flight deck will be provided by the end of the Phase I research. Phase II work will utilize the infrastructure built in Phase I to expand the VCUS to a full-scale prototype that supports cockpit automation and ground-based automation for SPO.
A significant portion of the NextGen research is aimed at (i) developing ground-side automation systems to assist controllers in strategic planning operations such as scheduling flights, and (ii) developing tactical controller decision support tools to separate and space the traffic. Central to the success of these automation systems is the ability to predict the future trajectory of any aircraft in the National Airspace System (NAS). The research related to this area is referred to as Trajectory Prediction (TP) and sometimes Trajectory Synthesis. Notwithstanding past research, TP remains a very challenging exercise and the quest for improved TP accuracy continues. Any improvements in TP can benefit a wide array of NextGen concepts pursued by NASA. The objective of the current research is to seek a novel approach to TP specifically aimed at addressing some of the deficiencies of the past TP research. The approach involves: (i) machine learning algorithms, and (ii) big data computational platforms.

Phase I research will demonstrate the benefits of supervised and unsupervised machine learning algorithms for TP. Phase II research seeks to develop real-time trajectory prediction algorithms that can be used for a wide variety of NASA NextGen concepts.
A spaceborne radar system that operates simultaneously at multiple frequency bands from microwave through millimeter-wave frequencies can exploit the largely varying frequency response of electromagnetic radiation to various atmospheric conditions, thus forming a highly-capable remote sensing system for NASA earth science objectives such as cloud and precipitation monitoring. We propose the development of an electrically scanned, co-located Ku/Ka-band (13.4/35.6 GHz) linear array in the Nuvotronics PolyStrata&amp;#174; technology for integration with an electrically scanned W-band (94 GHz) linear array to form the feed for a three-band remote sensing system. The PolyStrata&amp;#174; wafer-scale microfabrication process, with the capability to monolithically integrate dielectric-free antenna arrays with ultra-low-loss air-coax feed networks in three-dimensions, will be a key enabler of achieving the state-of-the art performance requirements for front-end losses at the desired operating frequencies as well as the desired scalability to 2-3 meters. Unprecedented transmit efficiencies and power levels will be achieved by leveraging Nuvotronics' history of developing Gallium Nitride (GaN) power amplifiers and low-loss switches at similar frequencies.  A prototype hardware demonstration of the co-located Ku/Ka-band antenna array fabricated in the PolyStrata&amp;#174; process will be provided.
IFOS proposes to design and build fiber-optically sensorized robotic fingers that can sense force and, objects using only tactile feedback, similar to the skin on a human hand. The innovation, employing fiber optic sensors, will b integrate the highest-density EMI-immune optical sensing for robotic hand systems to enable human-like tactile sensing capabilities.  The innovative high-density manipulative system will add great dexterity to robotic hands and will be fully adaptable to performing complex Extravehicular tasks. In Phase I, IFOS will design a robotic hand and fingers system, focusing on the skin and muscle hardware requirements for tactile and force feedback information to be relayed to a central processor, which will then identify objects based on tactile feedback and provide a full haptic sense.  A proof-of concept experiments planned for Phase I will demonstrate gripping and grasping using a sub-scale sensorized set of fingers. Results will be used as input for prototype planned for Phase II, along with preliminary test and evaluation recommendations for potential insertion into an advanced Robonaut servicer.
Radiation-hardened non volatile memory (NVM) is needed to store the golden copy of the image(s) has not kept pace with the advances in FPGAs. Consider that a single image of a Xilinx V5 FPGA typically is roughly 50 Mb large. If a designer wants to store several such images in a satellite, then a sizable amount of highly reliable, radiation-hardened memory is needed. Traditional Rad hard memory for space (CRAM, FRAM, MRAM) is not sufficiently dense and extremely expensive. As a consequence, there exists a clear need and market opportunity for highly reliable, higher density, NVM for storing program code, calibration tables and images of reprogrammable FPGAs. The goal of this SBIR project is to develop a highly reliable and fault-tolerant, radiation-hardened hermetic memory multi chip module (MCM), which can be used to configure and scrub reconfigurable FPGAs. The MCM will contain a simple radiation-hardened microcontroller and three (3) commercial flash nonvolatile memory (NVM) devices which have been radiation characterized. Our integrated device will support the needed standard interfaces that are commonly used for reconfiguring FPGAs, including Xilinx SelectMAP and JTAG. The output of our Phase II SBIR is a 32Gb device which meets at least 150Krads (Si) total dose. Space Micro has full capability to introduce and market this device into the international space business market.
ChemImage Sensor Systems (CISS), teaming with the University of South Carolina, proposes a revolutionary wide-field Raman hyperspectral imaging system capable of meeting the stated needs. The proposed innovation couples a spatial heterodyne spectrometer (SHS), a novel slit-less spectrometer that operates similar to Michelson interferometer, with a fiber array spectral translator (FAST) fiber array, a two-dimensional imaging fiber for hyperspectral imagery, to create a novel wide-field, high throughput Raman hyperspectral imager capable of yielding very high spectral resolution in a small form factor. The system can be configuredin both benchtop and standoff configurations. A standoff configuration is beneficial for any rover based mission, since it does not require close contact to the analyte of interest and Raman can interrogate targets up to 100 meters away.
Radiation Hardened Application Specific Integrated Circuits (ASICs) provide for the highest performance, lowest power and size for Space Missions. In order to dramatically reduce the development cycle and reduce the cost to tapeout Rad Hard ASICs, we propose a Structured ASIC approach. In this approach we fix an array of complex logic cells and provide a fixed Area Array for I/O pads supporting in excess of 400 CMOS GPIO pins. In addition, we fix the power grid and the pins associated with power (core and I/O) and ground.  Thus, we require only routing in a subset of the metal layers in order to configure the Structured ASIC to a specific design. This leads to substantial reduction in design and verification time to tapeout, and results in reduced cost by requiring a subset of Mask changes per design. In this work, we will build on existing 90nm Silicon proven Radiation Hardened Structured ASIC platform and develop a Structured ASIC platform at the 45nm SOI technology node with the objective  to increase the clock speeds to hundreds of MHz with SEU mitigation in sequential logic. We will also use High Density Interconnect (HDI) for packaging the Die in BGA and LGA packages. The HDI design does not change for each configuration of the Structured ASIC so that the same benefits of Structured ASIC are extended to packaging the part with high pinout and high speed I/O requirements eliminating layout design costs.
In the ATM Select topic area of Integrated Arrival, Departure and Surface (IADS) planning, this proposal addresses Tactical Departure Scheduling (TDS), which is a commonly used procedure in the NAS. It is estimated that approximately 60,000 flights each month are subject to tactical delays via TDS, which is approximately 3.5 times the number of flights that are impacted by strategic Traffic Management Initiatives (TMIs).  Despite recent advances in tactical departure scheduling like that demonstrated in NASA's Precision Departure Release Capability (PDRC), little is currently known about the overall effect on the NAS when implementing tactical events.  In fact, today no comprehensive guidance exists for FAA personnel to determine which TMI to use for a particular traffic problem, the duration of that TMI and the recommended control parameters. 
An integrated decision support capability is needed to provide ATM specialists and flight operators with information to support planning and decision-making about tactical and strategic TMIs. The significant challenge that exists in providing this decision support capability is the uncertainty of prediction of both demand and capacity.
To address this current shortfall of the National Airspace System (NAS), Mosaic ATM proposes to conducted detailed research on the interrelationship between IADS scheduling and metering capabilities and other TMIs. The output of this research will be both mathematical and simulation models that characterize and quantify the relationship between IADS capabilities and other TMIs. These models will provide guidance and input for further NASA research efforts and activities, and they will also provide real-time operational decision support for Traffic Management Coordinators (TMCs) and other ATC specialists.
Improved hyperspectral imaging technologies could enable lower-cost analysis for planetary science including atmospheric studies, mineralogical investigations, and geological mapping.  Traditionally, multispectral imaging (beyond RGB) requires numerous optical filters, complex spectroscopic instrumentation, or massive systems.  A compact system that enables real-time hyperspectral imaging or long-term averaging without moving parts could revolutionize planetary observation techniques.
Nanohmics, Inc. proposes to develop a novel on-chip hyperspectral imaging system for use in planetary missions.  The hyperspectral system can be integrated with existing commercial-off-the-shelf imaging systems, providing an immediate route towards commercialization.  The compactness will enable the technology to be applied in a variety of mission environments ranging from Flagship-class programs to cubesats.
Innoflight proposes developing a 0.5U Deep Space Cubesat Regenerative-ranging Transponder (DeSCReeT) compatible with NASA's Deep Space Network (DSN) and similarly capable ground assets and with flight-ready units available for CubeSats deployed in cis-lunar space via the Exploratory Mission 1 (EM1) program. The transponder will leverage Innoflight's flight-heritage Software-defined Compact Radio (SCR) family of radios.

Phase 1 design efforts include requirements gathering from Pre-Phase A and Phase A CubeSat missions, Forward Error Correction trades, X-Band versus S-Band trades, and radiation-tolerant component trades. Given the EM-1 timeline, the Phase 1 effort will successfully complete a CDR-level design by the end of the period of performance.
The proposed innovation builds on the successes of the Phase I program by integrating our direct oxidation membrane electrode assembly (MEA) into a monolithic solid oxide fuel cell stack (SOFC) capable of long-term operation on methane or syngas. This innovation is significant because it will contribute to durable, cycle-able simple SOFC systems to meet the needs for NASA and commercial customers.
ITN's Phase II strategy addresses the technical hurdles that limit the long-term durability and thermal cycling of state-of-the-art SOFCs operating on methane fuel, including
:
&lt;ul&gt;
&lt;li&gt;Matching stack components for coefficient of thermal expansion
&lt;/li&gt;
&lt;li&gt;Reducing stack mass&lt;/li&gt;
&lt;li&gt;Stack sealing&lt;/li&gt;
&lt;li&gt;Reducing anode degradation, and
&lt;/li&gt;
&lt;li&gt;Reducing operating temperatures.&lt;/li&gt;
&lt;/ul&gt;
With this innovation, we project that the proposed SOFC stack will be capable of operating without degradation for more than the targeted 2500 hours and will operate without power density degradation after 50 start-up and shut-down cycles. By utilizing the direct-oxidation membrane electrode assemblies developed in the phase I program, the thermodynamic efficiencies from fuel source to DC output should exceed 70&#37;. Higher efficiencies translate to lower cooling requirement as obtained by way of conduction through the stack to a radiator exposed to space and/or by anode exhaust flow.
Low-Frequency, All Digital Radar (ADR) can be a key component for NASA Phased-array and tomographic Radar systems spanning multiple earth-science measurement objectives. One of the key attractions of ADR is hardware re-use for different scenarios. Intelligent Automation Inc. (IAI) proposes the design of an ADR system to meet the technology requirements listed in this solicitation. State-of-the-art technologies in the design of data conversion devices like Analog-to-Digital Converters (ADC), Digital-to-Analog Converters (DAC), Direct Digital Synthesizers (DDS) and reconfigurable logic devices like Field Programmable Gate Arrays (FPGA) MMIC make it possible to realize the concept of ADR with low SWaP and low-cost goals. The proposed ADR will build upon IAI's Software Defined Radio/ Radar (SDR) design expertise. Our proposed approach is modular, scalable and meets the NASA goals of multi-channel, coherent altimeters along the cross track to obtain high resolution in the cross track direction.
The proposed novel program will use measurements of high-energy photon output from celestial gamma-ray sources to design a new, unique navigation system for a deep space CubeSat demonstration. An integrated CubeSat design will be developed to demonstrate the performance and feasibility of the Gamma-ray source Localization-Induced Navigation and Timing, or "GLINT", technology and software developed under a previous NASA Phase I SBIR. In this past research, our team established the feasibility of using photons from gamma-ray bursts (GRBs) to provide deep-space vehicles the capability for self-navigation, showing that with key improvements to detector and timing instrumentation, the technique could achieve three-dimensional position accuracies of less than one kilometer. In this proposed research, recent developments in these hardware components will facilitate the design of a high resolution GRB monitor and precise timing circuit board, which, due to their size, weight, and power requirements, are prime candidates for integration into a 6U or smaller CubeSat. The mission proposed will fly two 3U-sized CubeSats equipped with this system, which will use time differenced of arrival measurements from the same observed GRB to determine a relative position solution. The GLINTSAT demonstration mission will measure the performance capabilities of this system. The team will design the mission architecture, including system requirements and components. An advanced photon timing instrument board will be designed, along with an accompanying high-resolution gamma-ray detector. Integration into the 3U CubeSat design will be detailed. Navigation performance will be evaluated using the designs and a prototype laboratory relative timing experiment. An integrated system error budget will be produced and the mission performance will be assessed to establish the feasibility and detail the path to environmental testing and full CubeSat system development for a 2017-timeframe launch.
Acute challenges are faced by the designers of fluid transport systems for spacecraft because of the persistently unfamiliar and unforgiving low-g environment. However, with modern design tools capillarity can used to passively perform critical life support functions, increasing reliability, while enabling new device functionality. Such systems are directly tied to critical life support systems: i.e., oxygen supply, air revitalization, thermal management systems, water reclamation, medical fluids, and others. 

In this work IRPI will apply the Phase I design process toward the development of a much needed contingency waste water collection and processing device for human spaceflight. The device provides passive liquid collection, containment, bubble separation, and droplet coalescence functions for contingency urine collection in a lightweight, low volume, low cost, and potentially disposable device that may be used for subsequent sampling, metering, storage, disposal, and/or re-use. Our approach will include "fractal wetting" and design that incorporates "smart" capillary fluidics. Though the work is focused on a single application, the design approach and capabilities have a broad impact on capillary-based fluids management aboard spacecraft and on earth.
During this Phase II program Dimension Technologies Inc. (DTI) proposes to design and build an autostereoscopic (glasses-free 3D) LCD based aircraft cockpit display that features switchable 2D &amp; 3D operation, full LCD resolution in both 2D and 3D modes, a wide viewing area without head position restrictions, and high brightness.  The display will be configured for installation and testing in a Boeing 787 cockpit simulator for evaluation and testing at the end of Phase II. Given positive results this could be followed by modification and installation in a test aircraft in Phase III.  The display will be based on Rockwell's 15" flight deck displays currently in use and be designed to fit inside the existing display volume envelope.  Code will be written to allow Boeing's existing simulator software to produce 3D images on DTI's displays.  Presentation of images in 3D should increase the pilot's ability to extract information, particularly situational awareness from cluttered displays, as indicated by various studies at NASA and the US Air Force.  Boeing has agreed to partner with DTI in Phase II.
For spacecraft design and development teams concerned with cost and schedule, the Quick Spacecraft Thermal Analysis Tool (QuickSTAT) is an innovative software suite that will significantly reduce labor costs and effort associated with the design, analysis, and optimization of spacecraft. Unlike traditional analysis where highly-trained engineers spend days to months developing, running, and evaluating high-resolution models, QuickSTAT provides the similar results in near real-time to a broader range of users. QuickSTAT will enable, on one hand, highly skilled thermal engineers to more effectively explore complex design spaces, while on the other hand give better engineering design access to less skilled engineers and program stakeholders. For thermal analysts involved in multi-dimensional trade studies, QuickSTAT provides the means to rapidly compare hundreds or thousands of discrete design points and identify trends that lead to more optimal design solutions. For designers of low-cost spacecraft, QuickSTAT can enable quick and efficient thermal design trade studies without investing in a high-end thermal analysis tools.
The overall technical objective of this multi-phase project is to develop and validate a so-called 'AAW-Process' that consists of (i) the Active Aeroelastic Wing (AAW) technology of employing multiple control surfaces in tandem for achieving loads alleviation and drag minimization using the over-determined trim capability of ZONA Euler Unsteady Solver (ZEUS), and (ii) the aeroelastic tailoring technique for optimum stiffness distribution and weight minimization while satisfying structural design constraints using ZONA's Automated STRuctural Optimization System (ASTROS). The technical objectives specific to Phase II effort are twofold: (1) Analytically design the four Subsonic Ultra Green Aircraft Research (SUGAR) wind-tunnel models that employ Distributed Multiple Control Surfaces (DMCS) and Variable Camber Continuous Trailing Edge Flap (VCCTEF) to achieve the weight and drag benefits, and (2) Fabrication of one of these four designed models to validate the AAW-process experimentally by a future wind tunnel testing. As per the first specific objective, four wind tunnel models will be designed for high speed Transonic Dynamic Tunnel (TDT) testing along with their detailed fabrication and wind tunnel testing plans. These four models are carefully chosen to incrementally demonstrate the benefits of applying AAW technology and aeroelastic tailoring technique by potential future fabrication and wind tunnel tests. As per the second specific objective, the fabricated wind tunnel model will be delivered to NASA along with its target performance improvement predicted by AAW-process for validation with a near-term wind tunnel testing. In order to ensure the safety of the wind tunnel models during the TDT testing, flutter suppression and gust load alleviation controllers will be designed for those models that are not aeroelastically tailored and have analytically displayed potential flutter instability problems.
CU Aerospace proposes to perform design, fabrication, and ground test validation of a nanosat primary propulsion subsystem using non-toxic R134a propellant. Our approach, called CubeSat High Impulse Propulsion System (CHIPS), leverages CU Aerospace's very high efficiency warm-gas variant of an innovative resistojet that significantly boosts the performance of standard cold-gas systems with the existing Micro Propulsion System (MiPS) thruster technology development by our team partner, VACCO Industries. The MiPS system has been tested to 200,000 cycles without any technical issues, demonstrating excellent reliability. A 1.5U CHIPS subsystem, using non-toxic R134a propellant, is a compact thruster system having a total impulse of 680 N-s and a fully throttleable continuous thrust of 30 mN. The subsystem also includes an R134a 3-axis cold-gas attitude control system to replace reaction wheels.  Approximately 25 W of primary power is required from a lithium-ion battery included in the 1.5U package. This low-cost subsystem demonstration will pioneer a family of nanosat propulsion systems, which will become available to the CubeSat and nanosatellite communities for orbit change, de-orbit, precision maneuvering, and drag makeup missions.
Paragon Space Development Corporation (Paragon) and ENrG Incorporated (ENrG) are teaming to provide a highly efficient reactor for carbon monoxide/carbon dioxide (CO/CO2) conversion into methane (CH4). The system is a gravity-independent, compact, leak-tight, Solid Oxide Electrolyzer (SOE) system with embedded Sabatier reactors (ESR). Applying Corning Incorporated (Corning) Intellectual Property (IP), ENrG and Paragon can leverage an all-ceramic, efficient, and low mass solid oxide fuel cell (SOFC) that remains leak-tight after hundreds of thermal cycles. Paragon proposes that incorporation of the all-ceramic technology into our SOE/ESR system will result in a design that will: 1) be thermally shock tolerant and capable of hundreds of on-off cycles at faster cycles than compared to the metal-to-ceramic SOE designs, 2) be lighter, smaller, and require less power than existing designs, 3) allow for high (&gt;90&#37;) single pass utilization of feedstock, and 4) achieve a thermodynamic efficiency of up to 80&#37;. Our Phase II effort includes laboratory tests to optimize operation of an all-ceramic design for increased single pass utilization of the feed stock and mitigation of carbon deposition. Engineering analyses and component testing will be performed to inform the design of a stack. The stack will be built and tested to verify requirements. Results will be used to size a full system with recommendations for integration.  An engineering development unit will be built and delivered to NASA. Integrating cells that operate as either an electrolyzer or a Sabatier reactor simplifies operations, lowers hardware complexity, and increases reliability. The proposed system can perform multiple functions without modifications, making it a readily deployable technology for various missions from ISRU on the Moon and Mars to regenerating 100&#37; of a crew's oxygen in spacecraft or habitats.
Thorleaf Research, Inc. has demonstrated feasibility in Phase I and now proposes a Phase II effort to develop a miniaturized high flow, low dead-volume preconcentrator for monitoring trace levels of contaminants in liquid water under microgravity conditions. Our innovative design for the preconcentrator combines high water sampling flow rates with low dead volume, thus enhancing preconcentration. This is designed to meet monitoring needs for NASA's Spacecraft Water Exposure Guidelines (SWEGs) and addresses a key technology gap for long-duration human spaceflight, since standard techniques will not function without gravitation to stabilize phase boundaries. Human exploration of the solar system will depend on such technology, since water must be recycled and the option of returning grab samples to Earth for analysis from beyond low-Earth orbits does not exist.  

During Phase II, we plan to incorporate this technology into a miniaturized water preconcentrator module. Based on our Phase I results we project that it will be possible to develop this module with a mass of about 0.5 kg and average power consumption of &lt;1 watt.
NASA's future X-ray astronomy missions will require X-ray optics that have large effective areas, are lightweight, and cost effective.  Recent X-ray telescopes, such as the Chandra Observatory, utilized reflectors made from zerodur which were up to 20mm thick.  The thickness of these reflectors, as well as the mass, limited the number of nested optics that could be implemented.  Current state of the art telescopes, such as those found on XMM-Newton, utilize reflectors made from an electroforming process with shell thicknesses on the order of 1mm.  This reduction in thickness has enabled a larger number of reflectors to be implemented, 58 nested reflectors in the case of XMM-Newton, but the weight still needs to be significantly reduced for future missions.  The proposed innovation seeks to improve upon the current state of the art by replacing much of the NiCo with a stiff, lightweight, ceramic material.  A thermal spray process, which was tested for feasibility in Phase I, will be enhanced to allow for the deposition of porosity graded alumina onto the rear surface of the NiCo reflector. Several diagnostic techniques will be employed to adjust the in-flight particle state as well as the residual stress of the coating as to not adversely affect the micro roughness of the optical surface as well as the figure accuracy of the optic. The gradation of the alumina layer will allow for CTE matching with the electroformed shell as well as optimization of the ceramic stiffness.  By reducing the NiCo layer from 1mm to less than 100um with a 200um alumina layer as the support structure the overall mass of the telescope can be greatly reduced allowing for a greater number of reflectors to be nested.
Optical communication links provide higher data transfer rates with lower mass, power, and volume than conventional radio-frequency links. For deep space applications at long operational ranges, high performance stabilization of the space terminal data link is required. To meet this need, CDI has developed a novel application of our free-floating isolation platform. Based upon a Shuttle-proven technology, this approach yields 6-DOF isolation from the disturbances of the host vehicle while providing high-bandwidth active stabilization to attenuate both payload disturbances as well as any residual disturbances transferred from the base across the power/data umbilical. The proposed approach is designed to achieve better than 0.5microradian-rms stabilization for all frequencies above 0.1Hz when operating on a spacecraft.

Phase I developed the design concept, demonstrated robustness through sensitivity studies, demonstrated performance through simulation, and establish the feasibility of the approach to meet the space terminal isolation requirements. Component testing of the sensors and actuators further demonstrated that the design will meet the performance requirements. These tests and analyses advanced the technology to TRL-4.

Phase II continues the development by ground testing an end-to-end prototype on a soft suspension testbed to demonstrate overall performance in a simulated low-g operational environment. Both acquisition search and beacon track will be demonstrated. Iterations of development and environment testing are performed to produce several space qualified 2-axis strut assemblies for delivery to NASA. Three strut assemblies rigidly mounted to any space terminal will provide 6-DOF isolation and high-bandwidth stabilization. These struts are designed for robustness so they can be used as an add-on to any rigid structure, thus enabling a broad range of space applications that require high-precision stabilization, isolation, and pointing.
The program delivers a completely new technology solution to isolation and sensing of power flow (current and voltage).  Based on striction materials technology, these small isolation and sensing devices replace Opto-isolation, Hall-effect and Magnetic Transformer isolation and sensing with a lower cost and lower risk solution.  The elimination of optical, processor and magnetic components in the design means that these devices are inherently both rad hard and EMI immune.  The technology provides superior voltage isolation (ground loop elimination) in a smaller package size.  They also will be capable of reliably operating over significantly wider temperature ranges  (-55C to 200C) than is readily available to most NASA missions.
Numerous ground test and wind tunnel facilities are used extensively to generate forces and moments as well as surface measurements of test articles required to validate computational tools used to extrapolate wind tunnel data to realistic flight conditions and hardware.  Accurately mapping velocity flow fields remains a significant challenge in these facilities.  In addition, spatially and temporally resolved measurements of flow parameters such as density, pressure, and temperature are of paramount importance.  Intrusive probe type devices disturb the flow field while traditional particle-seeded techniques are not feasible in shock layers or stagnation regions.  Seeded molecular tagging approaches can not only alter the mean flow, but also introduce unsteady disturbances and requires sufficient upstream seeding in order to diffuse into the boundary layer.  Additionally, seeding can contaminate the tunnels, can become expensive, and reduce the effective run time.  This proposal offers an integrated package of truly cutting-edge, multidimensional, seedless velocimetry and flow diagnostics for ground test facilities.  The concepts and ideas proposed are ranging from proof-of-principles demonstration of novel methodologies using kHz-rate femtosecond (10-15 sec) duration laser sources to measurements in realistic tunnel conditions expected in the current solicitation.  In addition, the technologies and tools developed will be packages into robust and user-friendly testing platforms enabling dual use capability in both ground and inflight-test environments.
State-of-the-art additive manufacturing technologies for metal parts have evolved primarily around powder metallurgy and fusion welding-based processes.  These processing methodologies yield parts with inferior mechanical and physical properties as compared to wrought metal of the same composition.  Additionally, the production rates for even the fastest processes are relatively low, the part envelopes are limited to a few cubic feet, and often the process must be conducted in an atmospherically controlled chamber.  Aeroprobe's additive friction stir (AFS) process is a novel high-speed, large-volume wrought metal additive manufacturing technology that will enable affordable, full-density, near net-shape component manufacturing from a wide range of alloys, including aerospace aluminum alloys, nickel-based super alloys, and metal matrix composites.  The ability to rapidly fabricate large-scale, complex wrought and functionally graded aluminum components from three-dimensional models will be an enabling manufacturing advancement in exploration launch vehicle fabrication, for parts such as those on the Orion Crew Module. A scaled representation of the window frame structure proposed for the Orion Crew Module was fabricated from 6061 Al using Aeroprobe's additive friction stir process during the Phase I program.  To move AFS up the TRL ladder to full-scale demonstration and deployment, two major technical objectives must be met: (1) develop process/structure/property relationships for AFS deposition of aluminum aerospace alloys, such as 2219, which can be used for process control and material property optimization; and (2) demonstrate net-shape, large-scale aluminum launch vehicle and aerospace components (including a functionally graded structure) with mechanical properties comparable to traditional wrought metals.
Alphacore, Inc. proposes to design and characterize a 24Gsps (giga-samples per-second), 6-bit, low-power, and low-cost analog-to-digital converter (ADC) for use in a wide range of NASA's microwave sensor based remote sensing applications.  The goal of this program is to provide an ultra-high-speed, low-power ADC that does both, provides excellent interfacing capabilities to top FPGAs and also has an optimized low-power spectrometer DSP backend available to be integrated on the same chip. The proposed ADC employs an innovative topology with high-bandwidth front-end sampling circuit combined with a flash-type ADC and encoder circuitry that simplifies FPGA interfacing. Innovative and effective digital calibration is used to guarantee spurious free Nyquist frequency band which is an important requirement in remote sensing applications.Comparable commercial ADCs are based on expensive and power-hungry bipolar transistor technologies such as indium phosphide (InP), gallium arsenide (GaAs) and silicon germanium (SiGe). Alphacore designs take advantage of the latest low-power, high-speed digital CMOS processes, resulting in ADC power consumption that is less than 1/8 of the power consumption of competitor ADCs. Using a CMOS process provides additional advantages in that we can leverage existing intellectual property (IP) to enhance the system-level integration of the ADC, e.g., on-chip digital calibration logic, data buffer memory, high-speed transceiver logic, and direct on-chip DSP capabilities.
The Phase I project successfully demonstrated the feasibility of developing a technology that will reduce cost and manufacturing time, broaden design options, and improve performance of large space optics.  
Primarily addressed is light weighting ULE glass mirrors for large telescope systems.  

While milling and cutting materials such as ULE or SiC is often performed at Ormond using a novel abrasivejet technology, there is a need to develop this technology to a the requirements of large optics manufacturing.
In Phase I, Ormond proprietary glass and ceramic cutting and milling technologies were adapted to AMTD-2 requirements through software, process and tool development.  The technology is now at TRL5 and technology feasibility has been demonstrated.  

A demonstration coupon was machined based on the current AMTD mirror concept at rates several times faster than conventional grinding can accomplish.  This design has 0.75 inch deep hex cell pockets in the mirror back, the same as would exist on a full scale mirror.  Rough semi-elliptical optical surface machining was also demonstrated in Schott glass.  Tooling designed in the Phase II program will support substantial improvements in risk mitigation, tolerance holding capability and material removal rates.

This work will continue to be performed with close interaction with NASA and Exelis to insure that the work directly supports current and future program needs.  The Phase II program will result in a working system that is capable of completing a 1/3 scale model of the AMTD-2 mirror with tremendous cost savings, schedule reduction and risk reduction compared to grinding.  Capacity for full scale up will be demonstrated during Phase II.
Advances in the capabilities of electronics have enabled high power density devices.  However, even in light of advances in electronics efficiency figures, the increased power density operational points result in the generation of excess heat.  In order to maintain efficiency and to product sensitive components from thermally-induced failure, intelligent rejection of thermal energy is often a critically limiting constraint in system development.  Novel concepts for thermal management are particular necessary in applications with finite energy stores, such as long-duration space missions.  The Prime Photonics magnetothermal fluid pump provides for game-changing, autonomous self-powered thermal management systems.
Our self-powered pump converts excess thermal energy into point-of-use mechanical energy with a low mass insertion penalty.  The operational frequency of the pump is proportional to the magnitude of the thermal gradient, supplying additional pump capacity in response to increased thermal loads.
The traditional view of arithmetic operations dominating the computational cost of numerical algorithms has changed. As performance of new processors increases, we are moving into a new reality in which data movement is expensive and operations are becoming nearly free. In Phase I we discovered a new theory of data compression with unprecedented capability to reduce data movement in distributed HPC applications. Phase I results include: 1) the demonstration via proof-of-concept prototypes of lossless compressive gains of 4x-20x for NAS Parallel Benchmarks, and 2) the formulation of COPA, a Compression OPportunities Auditing &amp; discovery process that facilitates the analysis of any given large-scale code with the purpose of optimizing it for performance via data movement reduction.
Phase II targets the consolidation of the new theory through two major thrusts: 1) the development of software that facilitates integrating high-yield compression into HPC codes, and 2) the further infusion of the technology into NASA applications. Thrust 1 will produce a fully functional prototype of a software suite for the automatic/semi-automatic acceleration of HPC codes via compression. The prototype will incorporate ease-of-infusion features (e.g., MPI-enabled compression and decompression routines), as well as ergonomic features that allow the seamless integration of new compression modules into the suite. Thrust 2 will begin with the application of the Chapter 1 of COPA to five HPC codes of utmost importance to NASA, namely Cart3D, FUN3D, USM3D, Enzo, and WRF. Accelogic will collaborate with the developers of these codes to integrate the compression technology under three different levels of "integrability," namely automatic, semi-automatic, and manual. By the end of Phase II, at least one of these applications will undergo the complete COPA optimization process. Complementary Phase II/III funds for $1+ million have been secured to ensure successful commercialization.
This project addresses the need for a non-contact instrument capable of measuring the isotopic ratios O-18/O-16 and D/H from water ice and other solid materials (rocks). Frozen H2O is the dominant ice in the outer solar system, recently found on the Moon. Extensive deposits of near-surface ice discovered on Mars. Oxygen and hydrogen isotopic records preserve history of water/rock interactions depending on chemistry and ambient conditions. Ratios of these isotopes are the main tool in paleoclimatology studies on Earth. A proposed non-contact optical instrument similar to ChemCam will be capable of measuring not only complete elemental compositions but also the key isotopic abundances in surface materials. We demonstrated the resolution and sensitivity required to determine these isotopes in synthetic samples and natural minerals relevant to Mars. We are utilizing and developing our recently published technology: Laser Ablation Molecular Isotopic Spectrometry (LAMIS). Our concept is simple and scientifically proven. We will advance to TRL4 with the further aim of integrating our LAMIS detector with a ChemCam-like instrument. The proposed effort leverages and advances the technology developed for ChemCam. The added strength of measuring isotopes will greatly expand the capabilities of the ChemCam, which is already a highly successful instrument onboard "Curiosity". We will develop a breadboard prototype of the instrument that can be later amended to measure other key isotopes (C, N, B, Cl, Mg, Ca, Sr). We plan further infusion in NASA missions and commercialization. The immediate focus is on Mars but our concept is also highly germane to future landing missions to the Moon, other planets and their moons, asteroids, and to a broad range of applications in ecology, agronomy, nuclear industry, radio-chemotherapy, forensics, security and other fields. Our instrument can be used for stand-alone landing missions or for in situ sample characterization prior to sample return.
MicroLink Devices will increase the efficiency of multi-junction solar cells by designing and demonstrating advanced anti-reflection coatings (ARCs) that will provide a better broadband spectral response than that of conventional anti-reflection coatings.  Advanced coatings of this nature are needed to realize the full performance of the forthcoming generation of multi-junction solar cells, which will contain four or more junctions.  Two approaches to improving the performance of the antireflection coatings will be investigated: 

*  develop multilayer dielectric antireflection coatings incorporating LaTiO3 to achieve significantly improved optical coupling between the coverglass and cell at the ultraviolet and infrared ends of the spectral range of interest; and 
*  develop a structure and corresponding fabrication process to oxidize the Al-containing window layer in order to reduce the absorption of light at the short-end of the spectral range of interest, thus providing extra useable photons to the cell.   

These two technologies will be integrated into a hybrid design which will provide the best possible coupling of light from cover glass to cell in order to achieve the highest possible efficiency in next-generation devices containing four or more junctions.  It is expected that the new coatings will enable a relative efficiency increase of at least 7&#37;, corresponding to a 2.5&#37; absolute efficiency increase.  The reliability and radiation tolerance of these materials and the solar cells incorporating the new designs will be tested.
SySense, Inc. proposes to develop a framework for the design and implementation of fault detection and isolation (FDI) systems. The framework will include protocols which define how to work with an end customer so that an FDI system may be developed for a wide range of autonomous satellite, rocket, air, land, and underwater vehicle missions. The framework will define what kinds of data and information are needed a priori in order to design the FDI system, what kinds of mission requirements can be answered with the system, and how the system should be implemented in order to meet those requirements. The framework will also include the procedure to facilitate the efficient integration of our FDI methodology into both existing and planned systems. Clearly defining the FDI design process through this framework will make the technology more accessible to mission designers and lower the cost of implementation, providing more opportunities to apply this technology.  The efficacy of the framework will be confirmed by designing and implementing collocated and non-collocated FDI systems for a representative satellite mission. The framework will also include introductory tutorial material designed for mission planners.
We developed a highly sensitive and compact instrument to directly measure particulate matter (PM) optical absorption. This device is based on differential photoacoustic absorption spectroscopy (DPAS) technique, which is capable of eliminating background interference from gaseous NO2 and engine acoustic noise. This method significantly improves detection sensitivity compared to the single-cell photoacoustic technique. Over the currently used filter-based measurement techniques, it has the following technical advantages:
  1) Direct PM absorption detection
  2) Real-time measurement system
  3) Low background noise
  4) Low-cost commercial components
Microelectromechanical systems (MEMS) technology has the potential to create deformable mirrors (DM) with more than 10^4 actuators that have size, weight, and power specifications that are far lower than conventional piezoelectric and electrostrictive DMs. However, considerable development is necessary to take state-of-the-art MEMS DMs today and make them flight-like. This Phase II SBIR proposal addresses two critical areas in MEMS DM development towards the goal of developing flight-like hardware. Namely, Phase II research will further develop Iris AO's proven hybrid MEMS DM technology to: 1) develop and demonstrate wafer-scale assembly of deformable mirror arrays and 2) increase drive electronics resolution to &gt;=18 bits using hardware-controlled super-resolution oversampling techniques. The increased spatial and actuator resolution afforded by the development here will enable picometer resolution DMs required to reach 10^10 contrast levels necessary for direct detection of Earth-sized terrestrial planets.
The Trusselator technology will enable on-orbit fabrication of support structures for high-power solar arrays and large antennas, achieving order-of-magnitude improvements in packing efficiency and launch mass while reducing life-cycle cost.  The Phase I Trusselator effort successfully demonstrated fabrication of continuous lengths of high-performance carbon fiber truss using a novel additive manufacturing process, establishing the technology at TRL-4.  The initial truss samples displayed bending stiffness efficiency superior to SOA deployable mast technologies.  The Phase II effort will address the key technical risks and mature the Trusselator technology to TRL-6.  We will do so by first refining the additive manufacturing process elements to improve process reliability and increase structural performance of the truss products.  We will then design and prototype a Trusselator capable of operation in the thermal-vacuum environment of space, incorporating design improvements to reduce weight and stowed volume.  Demonstration of fabrication of multi-meter lengths of truss in a vacuum environment will establish the technology at TRL-6.  We will also develop an automated process for integrating the fabricated truss with thin-film solar cell blankets, and demonstrate this process with a solar cell blanket simulator.  These Phase II efforts will prepare the Trusselator for flight demonstration in Phase III efforts to enable its adoption into the critical path for flight missions requiring high-power solar arrays.
Energy storage devices in many aerospace applications are facing unique challenges. Most of such applications, including remote surveillance, satellites, reusable launch vehicles, etc. depend on high-performance, highly specialized batteries. In Phase I, STI prepared and tested several sulfur-carbon nanocomposites of different formulations to identify parameters that affect composite performance characteristics.  High efficient electrolyte solvent was prepared and demonstrated with high Coulombic efficiency and good cycling performance.  During the Phase II, the composite's composition will be optimized further. Electrolyte solvent will be further optimized to increase the purity and Li ion conductivity.  In parallel, cells with 500 mAh capacity will be designed and prototype batteries will be fabricated and characterized.
The proposed Phase II investigation will focus on the development of spacecraft systems required to obtain a sample from the nucleus of a comet, hermetically seal the sample within a capsule, and return the sealed sample to an orbiting spacecraft which can return the sample to Earth. A systems level concept for the Comet Surface Sample Return Probe has been developed in Phase I. This concept will be refined during the proposed Phase II investigation, including high fidelity prototypes and analyses of critical subsystems. These high fidelity prototypes will include the sample acquisition and handling subsystem, a hermetically sealed sample return canister, and a full scale mockup of the Comet Surface Sample Return Probe.  Orbital mechanics calculations were completed in Phase I based on simplified geometry assumptions of the comets shape and density in order to determine the feasibility of orbiting, impacting and ascending from the comets surface with a small scale spacecraft. During Phase II, these analyses will be refined to include uneven geometry and inconsistent density.
NASA missions for planetary exploration require high power, long-life Hall thrusters. However, thruster power and lifetime are limited by the erosion of plasma channel walls.  Current plasma channel insulators, BN or Borosil, have the required low secondary electron emission (SEE) but are susceptible to xenon plasma erosion. AlN has exceptionally high plasma erosion resistance but suffers from high SEE yield. AlN can be a "revolutionary" replacement for BN channel insulator since it provides high plasma erosion resistance with structural robustness and high thermal conductivity if it's SEE yield can be reduced. 

In Phase I program we demonstrated the SEE yield of AlN can be reduced to the levels of state-of-the-art BN-based materials by microstructural engineering  without sacrificing  its thermal and mechanical properties for long-life plasma channel insulators in high power Hall thrusters.
Future NASA space missions require advanced systems to convert thermal energy into electric power.  These systems must be reliable, efficient, and lightweight.  In response, we propose to develop a turbo-Brayton power converter with high efficiency and specific power.  The converter will use gas bearings to provide reliable, maintenance-free, long-life operation.  It will also consist of discrete components that can be packaged to fit optimally with other subsystems, and its continuous gas flow can communicate directly with remote heat sources and heat rejection surfaces without ancillary heat transfer components and intermediate flow loops.  Creare is well suited to succeed because we have a long history of developing advanced turbomachines, heat exchangers, and Brayton systems for challenging spaceflight applications.  We completed detailed analyses, trade studies, fabrication trials, and preliminary designs for the components and converter assembly during Phase I, and we now plan to fabricate and test a breadboard converter during Phase II.
The overall goal of the SBIR program is to develop a new Application Specified Integrated Circuit (ASIC) driver to be used in driver electronics of a deformable mirror (DM) system in order to reduce power dissipation, improve controllability, enhance preciseness, and to significantly reduce the form factors of the entire DM system, thus making it suitable for space-based deployment. A unique capability is being enabled through this SBIR program that allows selection from various DM vendors a best DM to be integrated with the driver ASIC in order to build an extremely high contrast, compact, and low-mass coronagraphs and nulling interferometer system onto a space-based telescope. Given its superior performances namely (1) low power dissipation, (2) high control preciseness, (3) tiny chip estate and low mass, (4) minimal number of needed cables, and (5) universal capability in driving various piezoelectric actuator loads, the proposed ASIC driver technology holds the promise of enabling ultimate deployment of low power, low payload, low cost, and high-performance adaptive optics (AO) systems into NASA's space-based platforms. The feasibility of the proposed Phase II approach is demonstrated through eight major technical objectives: (1)packaging and characterizations of the Phase I 8x8 driver ASIC, and based on the test results, (2) design optimization and simulation of the Phase II 32x32 switch array driver ASIC, (3) layout, simulation verification, and tape out for ASIC manufacturing, (4) packaging and basic characterizations of the driver ASIC, (5) ASIC UBM (Under Ball Metallurgy) fabrication, (6) building ASIC PC communication interface and PC software development, (7) fabrication of capacitive load arrays made of different piezoelectric materials, and (8) characterizations of the final Phase II 32x32 switch array driver ASIC in integration with load/actuator arrays.
NASA GRC is developing fission power system technology for future space transportation and surface power applications. The early systems are envisioned in the 10 to 100kWe range and have an anticipated design life of 8 to 15 years with no maintenance. A non-nuclear system ground test in thermal-vacuum is planned by NASA GRC to validate technologies required to transfer reactor heat, convert the heat into electricity, reject waste heat, process the electrical output, and demonstrate overall system performance. This SBIR project by ACT will develop a modular single-facesheet Variable Conductance Heat Pipe (VCHP) radiator, operating near 450K, to support the Technology Demonstration Unit (TDU) for surface power. Based on the Phase I results and the experience gained during previous NASA SBIR VCHP radiator programs, ACT and VST will develop in Phase II a low cost high specific power modular radiator for the TDU. New features of this radiator include direct bonding to the titanium condenser and the fact that it is modular and therefore, the CTE mismatch on the manifold direction is eliminated. The modular radiator will consist of 12 clusters of 9 modules each. ACT will design the modular radiator, validate the radiator module, fabricate the heat pipes and test the clusters in ambient conditions before sending them to GRC. VST will further develop the GFRC direct bonding and attach the GFRC fins to all the heat pipes.
Large, lightweight, deployable solar array structures have been identified as a key enabling technology for NASA with analysis and design of these structures being the top challenge in meeting the overall goals of the NASA Space Technology Roadmap. The use of analysis to drive design from an early stage is critical to their success, yet conflicting design requirements and demanding space constraints make traditional design/build/test methods challenging and expensive. The proposed SBIR program focuses on overcoming this through the development of a user-friendly multi-disciplinary design and analysis software toolkit that can rapidly perform parametric studies and design optimization of solar array concepts. The software package will provide a graphical user interface and analysis procedures to evaluate critical performance metrics, while eliminating the unnecessary pre-processing and computational overhead associated with current approaches. Analysis capabilities will include flexible multi-body dynamics, array deployment, modal analysis, and response simulation. Model creation will be simplified through the use of an extensible, hierarchical blockset solution and a library of blocks specific to deployable solar array analysis. The Phase II effort will focus on the development of advanced analysis and design capabilities and further validation of the tool through test-correlated modeling of a state-of-the-art solar array system.
We propose to develop an all solid state Li-ion battery which is capable of delivering high energy density, combined with high safety over a wide operating temperature range. The proposed effort builds upon an in-house developed inorganic solid electrolyte that has demonstrated high ionic conductivity at room temperature (1.5x10-2 S/cm). The primary objective of the Phase I program is to demonstrate that the recently invented solid electrolyte can be formulated into a useable form in a practical Li-ion battery, and that traditional challenges associated with the use of a solid electrolyte can be overcome. A key innovation is the use of a unique composite morphology for the solid electrolyte, wherein passive components, such as the binder and separator, are replaced by an active conductive electrolyte network. The proposed new solid electrolyte will fully eliminate the flammability issues of conventional Li-ion batteries, thereby leading to a safer device with high thermal and mechanical stability. The target energy density for the proposed solid electrolyte based Li-ion cell at the cell level are: greater than 500Wh/kg (gravimetric) and 2700 Wh/l (volumetric), while maintaining 80&#37; of initial capacity after 500 cycles under full depth of discharge. The Phase I effort entails fabrication of the proposed composite solid electrolyte, and cell level testing with a suitably modified cathode and anode. A successful Phase I program will lay the foundation for prototype cell and cell-pack demonstration in Phase II, where Li-ion cells will be designed, assembled, and tested to meet the requirements of NASA for safety, cycle life and energy density. Prototype cells will be delivered to NASA at the end of the Phase II program.
Accurate safety analysis of software suffers from a lack of appropriate tools for software developers. Current automated tools require approximate analyses; fully-assured verification with formal methods is expert-intensive. A key to improvement is machine-checkable specifications for software modules. Specifications are also needed to express the intent of software. Further, to scale to wide use, engineers who are not formal methods experts must have usable tools, as automated as possible, integrated into their usual software development environments (IDEs).

Our proposal, SPEEDY, is a user experience (UX) design for convenient generation, manipulation, and checking of specifications, directly in a common IDE (Eclipse). The tool's design integrates automated specification suggestion using current tools and published techniques. The tool also enables checking and debugging specifications directly in the IDE, with information presented in the context of the source code. The proposal targets C/C++ programs, particularly for embedded software development.

Phase I of SPEEDY assessed current specification languages and prototyped the key UX mechanisms: we are now confident that they can be implemented in the Eclipse IDE. We also integrated several analysis tools, demonstrating that SPEEDY can obtain specification suggestions from external sources. We assessed many specification suggestion algorithms, selecting some to be implemented and evaluated on realistic software in Phase II. Phase I also prototyped the integrating specification checking tools and specification debugging features. We demonstrated SPEEDY on NASA software from the NASA open software site.

The Phase II proposal presents a plan for scaling up the successful Phase I prototype in many dimensions: more language features; more sophisticated user guidance in generating and debugging specifications; more specification suggestion algorithms; scaled up to realistic program size.
The thermal management of spacecraft would be enhanced by dynamic control over surface emissivity in the mid-infrared. In this SBIR program, Triton Systems proposes to demonstrate a flexible film material whose emissivity self-switches from a low value to a high value when the film temperature exceeds a preset value. The wavelength of peak emissivity can be engineered between 1.5 to 15 ?m as desired, and the transition temperature can be varied between 5-70 C. The film is easily engineered for different requirements, and if desired, different film characteristics could even be applied to different areas of the same spacecraft. No external power is required. The film substrate is a light weight flexible material that can be produced in large areas by roll-to-roll nanoimprinting.  Triton Systems has substantial background in the computational design and fabrication of these types of switchable emissivity materials. In addition to NASA applications, the material will serve military needs such as IR signature control for ships, aircraft, UAVs or land vehicles,  commercial needs in  thermo-photovoltaics, and for energy efficiency in residential and commercial architectural uses for walls, roofs and windows.
NASA is emphasizing the use of larger, more integrated models in conjunction with systems engineering tools and decision support systems. These tools place a corresponding stress on legacy engineering visualization systems which now are required to handle larger data sets, provide more intuition to the user, integrate well with many other tools, and help the user with his/her ultimate goal: improving the design of complex systems.    
Phoenix Integration proposes to complete the prototype visualization environment created during Phase I to the point where it is a commercially viable product. New features, refinements, and integration with other tools will be accomplished in Phase II. In particular, the work will involve major improvements to whitespace exploration algorithms, techniques that enable users to unconstrain or modify the underlying engineering model in an effort to obtain results in previously unattainable areas. Work will also include more data mining algorithms (e.g. Principal Component Analysis), new graph types (e.g. spider plots), export formats to 3-D tools (e.g. Tecplot), integration with MBSE/SysML tools, integration with web-based decision support environments, and incorporation of probabilistic analysis. A rich integration with ModelCenter, the company's engineering integration and trade study environment, is planned, although a standalone capability will also be offered. The visualizer's architecture will be based on OpenGL and will use the GPU to parallelize rendering computations. Design will focus on usability and responsiveness, with the goal of providing quick insight into complex data. The tool will be user-tested through early adopters to ensure relevance and to guide development.
In situ production of methane as propellant by methanation of CO2, also called Sabatier reaction, is a key enabling technology required for sustainable and affordable human exploration of Mars. The Sabatier reaction is conventionally carried out in a fixed bed catalyst at high temperatures of 350-400 ?C. For the long duration future Mars missions (~ 18 months expected stay on Mars), the fixed bed Sabatier reactor design however is inadequate due to performance and catalyst durability issues. In addition thermal management within the reactor is a major issue due to exothermicity of the reaction. Lynntech has demonstrated the feasibility of a novel low power, low temperature plasma assisted catalysis process for addressing these limitations with the methanation of CO2 at a scale of 14 g/h methane production rate. In the Phase II project, Lynntech proposes to build and demonstrate a full scale (0.55 kg/h methane production rate) Sabatier reactor for NASA application. The anticipated Technology Readiness Level at the beginning and ending of Phase II will be 3 and 4, respectively.
Future spacecraft will require services offering higher data rates than those supported today and with improved SWAP and performance.  Complicating the environment in which these technologies operate is the shortage of available and interference free radio spectrum.  While the incremental advances in equipment design and performance in X, Ka bands requested in this topic may meet some of these future needs, MaXentric believes that developing equipment to provide high bandwidth communication services in as yet underutilized spectrum, namely the Inter-Satellite band 59-71 GHz, offers a higher return on investment and a more significant capability enhancement. The recent rapid commercialization of the E and V Bands (71-76, 81-86 and 60GHz) for terrestrial use  has driven the development of a large, cost sensitive market place for RF components that didn't exist even a few years ago. In this proposal MaXentric suggests revisiting the utility of these frequencies for space based high data rate communications by developing and demonstrating a high data rate transceiver for the range 59-71 GHz. As a Phase 1 and 2 participant  in Darpa's Fractionated Satellite ("F6", 60GHz, 1Gbps) , Mobile Hotspot UAV ("MHS", E Band, 1Gbps) and Microscale Power Conversion ("MPC") programs, MaXentric is in a unique position to design, develop and demonstrate a small, low SWAP, high data rate, power efficient,  59-71 GHz transceiver  that could be incorporated into NASA's SCaN Integrated Network Architecture in the future. This capability would not be restricted by availability of spectrum and has other inherent advantages because the attenuation of Earth's atmosphere reduces interference and associated coordination requirements. MaXentric believes the availability of almost 12 GHz of unrestricted communications bandwidth provides a very significant opportunity for the provision of high data rate services.
The development of an advanced green monopropellant propulsion system could have significant benefits to a wide range of NASA space missions, from deep space satellites to manned space vehicles.  However, the state-of-the-art thruster materials, refractory metals, cannot withstand AF-M315E combustion environment at temperatures of &gt;2000?C without loosing their mechanical integrity. 
Sienna Technologies, Inc, in collaboration with Moog-ISP, proposes to develop a revolutionary refractory metal-ceramic FGM material and an AF-M315E advanced green monopropellant thruster.  In Phase I we will demonstrate a refractory metal-ceramic FGM through materials design and microstructural control that meets the requirements for thrust chamber for AF-M315E monopropellant.  In Phase II we will fine-tune the FGM material properties to maximize the mechanical strength and thermochemical stability; and design, fabricate, and test a working FGM thruster in collaboration with Moog-ISP.
We propose to demonstrate a fully automatic capability for generating a global, high resolution (30 m) land classification map, with continuous updates from satellite imagery and crowdsourced ground truth, and an annual publication cycle. The resulting map will be fully extensible, supporting many layers including Anderson type land cover categories, specific crop types in agricultural areas, and even continuous variables such as crop yield estimates. Our methodology involves fusing imagery with existing raster and vector ground truth data sets, applying a novel classification technique to enable vastly improved spatial/temporal model portability, and continuous updating as additional imagery and crowdsourced ground truth data becomes available. By employing a systematic crowdsourcing strategy that is responsive to local and regional market incentives, the map's accuracy will improve most over time in those geographic regions where higher accuracy is most needed. The resulting map product will find immediate use for a multitude of applications in agriculture, commodities trading, ecological forecasting, wildlife conservation and climate change studies. We foresee monetizing the continuous production effort by obtaining stakeholder funding to make a standard product freely available to the global public, but we also intend to develop higher precision, commercial products for lucrative applications such as precision agriculture in targeted locations worldwide.
We propose to demonstrate an eye-safe laser source for a DIAL CO2 sensor that meets or exceeds all topic requirements for a high-pulse-energy laser with good beam quality, transform-limited spectrum, and efficiency &gt;25&#37;. Our approach will use a cavity-dumped resonator to directly generate Nd 1.4-micron pulsed output, and injection seeding for spectral narrowing. This approach, while based on established technology, is innovative in finding an optimal solution from uncommon elements. Our design allows us to start with a well-behaved four-level laser instead of the problematic quasi-three-level lasers like Er:YAG and Er:glass (fiber). Moreover, it avoids the loss in efficiency that comes from using an OPO pumped by the common 1-micron Nd or Yb laser to generate eye-safe near-IR output. We also propose to demonstrate that our laser performance is tolerant of high-temperature operation, making passive cooling possible with major advantages in overall size, weight, wall plug efficiency, and power scalability.
A major limiting factor in HPC growth is the requirement to parallelize codes to leverage emerging architectures, especially as single core performance has plateaued and architectures like short vector units (e.g., AVX), Intel Xeon Phi, and GPUs are embraced by hardware manufactures. The proposed SIMD/SIMT vectorization tools for emerging accelerator-based compute architectures will impact a world-wide range of academic, government, and commercial researchers.

The Geant4 toolkit enables the simulations of the passage of particles through matter.  As with many scientific codes, it was originally developed for single processor compute nodes using compute clusters, and has not been optimized for SIMD/SIMT architectures (e.g., many-core nodes, GPUs, short vector units, and other Application Processing Units, e.g., Intel Xeon Phi. Therefore, optimizations and code rewrites are required to target each new architecture.

This project will develop two tools to aid in the parallelization of compute applications for SIMD/SIMT architectures.  The first tool will perform a dynamic analysis to determine the potential to extract SIMD/SIMT parallelization from an application. The second tool will be a Domain Specific Language (DSL) designed to aid in the SIMDization of control dependent application components. The DSL compiler will automatically generate a SIMD/SIMT optimized code version targeted at the compute architecture of interest (e.g., GPU, SIMD Vector Units like AVX, or Intel Xeon Phi). Initial development and experiments will be developed for Geant4.
The proposed innovation is a simple, robust, sensor array for the detection of laminar/turbulent transition location, areas of flowfield separation, and shock wave locations.  The system can be used in both ground and flight test facilities.  The proposed system uses a very robust and proven sensor technology combined with a novel mounting and manufacturing technique.  The sensor array is reusable and can be produced in a configuration that requires no external power, acquisition or viewing, for flight test applications.  The system combines an array of small, surface flush, sensors embedded in an extremely thin, flexible polyimide strip.  The system operates by sensing changes in local heat transfer within the boundary-layer.  Variations in heat transfer coefficients due to the state of the boundary layer (laminar, transitional, turbulent, separated regions) produce changes in the sensor output.  Other flowfield features where heat transfer is affected will also be discernable, such as shock waves.  The flush mounted sensors, embedded in a smooth, thin polyimide sheet, conform to the local surface contour and produce minimal aerodynamic interference, allowing non-intrusive measurements.  The system will be quantitatively accurate across the low-speed through supersonic flow regime.  After testing, the system can be quickly removed and reused.  Compared to current systems designed for similar measurements, the proposed system promises to provide a significantly more robust and efficient system in a relatively simple, cost effective package.
This is an SBIR proposal to develop a revolutionary digital schlieren imaging system that will greatly improve a widely used aerodynamics tool and render it so robust, user friendly, and productive that it will be useable in test facilities and environments that have been prohibitive before.  Also, by incorporating recent advances in consumer camera and display technologies we can produce a new class of digital focusing schlieren (DFS) systems that drastically reduce the manufacturing costs as well as the size and weight, while maintaining sensitivity, improving robustness, making it more user friendly, and over all a much more powerful instrument. The digital schlieren concept represents the first major improvement in schlieren imaging in over 150 years, a true quantum jump in the technology. Conversion to digital obviates many of the long-standing problems with focusing schlieren systems that are associated with precisely matching the cutoff grid to the background light pattern. Because the system is digital, the control software can perform real-time image enhancement as well. Consequently, the most severe hardware production and alignment restrictions are now software problems that are solvable continuously, quickly, and inexpensively in real time. This capability enables the system to compute and compensate for imperfect windows and optics, optical aberrations, misalignments, and temporal changes in the system and subject.
In the current proposal, M4 Engineering will develop and evaluate the feasibility of an innovative concept aimed at enhancing previously developed databases with physics-based weight and load estimation relationships (via stochastic response surfaces) for unconventional (and conventional!) conceptual wing and fuselage designs.  The main goal for this effort will be to develop a software tool capable of generating weight and load responses for unconventional designs from physics-based simulations.  In an effort to minimize risk and expedite development, the proposed software tool will utilize two previously developed in-house robust toolsets for rapidly generating finite element models and constructing stochastic response surfaces.
We propose to design and demonstrate a portable source of lattice-trapped, ultracold strontium (PLUS). The device uses simplified and robust techniques for loading the traps, and directly leverages hardware already developed by AOSense. The simplified architecture for PLUS makes it amenable to future space qualification. When paired with a sufficiently stable local oscillator, PLUS can be operated as an optical lattice clock. Alternatively, the lattice-trapped atoms could serve as a starting point for producing quantum degenerate Sr gases for use in future sensor technologies or fundamental science studies. In the latter case, possibilities span explorations of artificial gauge fields to quantum information processing. In Phase I, AOSense will optimize the expected device performance through extensive modeling, trade-space analysis, and technology validation of the highest risk hardware. The design will cover the physics package and control system at the level of CAD models, ready for procurement that will begin during Phase II. We will also model device applications and generate a parts list and cost estimate for the construction of a prototype during Phase II.
Research is proposed to demonstrate the use of advanced manufacturing techniques to enable the affordable application of multi-functional thermal / environmental barrier coatings (T/EBCs) having enhanced resistance to high temperature combustion environments.  T/EBCs are envisioned to protect the surface of Si-based ceramics against moisture-assisted, oxidation-induced ceramic recession. Current T/EBC systems have been demonstrated in long time exposures at ~2400&amp;#176;F substrate temperatures. However, their use at elevated temperatures (i.e. 2700&amp;#176;F substrate temperatures) is limited by the low temperature stability and high diffusion activity of current T/EBC materials. One approach to increase the temperature capability of these systems is the incorporation of multi-layered T/EBC designs.  In this Phase I effort, enhanced processing techniques will be employed to demonstrate the manufacture of robust T/EBC bond coat systems using a physical vapor deposition based processing approach which enables improved coating adhesion and advanced coating architectural, compositional and microstructural control, as well as non-line-of-sight (NLOS) deposition. Scaled processing approaches will then be used to demonstrate the deposition of high temperature capable T/EBC bond coats onto components of interest to gas turbine engine manufacturers.  These bond coats will then be incorporated into full high temperature capable T/EBC systems planned in Phase II.  Finally, concepts to enable the deposition of T/EBC bond coat systems on NLOS internal regions of hollow components will be investigated. This work will significantly aid the incorporation of Si-based ceramic components in gas turbine engines resulting in reduced weight and increased operating temperatures.
As a result of significant technical effort, the Phase I was successful in delivering a solar simulator prototype that not only proved the initial concept but will significantly reduce future risk and increase our ability to deliver a fully-functional solar simulator in Phase II.   The proposed innovation is an LED-based, laboratory-scale, solar simulator.  The proposed innovation simulates AM0 response of single, dual, 3, 4, 5 and 6 junction solar cells by using an array of different wavelength LEDs in close proximity to the cell under test.  The simulator is adjustable in spectral matching for selected wavelengths and Class A, the highest standard, for spatial uniformity and temporal stability.  The solar simulator illuminates a square area 10 inches by 10 inches and includes optical sensors so that all metrics can be calibrated and validated automatically as needed.

Solar simulation is critical for all solar cell testing, and current simulators will not work for coming 4, 5 and 6 junction technologies.  Because the vast majority of NASA missions rely on solar cells, this is critical, enabling test technology for future solar cells.  While accurate solar simulation is critical to all solar cell missions, it is particularly important to missions requiring large amounts of power, such as solar electric propulsion (SEP) missions.  Beyond NASA's needs, other members of the aerospace community, including solar cell manufacturers, test labs and research institutions, have a critical need for this capability which presents excellent commercialization opportunities after the Phase II maturation of the technology.
In this Phase I SBIR, Terves will develop processing routes to produce high thermal conductivity magnesium composites for use in heat transfer applications such as radiator materials. Terves will use and refine ultrasonic casting processes developed over the past three years and move into a magnesium based material using high aspect ratio carbon fibers and diamond particles by dispersing in a liquid state. The cast material will be rolled into sheet and tested for thermal and structural properties and compared to currently available materials. A successful program will result in a new, high thermal conductivity material that is lighter than current aluminum composites with the same or similar strengths. This composite will be applied in spacecraft for fast and effective heat transfer, enabling lighter thermal transfer systems by removing previous design constraints.
Hybrid-Electric distributed propulsion (HEDP) is becoming widely accepted and new tools will be required for future development with validation and demonstrations during ground and eventually flight testing. Intelligent health management will be paramount to any future ground and flight testing activities planned by the industry on HEDP systems.  To support this, an intelligent prognostics and health management (ePHM) system will be designed and executed for the HEDP system on the NASA Dryden Hybrid Electric Integrated System Teststand (HEIST) (AirVolt optional), which will be developed as part of a parallel Phase III SBIR by ESAero, the proposer here.  Most developments in PHM surround air vehicle subsystems and avionics, specifically on the electronic board level, and many of these are integrated after the systems are designed.  These developments have or are establishing the ability to monitor the degradation of a subsystem in real-time, making it conceivable that actionable information can be fed to a Integrated Autonomous Controller for self-repair decisions, leveraging the Propulsion Airframe Integration benefits.  Reliability can be calculated and maintenance can be planned ahead of time rather than at the point of failure, significantly increasing safety.  
General Atomics, Electromagnetic Systems Group (GA) will continue to play a vital role.
Exquadrum proposes a high-performance liquid bi-propellant rocket engine that uses propellants that are non-toxic, self-pressurizing, and low cost.  The proposed engine and propellants provide the same performance as state-of-the-art storable propellants.  The propellants are storable for long durations without decomposition or degradation.  Because the propellants are self-pressurizing, they offer the potential for overall system weight savings by eliminating the pressurization system.

In Phase I, Exquadrum will develop this engine concept through trade studies and analyses and conclude with a proof-of-concept hot fire demonstration of a full-scale laboratory engine.  In Phase II, Exquadrum will mature the engine design to detail design, and deliver a full-scale engine to NASA for functional and environmental testing under simulated mission conditions.
Future NASA hypersonic vehicles offer a potential to incorporate advanced ceramic matrix composites (CMC).  The key characteristics include excellent mechanical properties, excellent thermal shock resistance  and ability to survive cyclic oxidation environments.  Among the CMC composites carbon fiber-SiC matrix composites offer excellent high temperature capabilities.  The highest specific strength C-SiC composites are fabricated via conventional Chemical Vapor Infiltration (CVI) SiC method.  There are several limitations to SOTA CVI SiC technology.  First, fixturing is required during the processing.  Secondly, transverse mechanical properties are quite often design limiting criteria, thirdly manufacturing times are very long and fourth the fabrication of very large parts is limited due to huge capital investments required for very large equipment needed to operate at very low pressure.  This proposal addresses all the above stated limitations of classical CVI.  First it offers unique 3-D preform capable of increasing transverse properties with minimum degeneration of the in plane properties.  Secondly the proposed processing eliminates the need of fixturing.  Thirdly, modified CVI SiC significantly reduces processing time.  And fourth, Phase II will extend to incorporate extremely novel atmospheric pressure CVI SiC, offering a paradigm shift in CVI SiC by allowing to utilize conventional, low cost atmospheric pressure furnaces routinely used in heat treating applications.
NASA's crewed spacecrafts require routine cleaning of particulate, moisture, organic, and salt contaminants on the crew cabin surfaces and fabrics. Self-cleaning surfaces will help in reducing the crew's effort in cleaning the cabin and reduce the amount of wipes used for cleaning. It will also be beneficial if the surfaces can be made antimicrobial to reduce the health risks of the crew members. Surface treatments also should be durable for 3 to 5 years long missions. In the proposed Phase I effort, a novel multifunctional coating will be developed which has both superhydrophobic and antimicrobial properties. Antimicrobial treatment of cabin crew surfaces do not resist the accumulation of contaminants on the surfaces. In the proposed Phase I Materials Modification Inc. (MMI) will develop a multifunctional coating for providing antimicrobial and self-cleaning properties to the spacecraft crew cabin surfaces based on its superhydrophobic technology. The best coating formulation selected from the Phase I effort will be incorporated in a prototype spray cans for NASA applications.
The General Mission Analysis Tool (GMAT) is a state of the art spacecraft mission design tool under active development at NASA's Goddard Space Flight Center (GSFC).  GMAT is an open source project, periodically releasing code on publicly accessible repositories.  The tool has recently been operationally certified for use planning maneuvers for the Advanced Composition Explorer (ACE).

The current implementation of GMAT is built on an architecture that was originally designed to support multiple parallel runs of space flight problems on a distributed processing platform.  The implementation of GMAT, to date, has not exercised the features of the design that make parallel processing available to users.  The GMAT program in its current implementation runs on a single execution thread on modern computer systems, even when those systems contain multiple processing cores that allow for parallel execution of operations.  Thinking Systems is equipped to undertake the task of coding components that plug into GMAT's base code libraries in order to produce an efficient parallelization of GMAT's capabilities.

The parallelization of GMAT will be built by building replacement elements of several components of GMAT's core control engine and by implementing user scriptable elements that capitalize on these core components to provide processing on multiple threads simultaneously.  Thinking Systems will construct these components in a way that allows the parallel processing engine to run using GMAT's core library code.  The parallel engine will be built to work alongside existing GMAT code, and will be accessed using a separate user interface tailored to the parallel engine.   

Examples of the types of problems that benefit from the proposed system are
Parametric studies using systematic changes in one or more parameters, Monte Carlo analysis problems, Large scale targeting problems, and Dispersion analysis studies
High performance LWIR detectors are highly needed. In order to image from long distance, it is important that imagers have high sensitivity, high resolution, and very low dark currents. This leads to technical goals of having low noise, low dark current in small size pixels in large arrays. While saturated performance levels of traditional systems based on bulk semiconductors have not quite met the requirement of applications, it is expected that novel quantum systems will bring new development stage for infrared imagers. In recent years, Type-II InAs/GaSb superlattice (T2SL) has experienced significant development, from theoretical modeling, material growth to device processing and packaging. Performance of LWIR detector based on T2SL has become comparable, even better than that of HgCdTe. However, LWIR T2SL devices have been shown to be limited by surface leakage, especially at lower operating temperature. This proposed effort will investigate gating of Type-II photodiodes as a means to suppress this bottle neck of T2SL technology. The ultimate goal of this project is to develop an effective method to completely suppress the surface leakage current in LWIR type-II superlattice photodiodes that is compatible with the development of high performance gated FPAs in Phase II.
Over the last decade, the CubeSat platform has emerged as a viable alternative for both innovative technology development and scientific investigation. However, to fully realize the platform's potential, propulsion capability is required. For low-cost spacecraft developers, this capability remains among the most resource intensive to successfully implement. Planetary Resources Development Corporation (PRDC) proposes to significantly reduce required resources by seamlessly integrating propulsion with another critical resource-intensive subsystem: the spacecraft's primary structure. PRDC will integrate high-reliability COTS components from the medical consumer products industries into an additively-manufactured primary structural element that includes integrated tank, plenum, and manifold geometries for a hybrid green monopropellant / cold-gas propulsion implementation in addition to the spacecraft's launch interface. The resulting module provides a standard interface, serving as the strongback for simple integration of other Cubesat subsystems and payloads within the 6U and 12U size regimes. During Phase I, PRDC will design, develop, and prototype a proof-of-concept configuration of the proposed integrated module and perform initial performance characterization of the system. Follow-on Phase 2 development would include fabrication, assembly, performance evaluation, and environmental test of a full- scale 12U module with integrated RCS and maneuvering thruster capability, resulting in a TRL 6 readiness level.
We propose to form a network and a set of tools that will create a shared situation awareness with Unmanned Aircraft Systems (UAS) Ground Control Stations (GCSs) and airline dispatchers at Airline Operations Centers (AOCs).  Our solution is motivated by the Collaborative Decision Making (CDM) community in commercial aviation, where the CDMnet was created back in 1997 to facilitate collaboration between airlines and the Federal Aviation Administration (FAA).  The CDMnet continues to exist today to allow airlines to collaborate on Traffic Flow Management (TFM) decisions that are made by airlines and FAA Air Traffic Service Providers (ATSPs) every day.  Today, with the introduction of Unmanned Aircraft Systems (UAS) flying in the National Airspace System (NAS), there is a need for collaboration between UAS, ATSP, and AOCs in UAS Traffic Management (UTM) in order to share airspace resources.  Thus, the focus of this SBIR effort is to build a network that allows UAS GCSs to share information and collaborate with airline AOCs in order to create a shared situation awareness and to share and coordinate NAS airspace resources.
NASA continues to be interested in returning to the Lunar surface. The Lunar surface is a harsh and unforgiving environment. Perhaps most challenging is the drastic and length thermal cycle surface equipment will experience on the surface. Standard spacecraft electronics and batteries cannot survive the extremes of the Lunar thermal cycle and must be protected by a thermal control system (TCS) that often features Plutonium-238 which is an expensive, strictly controlled material that is not a viable option for lower cost or commercial missions. An alternative approach would be an extreme environment flywheel energy storage system that could supply enough power to heat the critical electronics during the Lunar night. Honeybee Robotics Spacecraft Mechanisms Corporation (Honeybee) proposes to develop an extreme environment Flywheel Energy Storage (FES) system that enables a small spacecraft (e.g., 200 kg Lunar Rover) to repeatedly survive the long, cold Lunar night.   The FES system will also supply operational power during the Lunar day.
Small satellites such as CubeSats are in need of responsive propulsion, but are limited due to their size. Though single pulse, AP/HTPB fueled solid rocket motors exist in the market, greater mission flexibility is to be had from a motor with the capability of a second ignition in the same volume constraints. Digital Solid State Propulsion (DSSP) proposes research into the technology to not only to enable a second pulse from a high thrust solid rocket motor, but also into a safer class of propellants called Electric Solid Propellants (ESPs). A barrier system, developed on other DSSP programs, would be the stepping stone for the dual pulse ability of the motor. The ESPs are a group of propellants that are electrically ignited, but safer to handle compared to standard solid energetic propellants. For in-space use, Aluminized variant of ESP would be improved and utilized for this application. Phase I funding would allow for the advancements of these technologies to a TRL 3. Then following basic research and design goals of a Phase I contract, a Phase II contract would allow the design and test of an integrated Delta-V and ACS propulsion into a 1U module at TRL 6.
To address these critical needs associated with the integration of Unmanned Aircraft Systems (UAS) into the airspace, we propose to conduct research on the application of Dynamic Airspace Configuration (DAC) concepts and algorithms to the challenge of accommodation and integration of UAS into the NAS. The resulting algorithms and capabilities will provide real-time recommendations to Traffic Management Coordinators (TMCs) in the ATC system regarding the airspace boundaries that should be adopted, when the airspace boundaries should be changed and how long they should remain in place, and the necessary flight routes and other procedures that should be assigned to flights (both manned and unmanned) to ensure the safety and efficiency of all operations.
A novel actuation concept previously used for trailing edge tab control is to be extended for use in spanwise camber control for enhanced aerodynamic performance of next generation aircraft designs.  The key features of its low-power, two-position (bistable) nature and small size permit its application as secondary structure within wing assemblies, thereby allowing for flight-dependent customization of the spanwise camber to optimize vehicle aerodynamic efficiency.  The proposed Phase I program will leverage previous development success of the actuation concept to scale design applications for ultimate use on transport-category aircraft, and provide risk reduction via demonstration wind tunnel tests on a scaled wing half-span model.  A byproduct of the scaling law will be its incorporation within a Multidisciplinary Design Analysis and Optimization (MDAO) tool for ease of exploration of the actuation features in the context of novel vehicle configurations having flight control for performance adjustment.
NASA uses detectors for a broad range of wavelengths from UV to gamma for applications in astrophysics, earth science, heliophysics, and planetary science. Mg-doped ZnO exhibits room temperature, sub-nanosecond luminescence making it promising for use as a scintillator for UV detectors. The realization of the potential of Mg-doped ZnO as a scintillator is currently hampered by the relatively poor light yield and a unavailability of large single crystals with suitable scintillation characteristics. Growing large single-crystal boules having uniform activator concentration coupled with uniform optical quality are a major setback for single crystal technology. MMI proposes to develop a process for the fabrication of polycrystalline nanostructured Mg-doped ZnO scintillators.  A solution based process will be used to synthesize Mg-doped ZnO nanocrystals, which will be compacted to high density using MMI's proprietary plasma pressure compaction process. The scintillation properties vis-?-vis morphology will be analyzed and the process will be optimized for further scale-up and integration to UV detectors.
This SBIR program will investigate high energy density novel nanofuels combined with high density binders for use with an N2O oxidizer.  Terves has developed processes for stabilizing advanced high Isp fuels, such as LiBH4 to make them stable in thermoplastic binders such as PE.  If they combust efficiently and have suitable regression rates and stability, These materials can provide hybrid Isp's above 300 and density Isp's above 450 seconds with self-pressurizing N2O oxidizers, enabling very low cost propulsion systems to be designed.  This program will fabricate ultrafine- and nano- metal boride and hydride fuels, disperse them into high density binders, and evaluate their combustion efficiency in a hybrid test motor
This program will develop an ultra-high performance infrared detector manufacturing technology with improved performance and cost effectiveness, and reduced cooling requirements when compared to the best commercially available HgCdTe and InGaAs detectors. This will be accomplished using a two-pronged approach addressing both device design and materials. First, the conventional pn photodiode device is replaced with a new device structure, the nBn detector, which inherently suppresses performance-limiting dark currents, such as those produced by surface leakage. Second, highly manufacturable III-V materials are used, which are further enhanced with Amethyst's proprietary UV hydrogenation defect mitigation process. The result is a low cost, high performance detectors operating in the 2 &amp;#150; 5 micron wavelength region. There is a pressing need for ultra-high sensitivity detectors operating in this region for the detection of trace gases and chemicals.
In Phase I Amethyst produced a 2.8 micron cutoff detector.  The program met all objectives, demonstrating considerable improvements in performance over conventional pn diodes using the nBn and hydrogenation approach.  In Phase II, Amethyst will design, fabricate and test high performance detectors individually optimized with cutoff wavelengths throughout 2&amp;#150;5 micron wavelength range.  These detectors will have improved detectivity, and significantly reduced cooling requirements compared to currently available commercial detectors.  In addition, Amethyst will deliver a thermoelectrically cooled 3.3 micron wavelength cutoff detector to JPL's Microdevices Laboratory for comparative testing and to assist in development of methane detector systems. The overall objective of the Phase II is to establish performance metrics, manufacturing process, characterize and life test single element devices.  These efforts will help establish a US based manufacturing source of these ultra-high performance detectors.
Advanced Scientific Concepts, Inc. (ASC) has developed a number of 3D Flash LIDAR systems.  Flash LIDAR sensors are 3D video systems that return range and intensity for each pixel in real time.  ASC's Flash LIDAR has been used for autonomous berthing with the International Space Station and is currently under development for the OSIRIS-REx asteroid rendezvous mission.  Flash LIDAR is also being evaluated by JPL and NASA for Entry Decent and Landing for ALHAT and Mars. All of these applications use avalanche photodiode (APD) arrays in the camera focal plane array. APDs are complex epitaxially grown structures and biased at relatively high voltages (50-70V).  These arrays have a poor fill factor that is compensated by micro-lenses. These micro-lenses are restricted to F/#s greater than about 3.3 which in turn limits the effective receive aperture. If micro-lenses were unnecessary, an F/1 receive aperture could increase the collection area by a factor of 10 with no increase in noise.  This should result in an increased SNR of approximately 40&#37; but, because of the simplicity of PINs compared to APDs, an increase in reliability as well.  PINs are more radiation hard than APDs, are more operationally stable (therefore do not require individual fuses to protect against the development of high dark current pixels), inherently have lower dark current (lower noise), and are inherently more uniform. In addition low-voltage FPA drive electronics is easier to design than high voltage circuitry.  These improvements will result in a more reliable higher performance array.
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In this NASA SBIR-select Phase 1 program Fibertek, Inc., proposes the design, optimization, and analysis of a 1U CubeSat Lasercom Optical Terminal, optimized for deep-space colmmunication links, and targeting the following characteristics &amp;#150; (i) Low Size/Weight/Power (SWaP) 1U Lasercom Terminal for deep-space mission (total power budget P&lt;5W is targeted), (ii) Athermalized optical design of a fiber-coupled optical telescope for lasercom transmit/receive function, (iii) Innovative monolithic design and fabrication of the optical assembly with large 6.5-cm aperture, (iv) Integrated beam point-ahead and beam-pointing stabilization capability, (v) Integrated radiation-tolerant controller card for all control and interface functions for this 1U CubeSat terminal, (vi) Low power radiation-tolerant FPGA based electronics design, for a reconfigurable and highly capable processing platform, and (vii) Use of integrated simulation &amp; modeling tools (optical, thermal, vibration, jitter-control, etc.) for detailed design analysis, and to assist in future hardware-in-the-loop testing of critical functions to validate performance, prior to prototype build and test.
Advanced space propulsion systems are a critical need for future NASA deep space missions. High thrust or high Isp engines could revolutionize space exploration. Nuclear Thermal Propulsion ("NTP") is a high thrust/high Isp propulsion technology, with a demonstrated Isp ~850, twice that of chemical rockets. Zero boil off of LH2 propellant for long duration missions is among the critical technology advancements needed for NTP. 

Quest proposes to develop and test an innovative, high performance thermal insulation system, designed to provide high performance on large LH2 tanks.  Cellular Load Responsive ("CLR") multilayer insulation integrates a mid-size cryopumping self-evacuating vacuum cell core with load bearing LRMLI within the compartments. CLR can offer a structural, high performance insulation system, that is damage tolerant, can support external loads such as thermal shields, and provides good thermal insulation both in-air (for ground and ascent phases) and in-vacuum (once in-space). CLR could provide 92&#37; lower heat leak in-air during ground hold, and 97&#37; lower heat leak in-space than SOFI.

NASA's Technology Roadmaps call "Zero Boil Off storage of cryogenic propellants for long duration missions" and "Nuclear Thermal Propulsion components and systems" the #2 and #7 ranked technical challenge for future NASA missions.  

In this Phase I program, a CLRMLI system would be modeled, analyzed, designed, fabricated, installed on a cryotank, and tested for thermal performance for ground/ascent and in-space operation.  CLRMLI could provide a robust SOFI replacement, with higher performance, lower mass, able to eliminate freezing/cryopumping of air components during ground and ascent stages. CLRMLI could help meet NASA's cryogenic fluid management requirements such as Zero Boil Off for cryogenic propellant storage and transfer.
We propose a novel new architecture for a low-phase noise electronically tunable laser single-frequency laser at 2.05 microns that meets all the demanding requirements as a seed laser for NASA Lidar applications measuring CO2 densities in the atmosphere. The laser technology is based on previously developed hybrid integration technology that enables the direct optical coupling of active and passive waveguide chips.  Array scaling was previously demonstrated for a 4-channel IFOG optical engine and this technology will be applied to the development of the array-scalable tunable laser. The proposed tunable laser can address LIDAR applications at 2.05 microns and can be modified to any wavelength spanning the range of 640-2500 nm.
Future NASA and commercial missions will increasingly target destinations with challenging topography and limited communication including unmapped asteroids, comets, and outer planet moons; surface rendezvous sites for sample return; and challenging sites like polar peaks, crater rims, and skylights on Mars and the Moon. Given the hazards of exploring these destinations, robotic landers will most likely precede human mission, as they can significantly cut mass, size and cost relative to human-relevant landers without compromising human safety. However, a reduced lander size equates to reduced hazard tolerance, placing a strong demand on precise autonomous hazard detection and landing.    The proposed research innovates safe, precise navigation for autolanding for sample return missions to a distant asteroid, planet, or moon. The technology suite developed will be packaged as a commercial product
Strain sensor information is used in nature to achieve robust flight, good rejection of wind disturbances, and stable head motion. Similar man-made sensing devices will be used to demonstrate flight control using Fly-by-Feel, with the overall objective of achieving similarly good performance with piloted and autonomous vehicles. The Phase I work demonstrated the feasibility of using strain sensor arrays for flight control applications. This was done using hardware testing on a wing in a laboratory setting. An important part of showing feasibility was the use of novel frequency domain identification techniques, which were used to identify both modal frequencies and strain mode shapes. The proposed work will develop the ACES system: Attitude Control Enhancement using Strain sensors using both wind tunnel and flight test demonstrations. Acceleration feedback is known to improve the gust disturbance rejection, and the same will be demonstrated in an active control experiment using strain sensors in a wind tunnel. A second experiment will be conducted using a different and more flexible wing to demonstrate active control of shape. Modeling and simulation will be used to begin the transition of this technology to larger commercial vehicles.
This proposal discusses the development and demonstration of a swath-based airborne  instrument suite intended as a calibration and validation with relevance to the ICESat II, SWOT and CryoSAT II missions.  In particular our innovation will leverage prior NASA developments to focus on system miniaturization and increased performance.  It will also support NASA's airborne science missions by utilizing long-endurance unmanned aircraft such as the Ikhana or the Global Hawk.  These platforms become directly relevant due to the often remote nature of regions of interest, particularly as one considers the cryosphere.  The Phase I will result in a system design that can be realized in a Phase II effort. During the Phase I, measurement requirements will be revisited and key technologies will be identified and incorporated where advantageous into a revised design.  Data volume and system automation will be specifically evaluated and a plan for on-board data storage and compression/processing will be proposed.  An accommodation feasibility study for the Ikhana will be evaluated. The Phase II effort will realize a prototype of this sensor. At the end of the Phase I, a technology readiness level of 3 will be achieved.
NASA has a critical need for improved bi-directional data transmission rates from a variety of spacecraft to Earth.  NASA estimates that the current Mars to Earth transfer rate of 6 Mbps might be increased to 600Mbps using a Laser Communication (LC) system.  Beam jitter caused by spacecraft-based motion must be reduced to sub-microradian levels to enable beaconless optical beam pointing.  ATA will create a Compact, Lightweight Isolation Platform (CLIP) that will host the LC collimator telescope and provide a stabilized platform to prevent the 150-microradian spacecraft disturbance environment from reaching the LC terminal.  To enable that stabilization, ATA will develop an ultra-low angular noise Capacitive Angular Position Sensor (CAPS).  The proposed sensor will have low power and high reliability, which ATA will demonstrate by producing TRL 4 prototypes in Phase I and TRL 5 CLIP engineering development unit (EDU) in Phase II.
The integrated CLIP overall design is a major innovation.  Most significantly, the platform payload capacity must increase from the typical few hundred grams to as much as 50 kilograms, roughly two orders of magnitude, but without major growth in the mass of the platform itself.  While the payload for most stable platforms is only a small fraction of the platform overall mass, the CLIP payload must be from more than half (3 kg) to as much as 94 percent of the total platform mass (3-50 kg payload + 3 kg platform).  Combined with the large payload range, the needed disturbance rejection from 150-microradian to less than 0.5-microradian across the broad frequency range of 0.1 to 500 Hz requires innovation in the platform suspension, high-performance actuators, servo controls, and structure.  Other programs have demonstrated these requirements individually, but the innovation CLIP provides is to combine structure, suspension, actuators, and sensors to give the required performance within the stringent 3-kg weight and 15-W power constraints.
In future ground-based receivers for deep-space optical communications with spacecraft, aperture diameters of the order of 10 meters are required even with the most sensitive available detectors. Directly applying the technology of 10 meter class ground-based telescopes is cost prohibitive. Also, conventional astronomical telescopes are not compatible with operation within 5 degees of the sun, but such near-sun operation is required with the Ground-based Telescope Assembly to provide consistent and reliable wideband communications with interplanetary spacecraft. BEAM Co. proposes to develop a telescope based on diffractive optics that is expected to be far less expensive to manufacture than a telescope based on conventional reflective optics. Our approach takes advantage of the well-defined wavelength of the optical communications beam, thus allowing a high-efficiency design that is expected to be much lighter than a conventional design, thereby reducing the cost of the system that will be used to point the telescope. At the end of Phase I, we will have fabricated and tested subscale diffractive optical elements and performed tests to validate the technology's scalability to large apertures and its capability to support the &lt;20 microradian object space spot size requirement as well as the requirement for near-sun operation.
The goal of the program is to reduce the cost of substrate reclaim for high-efficiency solar cells fabricated by an epitaxial lift-off (ELO) process, and to increase the number of reuse cycles for a given substrate.  If successful, this will result in a reduction in the cost of GaAs-based multi-junction solar cells, in which the cost of the substrate accounts for approximately 50&#37; of the total cost.  The cost reduction is achieved by introducing a new multi-layer etch-stop structure into a inverted metamorphic (IMM) triple-junction cell.  The etch-stop structure is grown between the original GaAs substrate and the ELO release layer, thereby becoming the effective substrate surface after the ELO process.  The etch-stop structure prevents pits and surface damage that occur during ELO from damaging the surface of the GaAs substrate.  The standard method of reclaiming the GaAs substrate after ELO is to employ chemo-mechanical polishing (CMP) to remove the defect-ridden GaAs surface and chemically polish the underlying GaAs to yield a surface that is suitable for epitaxial growth.  The CMP process works but reduces the substrate thickness and causes minor wafer damage itself, which requires further polishing.  These factors accumulate, in practice limiting the number of reclaim cycles to 5 - 10 for a given substrate.  With the incorporation of the proposed etch-stop structure, the defects are isolated in the etch-stop structure, which can be dissolved by successive selective wet chemical etches to produce the original pristine GaAs surface on a substrate of the original thickness.  All mechanical polishing is eliminated in this proposed work, ensuring a constant substrate thickness through repeated substrate reclaim cycles and reducing the estimated cost of the recycling process to &lt;$1 per substrate.  The Phase I program demonstrated that this method for substrate reclaim works; in Phase II we will develop the reclaim into an optimized batch process.
There exists a programmatic need across several government agencies for both UAV and manned aircraft to be able to deploy in-situ observation sensors within areas of scientific interest. These missions include sampling ice at high resolution over the arctic, investigating plumes near active volcanos, measuring ionizing radiation within denied HAZMAT or nuclear emergency areas, and sampling the thermal and momentum fluxes within eyewall of an active hurricane. This latter capability is crucial for the success of future UAS missions such as NASA's Hurricane Severe Storm Sentinel (HS-3). Guidesonde will enable the Global Hawk to loiter at a safe stand off distance, well away from highly turbulent storm areas.
Numerical simulations of chemical kinetics are a critical component of aerospace research, Earth systems research, and energy research. These simulations enable a better understanding of the evolution of chemical species over time in domains as diverse as climate and weather prediction, combustion simulation, and air quality prediction.  The time-to-solution in these simulations can be improved by over 30X via computational accelerators like Graphical Processing Units (GPUs) or the Intel Xeon Phi coprocessor, but the state-of-the-art tools for chemical kinetics do not support accelerators.

ParaTools will develop a code generation tool called "Kppa" into a production-grade product that translates a high-level description of a chemical reaction network into simulation code that supports computational accelerators to significantly reduce time-to-solution.  The generated code will provide the same software interface as existing tools to ensure immediate compatibility with popular codes like GEOS-Chem, WRF-Chem, MCM, etc.  Kppa will include an online user productivity environment called "Kppa Cloud" for the development, testing, and benchmarking of chemical simulation codes.  Kppa Cloud will enable users to graphically formulate new chemical reaction networks, maintain a library of chemical mechanisms, develop new mechanisms collaboratively, generate simulation code, explore the computational and numerical characteristics of the generated code, and test the generated code for stability and correctness.

Kppa will enable supercomputer-level performance on smaller computers with lower costs, lower barriers to entry, and enable the rapid creation of high-performance kinetics simulations.  Kppa will build on open source technologies to be backward compatible with the state-of-the-art in modeling and simulation and employ a modular design enabling extensibility to the computer architectures of the future.
This program will develop low friction hard coatings for lubricating mechanical and tribological components used for exploring Mars, the Moon, asteroids, comets and other small bodies. This proposed SBIR program will build on MesoCoat's extensive prior experience in developing dense, hard friction-free coatings.
Wick properties are often the limiting factor in a heat pipe design. Current technology uses conventional sintering of metal powders, screen wick, or grooves to fabricate realtively simplistic wick geometries. Additive manufacturing (laser sintering) of a porous structure would allow much greater freedom in defining the wick geometry and properties. One example is the RDU thermosyphon wick. Valuable real estate was consumed for a liquid reservoir for freeze/thaw tolerance. A more complex laser-sintered geometry could put the reservoir in the center, allowing greater evaporator area, lower heat flux, and lower DT. Another example is loop heat pipes, which are in limited use due to the cost. Laser sintering of an LHP directly in to the evaporator bodye could greatly lower cost, making LHP vaible for commercial use. Applying laser sintering to develop complex wick geometries can greatly extend heat pipe heat transport capabilities and lower cost.
Adsys Controls' Razor UAS Test System is a high fidelity simulation and Hardware-in-the-Loop (HIL) test system.  Razor provides extensive existing capability for high fidelity real world modeling, extensive I/O capability, real-time execution, system fault simulation, full test automation, and extensive diagnostics.  Razor was developed not just as a 6DOF simulator, but as a whole vehicle simulator for testing of state of the art UAS for all avionics and software.  Razor has a proven track record within the UAS market where it has been used to support development and testing of various vehicles by Northrop Grumman and Lockheed Martin.  Northrop Grumman used Razor for their Firebird prototype development program.  Lockheed Martin used Razor for various programs including the development of their Fury UAS.  
Under this program, Adsys Controls will enhance the Razor UAS Test System such that it provides a platform for testing and evaluation of UAS in support of Safety Analysis and Autonomous Operations.  The objective system will result in a comprehensive tool for modular UAS simulation, HIL testing, extensible scenario generation, and fault testing.
This SBIR Phase I project will develop a multifunctional electrolyte for high energy density abuse-tolerant lithium ion batteries with 5 V cathodes such as LiCoPO4. The multifunctional electrolyte comprises of a non-flammable ionic liquid as solvent and a porous ionomer membrane which serve as both separator and lithium cation source. No additional lithium salt such as LiPF6 or LiTFSi is required. The ionic liquid and the ionomer are electrochemically stable at 5 V vs Li/Li+ for many charge-discharge cycles, therefore will enable a lithium ion battery with high voltage and high energy density. The ionomer is a high temperature polymer with anions chemically bonded to the polymer chain. With a super-CO2 facilitated processing technology, porous membrane can be formed with the ionomer with interconnected pores (~50&#37; porosity and pore size of 0.3 ~0.6um). In addition, the porous ionomer membrane has high mechanical modulus and strength and high thermal stability &gt;150 degree Celsius. The high energy density abuse-tolerant lithium ion battery will be enabled by combining: 1. high voltage 5 V cathode; 2. abuse-tolerant cathode that fail mildly; 3. high voltage electrolyte with cycling stability; 4. Superior ionic conductivity ~ 1 mS/cm at -20 degree C; 5. non-flammable electrolyte with ionic liquid; and 6. mechanically and thermally stable porous ionomer membrane. The energy density can be further improved by using lithium metal anode.
The space suit contains metallic bearings at the wrist, neck, and waist, which are exposed to the space environment. There is a need to maintain a high degree of insulation on the surface of the metallic bearings. Current methods to preserve the insulation feature include the use of anodized coatings and polyimide films. However, they are easily damaged and are hard to replace or repair. Innovations are needed to provide a protection method that is easy to maintain. Working with a developer and supplier of systems to NASA, we propose to demonstrate the feasibility of a self-healing insulative polymer coating on the metallic parts that will allow the coating to repair damages under normal operational conditions of the spacesuit. The self-healing capability is afforded through a novel polymer morphology. In Phase I, we will coat 17-4 PH stainless steel flat panels, test coating properties, and evaluate the self-healing performance under near ambient temperatures. In Phase II, the self-healing coating will be applied on a prototype metallic bearing and the coating composition and morphology will be optimized so that it meets all the functional performance requirements.  A functioning prototype metallic bearing will be delivered to NASA. The goal is to achieve TRL 6 by the end of the Phase II program.
Intelligent Optical Systems (IOS) proposes to develop a unique coating that uses fluorescence quenching in an entirely new way to provide high resolution images of the true pressure distribution on surfaces in hypersonic flow. IOS will use unique pigments whose fluorescence depends directly on absolute ambient pressure, not on the partial pressure of oxygen in the flow field, to develop coatings that will allow "legacy" (oxygen-based) visualization equipment to characterize flows in oxygen-free atmospheres. The new pigments will also be completely compatible with temperature indicating materials and binders currently used in temperature-compensated pressure sensitive paints.
In Phase I IOS will create two different oxygen-insensitive pressure-sensitive pigment materials, combine them with a suitable binder, and apply the resulting paints to stainless steel test coupons. The fluorescence of these test samples will be measured under varying static pressures of pure nitrogen, and imaged in a low-speed flow environment at varying angles of attack. This will set the stage for Phase II development and delivery of a complete temperature-compensated true ambient pressure sensitive paint system that can be used to characterize flow around structures in hypersonic wind tunnels and other facilities where oxygen-independent pressure mapping is needed.
This proposal addresses development of techniques that support experimental modeling, simulations, ground testing, wind tunnel tests, and flight experiments, with primary emphasis on ground testing requirements. Advanced System and Technologies Inc. proposes to develop a dual-function, non-contact sensor designed to support simultaneous dynamic Doppler imaging of flow-induced structural vibration (FISV) and flow-field visualization (FFV). The ability to capture full-field non-stationary structural dynamics and correlate these data with the unsteady flow fields which drive them could elucidate, for the first time, the complex mechanisms involved in limit cycle oscillation and transition to flutter in the transonic regime. The comprehensive spatio-temporal content of data captured by the dynamic Doppler imaging system (DDIS) will be compared with predictions from computational models in the transonic regime in support of efforts to more fully address the complex interdependent relationship between structural, aero-dynamic and aero-acoustic phenomenon. 

We describe the core technology behind the DDIS, provide a detailed description of a practical design for deployment and show experimental data which conclusively demonstrate the feasibility of the proposed approach. A structured work plan is presented leading to practical implementation of a demonstrator prototype in a robust and compact instrument architecture suited to ground testing, wind-tunnel and ultimately flight-test deployment.
M4 Engineering proposes to conduct canonical aeroelastic benchmark experiments.  These experiments will augment existing sources for aeroelastic data in the transonic regime.  Models will be constructed with well characterized engineering materials and will include measurement of high frequency pressure data.  A variety of transonic conditions will be tested to provide opportunities for validation of aeroelastic response of transonic flows not previously available.
Composite cryotanks, or Composite Overwrapped Pressure Vessels (COPVs), offer advantages over currently used aluminum-lithium cryotanks, particularly with respect to weight savings. Future NASA missions are expected to use COPVs in spaceflight propellant tanks to store fuels, oxidizers, and other liquids for launch and space exploration vehicles. However, reliability and reusability of the COPVs are of concern, especially in cryogenic temperature applications; this limits adoption of COPVs in future reusable vehicle designs. The major problem with composites is the inherent brittleness of the epoxy matrix, which is prone to microcrack formation, either from exposure to cryogenic conditions or from impact from different sources. If not prevented, the microcracks can grow into larger cracks, leading to catastrophic failure and loss of function of the composite. Accordingly, materials innovations are needed to mitigate, as well as self-heal, microcrack damage in composite cryotanks. In Phase I we propose to demonstrate microcrack prevention and mitigation in composite test panels through the use of a novel nanocomposite matrix containing engineered nanoscale materials which will also enable self-healing of microcracks. Phase II will build upon the Phase I program in order to optimize the material design and to characterize the long-term durability of the scaled-up composite test panels.
The increased system complexity resulting from interaction of human and automated systems in aviation programs introduces new challenges that need to be addressed. Many notable flight incidents can be wholly or partially attributed to crew error, either due to inexperience with the aircrafts automated control systems or in response to component failures or adverse conditions. Flight safety experts can piece together information and data from multiple sources to identify the cause after an accident or incident has occurred whether it is due to human errors, machine failures or a combination of both. It is therefore reasonable to expect that much of the information is already dispersed in various databases and, with the right tools, flight safety experts can identify deficiencies and factors that may provide indicators or serve as precursors of accidents. Such actionable knowledge will lead to better training, design and/or onboard systems to ensure safety. In response to this need, SSCI proposes to build Analytics to Improve Reliability &amp; SAfety in Flight Environments  (AIRSAFE), a software toolbox that assists flight safety analysts in discovering key factors and their interactions among a large number of potentially relevant factors, testing one's hypothesis on the key factors to safety, and identifying previous incidents that support the hypothesis. The software toolbox is built on our previous and on-going efforts, such as DARPA's XDATA program, in BigData machine learning.
To reduce the cost of space travel, NASA is developing In-Situ Resource Utilization (ISRU) methods to collect and convert local resources into products that can be used during the mission. Towards this objective, BlazeTech is proposing the development of an innovative system to filter Mars dust from gas streams. Our system combines the cyclone concept with a spinning and cylinder that acts as a self cleaning filter. The main advantages of the proposed device over conventional systems are the self-cleaning aspect of the filter surface a reduction in pressure drop and volume requirements.  This makes the concept particularly suitable for NASA's requirements which include a modest throughput but a high capture efficiency of the fine particles.
SSCI proposes to develop, implement and test a collision detection system for unmanned aerial vehicles (UAV), referred to as the Asynchronous Sensor fuSion for Improved Safety of air Traffic (ASSIST). The ASSIST system is robust to ADS-B spoofing, and will associate the EO/IR and airborne radar (ABR) tracks generated onboard the UAV with those generated by the ground-based radar (GBR) to  minimize false tracks generated by EO/ABR due to clutter. Under this project, we plan to leverage our FORECAST technology (Fast On-line pREdiCtion of Aircraft State Trajectories) that fuses the ground-based radar information with airborne radar and transponder data to achieve accurate track generation and efficient prediction of potential NMACs in a high-density airspace. We will also leverage our SAFESEE (Sense and Avoid using Fusion and Expansion SEgmEntation) technology - a collision detection system that uses pixel-level fusion of EO/IR optical-flow features to achieve robust probability of detection and low FAR under realistic operating conditions. SAFESEE has been recently flight tested at the Air Force Bombing Range at Avon Park, FL. Under our FORECAST project we developed a capability of simulating communication delay between the ground station and the UAV. We plan to extend this capability and carry out a study of effects of the communication delay on the ASSIST system. Specific Phase I tasks include:  (i) Acquire target tracks and FAR related to existing capabilities from NASA; (ii) Develop, implement and test the ASSIST system; and (iii) Carry out a trade study of the effect of the communication delay on the ASSIST system. In Phase II we plan to carry out extensive  analysis and simulation testing of the ASSIST system, and arrive at a flight testing plan for the continuation of the work beyond Phase II.
We propose a new approach for to the design and fabrication of miniaturized Interferometric Fiber Optical Gyroscope (FOG) that enables the production of smaller IRU with enhanced performance. The size and performance limitations of the standard FOG are being reduced due to the utilization of highly integrated approach of all the gyro components. Specifically, the ASE light source and the receivers, splitters and TIA are all incorporated in a small, robust silicon/silica platform using hybrid integration. In addition, the sensor is using an innovative new coil design and high performance miniaturized IOC that results in tenfold reduction of the bias temperature sensitivity compared to the existing FOG products. The combination of these attributes supports a smaller, lower cost, high performance and robust IRU that can serve future NASA mission needs.
Advanced wing configurations where traditional control surfaces are replaced by dynamically controlled distribution of wing twist and/or camber can provide significant benefits to aircraft performance, such as reduced vibration and noise, increased fuel efficiency. Elimination of traditional control surfaces such as flaps can lead to smoother wing surfaces which are especially important in reducing electromagnetic signature of the wings in military aircraft. In this research and development program, Materials Technologies Corporation (MTC) and its team members propose a three-dimensional warping concept in which the typically closed airfoil section is cut open to create a torsionally compliant mechanism that acts as its own amplification device without needing additional mechanisms whatsoever. Deformation of the airfoil is entirely controlled by out-of-plane warping, a purely geometric effect.
The pace and progress of new sensor technology development continues to lag far behind the broad ranging potential offered by guided wave NDE. In response to NASA solicitation H13.01 for Advanced NDE Techniques for Complex Built-up Structures, Advanced Systems and Technologies Inc., propose a collaborative program which seeks to combine an advanced sensor technology for rapid wide-area capture of ultrasound wave-field data with recent advances in NDE guided wave signal processing. This proposal describes how the Spatially Coherent Optical Vibrometer Array (SCOVA), combined with chirped ultrasound excitation and narrow tone-band decomposition provide deep data sets for application of new spatio-temporal and spatio-spectral analyses to address a broad range of NDE functions pertinent to NASA spaceflight structures. In form and function, SCOVA offers a sensor geared towards practical deployment of guided wave NDE. The ability of SCOVA to capture swept ultrasound data at hundreds of points simultaneously, offers a major advancement in the practical application of guided wave NDE targeting multiple defect modalities in current and future complex spaceflight structures.
In-situ analysis of solar system bodies plays a crucial role in understanding the evolution of our planet, setting the stage for life's origins.  As has been demonstrated by several NASA interplanetary missions, there is no replacement for in-situ observations, like spectral imaging, that prove critical for understanding the context of solar system bodies.  There is, however, a conflict between more capability at the target and the desire for minimizing mission cost.  Minimizing the mass and power of an instrument reduce the size, complexity and therefore the mission cost.   To enable more capable missions without high cost we propose to develop a hyperspectral/multispectral imager designed for a microsatellite platform that will function in a reduced light environment while minimizing the mass and power consumption.  This type of instrument is crucial to the study of small bodies such as near earth asteroids and for missions further afield by maximizing capability while minimizing the instrumental cost and complexity.  The Compact Hyperspectral Aberration-corrected Platform (CHAP) is proposed as a new, innovative instrument using an aberration-correcting holographic grating to make maximal use of two optical components, allowing for functionality over an optical bandpass (400-800 nm) with &lt;100 microradian spatial resolution and 1.44 nm spectral resolution. The optical design of CHAP produces a white light zeroth order image from undiffracted light to be formed at the telescope focus, enabling the co-registration of spatial and spectral information, providing unprecedented context never before seen in an instrument for planetary and lunar science low-light observation. The CHAP spectrograph will be demonstrated in a 3U CubeSat-compatible form factor. Phase I activities will produce a proof-of-concept demonstration on an optical bench-top to a TRL 4 level. Follow on Phase II efforts will produce a CHAP with full capabilities for space environment qualification.
A procedure and supporting computer code for the prediction of noise that radiates from small, vertical lift UAV aircraft is proposed.   The resulting building block procedure is theoretically based but is verified experimentally at several output stages. Noise source models for rotors, lift-fans, engines etc. are developed and validated through specially designed experiments and stored in a component digital library.  For a given small lifting UAV configuration, these noise source models are combined into a hemispheric representation of the total radiated noise.  The total radiated field is governed by the operating state of the vehicle as described by the governing performance model for the chosen configuration.  Standard propagation effects and subjective weightings are used to radiate hemispheric noise levels to ground observers. The resulting computer program can be mathematically flown along prescribed trajectories to estimate ground noise radiation of several small UAV aircraft.
Additive manufacturing is a modern fabrication process by which three dimensional components are built up layer-by-layer.   Each layer corresponds to a cross-section of a 3D CAD model of the product.  LPT proposes an active machine vision, based on a monitoring system to improve Electron Beam Freeform Fabrication (EBF3) processes, by measuring spatial, spectral, thermal and temporal information of the melt pool and element compositions of materials.  The proposed technology will provide clear and accurate information of the melting pool during the metal deposition processes in order to control operation and correct defects.  LPT has extensive expertise in monitoring laser machining processes using various optical sensing technologies.   These sensing technologies have shown significant promise for developing a sensing system to monitor EBF3 processes.  During Phase I, LPT will complete the theoretical design of the active machine vision system.  The proof-of-concept tests will be performed in lab conditions to demonstrate the feasibility of the proposed approach.  The research and development efforts in Phase I will provide a solid base for implementing a prototype during Phase II and commercializing this technology during Phase III.
Oxidation catalysts based on innovative, physically-robust activated carbon materials containing dispersed noble metals are essential in process optimization for production of high-quality potable water in long-duration manned space missions. An innovative catalyst technology is proposed for development to a full-scale advanced life support and space station system size and configuration. The innovative support material is Porous Solid Carbon (PSC) monolith, which has been highly successful at small scale operation under previous programs, but has not been fully developed for spacecraft use to date. This material represents the state-of-the-art in advanced catalyst supports being developed for industrial applications. A catalytic oxidation process based on the PSC catalysts and operated at or below pasteurization temperatures is expected to meet NASA objectives at the minimum power/mass/consumables penalty. The key benefit of the PSC catalyst technology is that it has unsurpassed potential to exhibit the combination of physical stability and high catalytic activity over multi-year operational lives. The Phase I material development program will lay the foundation for an operational pilot system to be fabricated and delivered during the Phase II program.
Physical Sciences Inc (PSI) proposes the development of a longwave infrared (LWIR) imaging spatial heterodyne spectrometer (I-SHS) for standoff detection of clear air turbulence (CAT) and wake vortices from an airborne platform.  PSI will team with Georgia Tech Research Institute (GTRI) who has produced significant research on the application of LWIR hyperspectral imaging for detection of these and other air hazards.  The research has produced extensive simulations, however, the predicted spectral radiance signatures are an order of magnitude below the noise floor of state of the art in LWIR hyperspectral imagers.  The proposed LWIR I-SHS will offer this order of magnitude improvement in noise equivalent spectral radiance through a combination of high throughput and minimal noise-inducing sampling errors owing to the stationary interferometer.  A preliminary systems analysis predicts a per-pixel NESR of 1E-9 W/(cm^2 ster cm^-1) at 16 cm^-1 spectral resolution.  

In Phase I, PSI will formalize a system performance model and will produce and characterize a breadboard I-SHS which will be used to demonstrate a molecular imaging measurement as a surrogate for a wake vortex.  With the support of GTRI, PSI will generate requirements and a conceptual design for a TRL 5 system to be developed in Phase II.
Paragon Space Development Corporation&amp;#174; (Paragon) will advance our Solid Oxide Electrolysis / embedded Sabatier reactors (SOE/ESR) system to generate power from its oxygen (O2) and methane (CH4) products. Leveraging our SOE/ESR technology, Paragon can offer a carbon deposition resistant system capable of internally steam reforming CH4 and generating power in fuel cell mode. Minimal water is required at start up; operations are sustained by recycling water from the affluent using Paragon's spaceflight-qualified humidity control membrane technology. The system is gravity-independent and compact with no moving parts and a high single-pass utilization of feedstock. Leak-tight operations are improved by employing a new 3D glass seal approach. The system will tolerate 100s of thermal cycles in high differential pressure environments.

Our Phase I effort includes laboratory tests to determine the feasibility of employing new sealing features at high differential pressure and multiple thermal cycles. Tests will also confirm simultaneous internal CH4 reforming and fuel cell operation without carbon deposition. 

The SOE/ESR Internally Reforming SOFC integrates cells that operate as either an electrolyzer / Sabatier reactor or a fuel cell. This simplifies operations, lowers hardware complexity, and increases reliability. The proposed system can perform multiple functions without modifications, making it a readily deployable technology for various missions from ISRU on the Moon and Mars to regenerating 100&#37; of a crew's oxygen in habitats and space crafts.
Creare and Embry-Riddle Aeronautical University (ERAU) propose to complete the design, development, and testing of an ultra compact star tracker specifically intended for small satellites such as the CubeSat platform.  Our design is based on proprietary "folded optics" technology previously developed by ERAU for use in military and commercial optical applications that require a compact footprint and high performance.  Furthermore, the design utilizes recent advances in high pixel count CMOS imaging sensor technology.  The folded optics design is superior to conventional refractive optics in miniature star trackers because (1) the compact footprint is achieved without sacrificing accuracy; (2) the light-gathering aperture is much greater, leading to better sensitivity; (3) the aperture geometry makes the shielding baffles smaller; and (4) the imaging sensor can be shielded efficiently from cosmic radiation.  During the Phase I project, we demonstrated a pointing accuracy of the order of 1 arc second testing a brassboard model of our design.  We furthermore completed the design, performed analysis to determine the optimal design parameters, and confirmed the brassboard sensitivity and resolution.  In Phase II, we will fabricate the optimized design, test the prototype in the laboratory and in the field, and deliver the prototype to NASA so that NASA can fly the prototype on a NASA high-altitude balloon mission.
This SBIR Phase I program proposes to develop a bulk processing technology for producing ultra fine grain (UFG) aluminum alloy structures. The goal is to demonstrate a practical, production level manufacturing approach for producing bulk-sized aluminum alloy structures and eventually near-net shape components with nano-scale microstructures. Ultra fine grain aluminum alloys could be particularly advantageous for higher performance, lighter weight spacecraft structures, airframes, and space-frames and structural components needed for next generation commercial and military systems. The effect of different thermo-mechanical conditions to achieve the requisite microstructure-properties also needs to be understood, and will be developed in this project.
A hybrid electric aircraft simulation system and test bed is proposed to provide a dedicated development environment for the rigorous study and advancement of hybrid electric powered aircraft.  The new test bed and simulation system will provide a dedicated platform and set of analysis tools to study, design, and test hybrid electric powered propulsion components and systems for use in commercial, general aviation, military, and UAV systems.  The test bed will allow various hybrid electric propulsion system technologies to be tested to determine performance, reliability, safety, and cost.  These include various motors, motor controllers,gas turbines, batteries, fuel cells, super capacitors, propeller, and fan technologies.  Additionally, the platform could be used to investigate performance characteristics unique to hybrid electric propulsion, determine the most accurate methods for measuring energy used and remaining, and research redundancy possibilities unique to hybrid electric aircraft. Studies performed during Phase I demonstrated that pure electric aircraft are limited in range and endurance by the specific energy of current battery technology. Although there is a great deal of effort being put into advanced batteries, the most practical solution in the near term is to utilize a hybrid electric system. The proposed Phase II program builds upon the Phase I results by developing a detailed propulsion system simulator model for hybrid electric propulsion systems, with the ultimate goal of a bench test model of the propulsion system.  Using a detailed multi-platform/mission trade study, a coupled parallel, uncoupled series, and split series-parallel hybrid system architecture will be compared to determine the most advantageous and efficient.  The propulsion system simulator will also be used to perform a sensitivity analysis of each architecture to determine critical performance aspects for individual components.
NASA's successful development of next generation space vehicles, habitats, and robotic systems will rely on effective Fault Management Engineering. Our proposed innovation aims at developing a method and associated tool suite to support Model-Based Fault Management Engineering (MBFME) for these upcoming projects. Our goal is to leverage Model-Based Systems Engineering (MBSE) concepts, and adapt them to Fault Management (FM). Model-Based Fault Management Engineering is proposed to be the formalized application of modeling to support Fault Management Engineering activities. Traditional approaches to fault management are costly, difficult to execute, and are largely decoupled from the main system engineering activities which aim to capture the system requirements and transform them into a robust and safe design. Our concept will enable the integration of fault management early in the system engineering lifecycle, facilitating the discovery of design weaknesses and enhancing the capability to produce safe, hazard-free systems. This tool suite will enable safety engineers to use system models captured by system engineers to evaluate designs for potential faults, perform safety analysis, and contribute to the overall system models by adding specific faults and associated safety related knowledge
The Assimilation Dynamic Network (ADN) is a dynamic inter-processor communication network that spans heterogeneous processor architectures, unifying components, significantly improving flexibility, efficiency, and overall usability. ADN has the following main features:
-	A uniform programming model for intra-platform communication among heterogeneous    processing resources that creates a homogeneous programming environment.
-	A novel networking layer encapsulates and abstracts hardware resources (e.g. a mixture of multicore CPUs, FPGAs, ASICs) with a uniform communication method &amp; format across the physical resources. 
-	Extends memory resources and network connectivity to facilitate flexible, efficient partitioning and placement of functionality across the heterogeneous physical resources. 
-	Enables gradual optimization during development and beyond, e.g. functions that initially ran on CPUs are moved to FPGA cores for optimization while still remaining in the same application software framework.
Technical Objectives and Milestones for the Phase II project:
-	Establishing an ADN specification
-	Developing ADN libraries for HDL and C designs
-	Expanding hardware support for multicore CPU, FPGA and ASIC platforms
-	Developing tools to facilitate ADN designs
-	Demonstrating and evaluating ADN use in an example application
-	Releasing ADN libraries and tools
The objective of this work is to quantify the reduction of biofilm formation in a water distribution system resulting from an organoselenium surface coating on stainless steel pipes and fittings.  Differentiated from currently marketed antimicrobials, selenium, is permanent, catalytic and does not leach into the environment. This will reduce the problems associated with biofilm growth and fouling in the water recycling system.. Thus, we could draw quantifiable conclusions about the system performance for long term missions in complex water treatment systems containing organoselenium coatings and provide the data to NASA engineers who may then make an assessment as to whether or not this is a viable technology to reduce the need for biocides, reduce ESM, and potentially impact NASA by decreasing the chemical burden for treatment which would decrease payload mass and downtime affecting astronauts' efficiency.
The project will quantify the impact of an organoselenium surface coating within stainless steel pipes and fittings on product water quality and service life of the pipes and fittings over time.   
Objective 1.  Optimize the attachment of organoselenium to the surface of stainless steel to achieve the greatest and most reliable reduction in biofilm growth and formation.
Objective 2.  Assess performance of the organoselenium surface treatment of stainless steel pipes and fittings in a bench-scale system over varied periods of time (i.e. 1 week, 1 month, 3 months) against biofilm accumulation and service capacity.
The overall objective of this Phase I project is to develop a nonlinear trim module in FUN3D for enabling the determined and over-determined trim analyses to be performed by FUN3D with static aeroelastic effects. Based on an optimization formulation, the over-determined trim analysis can determine the optimum control surface scheduling of multiple control surfaces to achieve the best aerodynamic efficiency of the aircraft using the high-fidelity Navier-Stokes (N-S) solver in FUN3D. At the critical loads flight conditions, the optimum control surface scheduling can minimize the design loads; leading to a lighter and more flexible structural design. At the cruise conditions, the optimum control surface scheduling can aeroelastically deform the more flexible structure to an optimum shape for induced drag minimization at cruise.

One non-conventional design concept under investigation by NASA is the Variable Camber Continuous Trailing Edge Flap (VCCTEF) system that utilizes multiple advanced actuators such as shape memory alloys (SMA) to achieve an optimum continuous deformed wing shape for obtaining the best aerodynamic efficiency. The VCCTEF design concept for the aerodynamic efficiency improvement will be ultimately verified by wind tunnel testing. However, such a wind tunnel testing will be impractically without a viable wind tunnel test plan that can provide a guideline for seeking the optimum actuation scheduling in the multi-dimensional design space. This viable wind tunnel test plan for testing the VCCTEF concept can be established by the FUN3D nonlinear trim module.
ColdQuanta's ultimate objective is to produce a compact, turnkey, ultracold-atom system specifically designed for performing interferometry with Bose-Einstein condensates. In Phase II, we propose to develop an ultracold-atom system based on ColdQuanta's channel cell technology. With this approach to ultrahigh-vacuum systems, we can design and fabricate cells that are far smaller and more robust than any other vacuum technology  used with ultracold atoms (of which we are aware). With a channel cell, each stage of BEC production can occur simultaneously throughout a series of interconnected vacuum chambers. The resulting system creates ultracold atoms quasi-continuously and increases production rates by virtually eliminating dead time between sequential operating cycles. Part of the channel cell's small size is due to an integrated atom microchip that can be used to quickly produce ultracold atoms and utilize them for a variety of applications. With the flexibility afforded by atom chips, channel cells can be easily configured for a variety of interferometer geometries, including a Michelson configuration for measuring accelerations and a Sagnac configuration for measuring rotations.
The proposed program will develop titanium/water heat pipes suitable for Spacecraft Fission Power.  NASA is examining small fission power reactors for future space applications with the most recent being Kilopower, which provides roughly 1 kW of electric power. Kilopower uses titanium/water heat pipes to remove the waste heat from the cold end of the convertors.  Previous water heat pipe designs for space fission power are not suitable for Kilopower as they are either for surface fission power and use thermosyphons, or are grooved heat pipe designs, which are not suitable for ground testing.  ACT will develop heat pipes with two different designs that are suitable for Kilopower: Hybrid grooved/screen wick and Self-venting arterial wick. Hybrid wick heat pipes will satisfy the Kilopower requirements and ACT has already successfully tested similar hybrid wick heat pipes.  The self-venting arterial wick has not previously been tested in a vertical orientation but will be investigated as a higher performance, lower mass alternative to hybrid grooved pipes. The overall technical objective of the Phase I and Phase II projects is to develop a titanium/water heat pipe radiator suitable for Spacecraft Fission Power, such as Kilopower. During Phase I, ACT will investigate both a hybrid wick system, utilizing a screened evaporator and grooved condenser design, and a self-venting arterial wick design.  The heat pipe design will also include a small NCG charge, which allows the fluid in the heat pipe to freeze in a controlled fashion as the heat pipe is shut down, avoiding damage, and aids with start-up from a frozen condition. In addition to testing the heat pipes in different orientations, freeze/thaw tolerance will also be demonstrated.
This project will combine the advantages of adaptive materials with the simplistic passive design of state-of-the-art acoustic liners to provide the ability to tune them for specific operational frequencies (ex. take-off/cutback, cruise, and approach). The main deterrent to implementing these methods is not having the materials on hand to provide the functionality needed in a simplistic way. Many proposed solutions are not practical from a manufacturing/cost perspective: too complex or add weight to the aircraft that is not justifiable. CRG has already demonstrated feasibility of the ability to implement adaptive technologies into acoustic liners. The next step is to demonstrate repeatable liner control performance supported by more extensive acoustic testing runs to understand the initial shifting and increased suppression behaviors that have been observed. Also, automated cyclic testing of a given adaptive liner parameter will be executed to demonstrate the durability of the adaptive material and applicability to this application. CRG will focus liner adaptive design initially on demonstration of tuning liner reactance to TRL 3 in Phase I.
The ISTAR Group ( IG) and team mate Thin Red Line Aerospace (TRLA) propose a Venus altitude cycling balloon (Venus ACB), an innovative superpressure balloon architecture that is ideally suited to cloud level mission parameters and to incorporation of a variety of buoyancy control mechanisms that will enable significant altitude cycling capability.  The 5.5 meter diameter vessel is similar to the dimensions contemplated for higher altitude Venus missions. The pro posse Venus ACB balloon platform is based on TRLA's proprietary Ultra High Performance Vessel ( UHPV). The attributes that set UHPV apart in its unique ability to address the fundamental challenges confronting a cloud level Venus balloon mission capable of significant altitude cycling are described in detail for these seven innovative design elements:   1. Strongest, lightest weight balloon option  2. Balloon fabrication is easier, less expensive, more accurate and highly reproducible  3. Greater performance predictability reduces FOS, which reduces mass  4. Standardized fabric and scalability to size  5. Lighter weight fabric  6. Strongest balloon/polar bulkhead integration  7. Potential for balloon-parachute hybrid vehicle
SSCI and MIT propose to further develop, implement and test the Integrated Mission Planning &amp; Autonomous Control Technology (IMPACT) system software for autonomous ISR missions employing collaborating UAVs. IMPACT system is based on real-time learning about dynamic and stochastic environments, and on a capability to autonomously react to contingencies while satisfying the mission objectives and the overall flight safety. 
Phase II focus will be on real-time vehicle assignment &amp; trajectory planning technologies for forest fire monitoring, overall system integration, and evaluation of its performance through computer and hardware-in-the-loop simulations and flight tests at Olin College or Great Dismal Swamp. Key technologies to be further developed &amp; tested in Phase II include: (i) Vehicle assignment &amp; real time trajectory generation for 
collaborative ISR for fire boundary identification using the MOTOR system (Multi-objective Trajectory Optimization &amp; Re-planning); (ii) Robust on-line learning for prediction of the fire spread using the 
intelligent Cooperative Control Architecture (iCCA); (iii) Collaborative assignment for fire perimeter tracking with reactive trajectory planning based on predicted fire spread using MOTOR and iCCA; (iv) Contingency management, including the loss of vehicle, vehicle replacement &amp; mitigation of lost communication link; and (v)
Predictive camera pointing control based on predicted fire spread. The project will leverage a number of technologies recently developed by SSCI and MIT, and integrate various system modules within a flexible and 
user-friendly software product. Phase II deliverables will include the IMPACT software and accompanying documentation, while Phase III will be focused on commercialization of the IMPACT software.
Heat shield technology is a critical component for both re-entry and
hypersonic vehicles. The traditional manufacturing approach for
designing heat shields consists of joining TPS tiles together with an
adhesive that fills any gaps between them. This approach has significant
challenges, including the reduction in thermal-mechanical performance as
compared to that of acreage woven material. Nhung's Notions proposes to
address this problem by modifying existing equipment to mechanically
join these materials prior to infusion. In Phase I, we will determine
the material and pattern parameters required to use with equipment to
prepare the joins while minimizing damage to the pristine woven material
while maintaining consistent thickness between pre- and post- joined
material keeping pattern consistency throughout the process.
The proposed Phase 1 program will fabricate and demonstrate a small diameter single fiber endoscope that can perform high temperature thermal imaging in a jet engine turbine and combustor. Task work will design, fabricate, calibrate, and test the single fiber thermal imaging system in a 1000 C environment. Equipment needs will be documented in detail and system characteristics such as spatial and temporal resolution will be established. Feasibility will be established by demonstrating that a good thermal image of an illuminated high temperature target can be obtained. Imaging access to turbomachinery and combustors in during normal operation or even simple installation in a test rig would be an important advance in aircraft engine diagnosis. A prototype endoscope will be designed, fabricated, and tested in Phase 2.
The proposed Phase 1 program will demonstrate the feasibility of large ceramic to metal joints/seals that can tolerate extreme environments.  The immediate application of the work is bonded sapphire viewports for a Venus probe.  TvU's commercial viewport products have demonstrated that the pressure and temperature constraints of the surface of Venus will be met, while the use of materials appropriate to the atmospheric conditions will satisfy the overall physical constraints. The ceramic bonding and viewport systems will be shown to be adaptable to overall NASA use constraints.  Task work will detail the design of the ceramic to metal joining process as well as a generic viewport design.  A variety of alumina and sapphire fixtures will be fabricated and tested under wide thermal and mechanical conditions.  A specific prototype viewport will be designed, fabricated and tested at Venus lander atmospheric conditions in Phase 1. Phase 1 work will lay out the foundation for a variety of prototype systems developed and tested in the Phase 2 program.
Cornerstone Research Group Inc. (CRG) proposes to advance fundamental material development of a high-temperature resistant, multifunctional polymer system conceived and demonstrated previously by CRG, which will provide NASA with an innovative, low-cost material for thermal protection systems. The proposed material technology results in a polymer system that transitions from a thermoplastic at temperatures below 230F, to a thermoset at temperatures above 230F, and finally to a graphite-like material at higher temperatures.   CRG has demonstrated the concept and feasibility of this material, trademarked as Metagraphite, during a previous research effort. In that effort, CRG confirmed that bulk thermo-mechanical, thermal, and electrical properties of the polymer could be altered through the application of varying amounts of heat. The described polymer can be combined with fabric reinforcement to create a system that presents NASA with the potential for low-cost, adaptive structural materials with properties ranging from those of thermoplastics to carbon matrix composites. Such materials would find wide use in thermal protection systems and high-temperature components for launch propulsion system rocket nozzles.  The extremely low-cost raw materials and the range of material properties available will enable innovative processing methods and reduced component manufacturing costs when compared with state-of-the-art materials.
This SBIR project seeks to develop a miniature sensor for mass measurement of size-classified aerosols. A cascade impactor will be used to classify aerosol sample into 8 uniform bins on a logarithmic scale, covering an aerodynamic size range of 0.01 to 10 microns. In each of the 8 stages aerosols will be deposited on a MEMS microbalance that will record aerosol mass in real-time. The proposed device incorporates state-of-the-art MEMS microbalances from the subcontractor femtoScale in the applicant MSP Corporation's advanced cascade impaction technology. With the help of a consultant, who has decades of experience in airborne aerosol measurements, we propose to adapt this device to unpiloted aircrafts, like Black Hawk for NASA's Airborne Science Program. During Phase I, we propose to design a miniature cascade impactor with a low flow rate of 0.5 liters per minute or smaller. A prototype will be built with 8 stages pertaining to 8 aerosol size classes. MEMS microbalance on each stage will measure the deposited aerosol mass with a frequency of 1 Hz. This prototype will be tested and validated in Phase I and the final flight-worthy deliverable will be built in Phase II. The proposed device is expected to weigh less than 5 kg and consume about 100 W electrical power. Besides being valuable for NASA's airborne science program, this instrument will have numerous R&amp;D and industrial monitoring applications that need real-time aerosol measurements down to 0.01 micron.
Indiana Integrated Circuits, LLC (IIC) proposes to develop the customizable, high-performance microchip interconnect technology called Quilt Packaging (QP) to address NASA's requirement for high performance integration of heterogeneous microwave systems. 	QP is an affordable, scalable, patented edge-interconnect technology for joining microchips of disparate materials and/or process technologies into monolithic-like systems that perform electrically as if they were one chip. QP enables sub-micron chip-to-chip alignment, extremely small (&lt; 10 micron) chip-to-chip gaps, and can be implemented in multiple substrate materials, including SiGe, GaAs, Si, InP, GaSb, SiC, GaN, and more. Quilt Packaging can enable extremely low-loss, wide-bandwidth integration of MMIC modules comprising disparate material systems and/or process technologies. QP has demonstrated less than 0.1 dB insertion loss up to 100 GHz, and under 1 dB out to 220 GHz. Initial reliability testing of QP chipsets have demonstrated no degradation or mechanical issues, having undergone thermal cycling from -40 C to 125 C for over 350 cycles and counting. In addition to excellent microwave performance, QP has the potential for decreasing system size, weight and power. The proposed effort will leverage previous work in GaAs and Si QP to demonstrate a heterogeneously integrated "quilted" chipset of SiGe, GaAs and/or InP chips. Resulting data from this Phase I will directly apply to the design, fabrication and demonstration of a functioning MMIC module in Phase II. Throughout Phase I consideration will be given to NASA system needs and transition to production-level Quilt Package chip fabrication with commercialization partners Research Triangle Institute and Northrop Grumman Corp. for manufacturing scale-up of Quilt Packaging enabled MMIC modules.
The innovative methodologies proposed in this STTR Phase 2 project will enhance Loci-STREAM which is a high performance, high fidelity simulation tool already being used at NASA/MSFC for a variety of CFD applications.  This project will address critical needs in order to enable fast and accurate simulations of liquid space propulsion systems of relevance to NASA's Space Launch System (SLS) program (LOX/RP-1 engines such as F-1 or potential replacement of RD-180, and LOX/LH2 engines such as RS-25, RS-25D/E, RL10, J-2X). The key methodologies which will be integrated into a production version of the Loci-STREAM code are the following: 
(a)	Primary atomization modeling using Level Set methodology to model the liquid (core) jet,
(b)	Lagrangian particle tracking (LPT) for the droplets resulting from primary atomization,
(c)	Evaporation models for the droplets, 
(d)	Flamelet models for turbulent combustion,
(e)	Adaptive tabulation for flamelet models, and
(f)	Hybrid RANS-LES (HRLES) methodology. 
Integration of the above methodologies into Loci-STREAM will result in a state-of-the-art multiphase combustion modeling tool which will enable fast and accurate design and analysis of liquid rocket engine flow environments, combustion stability analysis, etc. which constitute critical components of space propulsion engines that are part of NASA's SLS.
The proposed Phase I program aims to develop new methods to support safety testing for integration of Unmanned Aircraft Systems into the National Airspace (NAS) with a particular focus on testing the collision avoidance (CA) algorithms of a UAS Sense-and-Avoid (SAA) system.  The two primary issues addressed by this research are: (i) the risk that incorrect/mismatched modeling assumptions will skew simulation analyses and (ii) the fundamental difficulty of verifying the performance of autonomous systems that dynamically react to the environment.  In particular, this research program would develop novel methods for conducting non-parametric, closed-loop simulation testing of collision avoidance algorithms.  The technology generates a campaign of simulation experiments that automatically adapt to the algorithms in question. The purpose of this innovation is to expose potential vulnerabilities in UAS autonomy that are generated through the interaction of autonomous UAS algorithms with other agents such as an intruding aircraft operating under ``right of way rules".  This work augments both the probabilistic open-loop testing methods, where agents do not react, and closed-loop testing where agent behavior is fixed a priori.
We proposed to design, build and test a high temperature Pneumatic Drill and Trencher system for Venus subsurface exploration. The Venus Drill and Trencher will be hybrid systems capable of acquiring surface and subsurface regolith as well as pulverized rocks (i.e. cuttings) from depth (the exact depth will be driven by the science requirement). The drill and the trencher unique sample delivery system will be able to transfer samples as they are being acquired, directly into the science instruments. Hence, these systems could be a single deployment system &amp;#150; it will have to drill/cut down once to deliver samples, and never retract. If the Venus Drill and/or Trencher will be deployed from a robotic arm, the system could be used multiple times. If the Venus Drill or the Trencher will be body mounted or mounted to a single degree of freedom system (spring deployable single action arm), it would be deployed once. Depending on the deployment requirements, the Drill and the Trencher could require just one actuator, while the remaining degrees of freedom (lowering the system to the ground and/or deploying the system some distance from the lander) could be achieved by a set of springs and hinges.
The ultimate aim of proposed efforts are to develop innovative material and process (M&amp;P) engineering technology to reduce thermal resistance between space power components and cold plates of the space system. This proposal will use AMSENG produced few layer graphene with carbon nano tubes (CNT) to design and process the Advances Thermal Interface Material Systems (ATIMS) to achieve the performance improvement and to achieve the High Heat Flux capability. An increase in mechanical compliance; increase thermal cycles before degradation and efforts to ensure ease of workability for the engineered TIMS are also planned. The proposed tasks use the innovative engineered Graphene-CNT and High K BNNT - AlN conductive phases with use of AMSENG's innovative ultra low out gassing polymers for space application through the computer assisted thermal interface modeling for guiding the material selection. Our aim is to illustrate gains in cyclic durability at operating temperatures between -55C and 200 C. The proposed concepts have possible potential for providing improvements in peak junction temperature rise, &amp; can yield a several fold improvement in cyclic durability, resulting in desired improvements for the robust space based power systems and spacecraft thermal management components. The proposed efforts are also geared to illustrate four fold increase in thermal conductance in thermal greases and state of the art interface materials and targets achieving &gt; 10C reduction in the  junction temperature for the typical heat flux of 50W/cm2. Plans are also presented to conducts experimental evaluation of the M&amp;P engineering concepts that can suggest further maximization of improvements in ATIMS performance when higher flux rates (100 W/cm2) are involved.
ORBITEC proposes to develop the Miniature Nontoxic Nitrous Oxide-Propane (MINNOP) propulsion system, a small bipropellant propulsion system which we offer as an alternative to miniature hydrazine monopropellant thrusters for CubeSat-class spacecraft.  As compared to state-of-the-art hydrazine systems, MINNOP propulsion will provide significant increases in specific impulse (in bipropellant mode) and comparable levels of minimum impulse bit (in cold gas mode), and it will do so with a nontoxic, environmentally benign, self-pressurizing set of propellants.  In Phase I, we will focus on demonstrating the operation of the bipropellant thrust chamber, and ignition of that chamber within appropriate weight constraints.  Our preliminary propulsion system design is intended to occupy 1U of a 3U-size CubeSat.
In Topic Z1.01, NASA seeks advanced photovoltaic technologies that can deliver cost, reliability, mass, volume and efficiency gains over current solutions.  Future photovoltaic systems range in size from Cubesat-class to International Space Station sized arrays.  Operational domains range from low Earth orbit to interplanetary distances.  Power levels may reach 100's of kilowatts operating at several hundred volts.  Specific power of greater than 130 w/kg, and stowed volumes 4 times denser than the current state of the art are required.  These functional parameters drive the need for large flexible blanket arrays comprised of solar cell modules assembled in myriad configurations.  Manufacturers of flexible solar arrays currently use manual processes to accomplish final assembly.  NASA's cost and reliability goals require new approaches to manufacturing.  Building on recent successes in flexible substrate photovoltaics, our proposed effort creates a preliminary design for an automated final assembly manufacturing cell for flexible blanket solar arrays.  Modular, scalable, and flexible, the proposed system incorporates the latest in machine vision, material handling, laser welding, and automated test capabilities.  When fully implemented in Phase II, the system will deliver immediate return on NASA's investment through labor reductions and reliability improvements.  Missions from across NASA's entire portfolio will benefit from the significant cost savings, allowing fiscal resources to be focused on the primary scientific or operational goal.
To-date, the realization of high-performance liquid bipropellant rocket engines for ascent vehicle and sample return applications has largely been hindered by the inability to obtain "on-board" pressurization through a light-weight and low-complexity pump. Ventions seeks to fulfill this critical need by designing, fabricating and testing an electric pump for a Mars Ascent Vehicle compatible with LOX / propane produced via in-situ resource utilization to achieve significant performance improvements over the current baseline.
National Aeronautical and Space Administration's (NASA) Aviation Safety Program "seeks capabilities furthering the practice of proactive safety management."  Specifically, one of the key interests in Topic A1.04 are proposals for Remaining Useful Life prediction techniques.  In response, Nokomis is proposing to develop an Electronic Health Monitoring (EHM) Sensor Unit which would be able provide accurate estimates of the Remaining Useful Life of avionic systems.  This sensor module would identify changes in the unintended electronic emissions of various flight-system electronic components to determine the current health state and predict the future reliability of the scanned system.  Designed as a handheld unit which would allow for system scans of components while installed in the aircraft, the EHM Sensor Unit would be capable of scanning and returning results in as little as 3 seconds per system scanned.  This speed would allow for frequent maintenance monitoring, including during the brief turnaround periods experienced at the gate.  This technology would allow NASA, as well as flight-system and aviation maintenance providers, to better monitor the electronic health of these critical avionic components, as well as better predict their future lifespan, allowing for systems to be repaired or replaced prior to an unanticipated failure.
Advanced Systems &amp; Technologies proposed WHISPER (Wireless Hybrid Identification and Sensing Platform for Equipment Recovery) solution to NASA's need for automatic location and tracking of a large number of individual crew items in a space habitat microgravity cabin is to combine a EPCglobal compliant WISP wireless identification and sensing platform (a quarter-sized device that is powered and read by off-the-shelf UHF RFID readers and contains a microcontroller and INS) with an IR sensor that works in conjunction with AS&amp;T's existing Low Latency Infrared Positional Operating Projection (LOLIPOP) system. This would enable simple wireless location tracking of an unlimited number of items such as fasteners, hand tools, and clothing but would also do more complex orientation and velocity tracking. WHISPER modules can also be attached cold thruster maneuver platforms or even personnel for monitoring tasks or exercise.
The liberation of particles induced by rocket plume flow from spacecraft landing on unprepared regolith of the Moon, Mars, and other destinations poses high mission risks for robotic and human exploration activities. This process occurs in a combination of "extreme environments" that combine low gravity, little or no atmosphere, rocket exhaust gas flow that is supersonic and partially rarefied, and unusual geological and mechanical properties of highly irregular surface regolith. CFDRC and the University of Florida will deliver unique plume driven erosion simulation software for such environments by combining novel granular physics simulation modules developed by UF with multi-phase gas-granular flow simulation software developed by CFDRC. Granular flow constitutive models, formulated through first-principle 3-D Discrete Element Method particle kinetics and implemented in an efficient Eulerian gas-granular flow solver are the foundation of this software. The fidelity of these simulations will be advanced towards simulating particle compositions with broad shape and size variations. Novel particle kinetics modeling concepts will be applied to formulate granular flow physics models for both, realistic irregular particle shapes and dispersed particle size distributions. Phase I demonstrated the successful implementation and validation of irregular granular shape physics modeling in CFDRC's gas-granular multi-phase flow solver. An approach for extension to poly-disperse particle mixture simulations was also developed. Full integration of these models in Phase II will enable the simulation of gas flow interaction with poly-disperse, irregular shaped particle materials. Extensive verification, validation, and application demonstrations will be performed. The proposed technology development will result in unprecedented computer modeling capability for predicting liberation and flow of realistic granular material compositions in extreme extra-terrestrial environments.
Automation improvements are needed to reduce the dependency on human reflexes and unreliable data links. Modern autopilots are capable of detecting loss-of-GPS and loss-of-communications. There is no mechanism for the aircraft to autonomously return to a safe landing zone under these conditions. Furthermore, experience has shown that existing controllers are not good at detecting bad position data caused by intermittent GPS. These conditions are known to cause flyaways.  The only existing protection is the operator. There is currently no automation that can protect an SUAS when the flight controller is unable to recognize that the GPS and comm links are unreliable.

A unique feature of the invention is a dual onboard flight controller. One is a failsafe controller, and the other is experimental. The failsafe controller allows access to control outputs by the experimental controller. Meanwhile, it detects conditions such as lack of GPS reliability, imminent airspace violations, flight profile violations, imminent loss-of-control, and loss-of-stability by experimental software. If the failsafe controller detects one or more of these conditions, then it autonomously seizes control authority from the experimental flight controller and navigates the aircraft to a pre-determined recovery spot, using visual navigation if necessary. No comm link is required.
NOHMs Technologies proposes to develop a novel ionic liquid electrolyte formulation developed for the Lithium-Sulfur chemistry that can protect the lithium metal and has demonstrated superior performance and safety characteristics with the potential to offer 600 Wh/kg on the cell level. For this NASA Phase I project, NOHMs Technologies will optimize our proprietary ionic liquid electrolyte and demonstrate how the electrolyte provides safe, non-flammable high-energy performance and provides Li-metal protection. NOHMs will provide full cell data and analysis to demonstrate the feasibility of our system to meet NASA's 'Far Term Mission' specific energy and energy density goals. The battery technology under development by NOHMs is capable of delivering batteries with specific energies that are three times higher than today's state of the art Li-ion battery systems. For NASA missions, this can be translated into increased operational range, functionality, or payload capabilities and significantly reduced operational cost. NASA applications.
A key objective for NASA's next rover mission to Mars is the demonstration of oxygen production from atmospheric carbon dioxide.  Such a technology demonstration may pave the way for a future sample return mission to the Red Planet as well as possibly a future manned mission to Mars.  A necessary component in such a demonstration system is a blower or compressor that can deliver the necessary carbon dioxide mass flow to a production plant.  Creare proposes the development of a multistage radial flow compressor that is capable of compressing 400 g/hr to a pressure of up 0.1 Bar.  The compressor will be a turbomachine based on our space-qualified vacuum pump technology currently operating on the Curiosity rover in Gale Crater on Mars.  In Phase I, we propose to design the compressor and perform benchtop testing.  In Phase II, we propose to design and build a full-up multistage system.
Thorough understanding of aircraft airframe and engine noise mechanisms and the subsequent acoustic propagation to the farfield is necessary to develop and evaluate noise mitigation concepts. Therefore, continued assessment and development of advanced prediction methodologies and tools is essential. Despite significant progress made in computational fluid dynamics (CFD) in past several decades, some production unstructured CFD codes used at NASA for noise prediction are only 2nd order accurate at best. In this SBIR study, we propose to develop a modular high-order scheme with low dissipation flux difference splitting that can be integrated into existing CFD codes for use in improving the solution accuracy and to enable better prediction of complex physics and noise mechanisms and propagation.  The salient features of our proposed approach include: (1) high-resolution schemes with physics-based low-dissipation flux-difference splitting; (2) very low memory requirements; and (3) modular structure for easy integration into existing CFD codes. During Phase I, a module providing 3rd order accurate schemes will be developed and integrated into FUN3D code. Verification and validation studies will be conducted to demonstrate the improved solution accuracy. During Phase II, 4th order accurate schemes will be developed and implemented with FUN3D, and the performance of improved schemes will be assessed for realistic aeroacoustic problems. Adaptive use of high-order schemes near solution discontinuities (such as shocks) will be investigated. Phase II plans will also consider integration of the high-order module with other unstructured CFD codes such as USM3D and Loci/CHEM.
While small satellites continue to show immense promise for high-capability and low-cost missions, they remain limited by post-deployment propulsion for a variety of activities like precision maneuvering, orbit change and controlled re-entry / recovery. Furthermore, any on-board propulsion system capable of providing sufficiently high delta-V is likely to impose constraints on handling, storage, operations and safety that may limit consideration as a secondary payload. Ventions proposes to overcome these limitations by developing a compact, light-weight and low-cost 3U cubesat propulsion system that uses non-toxic propellants to provide approximately 125m/sec of delta-V within a 1kg and 100mm x 100mm x 100mm mass and size budget.
The proposed innovation is the development of a cathode feed electrolysis cell stack capable of generating 3600 psia oxygen at a relevant scale for future exploration missions.  This innovation is relevant to NASA's need for compact, quiet, efficient, and long-lived sources of pressurized oxygen for atmosphere revitalization (AR) and EVA oxygen storage recharge.  Present AR equipment aboard International Space Station (ISS) consists of power-intensive, noisy compressors that have service lives less than 2 years.  Proton's proposed electrolyzer stack will eliminate the need for these compressors, by developing a cell stack that can produce 3600 psia oxygen via electrochemical compression.  This innovation results in a quiet, efficient solid state device with no internal moving parts to service or fail.
The Sense-and-Avoid Display System (SAVDS&amp;#174;) represents a technology that was developed to address the mid-air collision risk for low-flying Unmanned Aerial Vehicles (UAVs). Over a 4-week period in July-August 2013, SAVDS was used as a decision support tool (DST) for NASA's Marginal Ice Zone Observations and Processes EXperiment (MIZOPEX) Project in northern Alaska. Integrated with a Thales-Raytheon Systems (TRS) Sentinel AN/MPQ-64 (FRP-5) radar data feed, SAVDS was housed in a UAV Ground Control Station and served the time-critical DST function of showing the real time location and altitude of NASA-supported UAVs and other airborne vehicles within and around a pre-defined safe separation transit corridor. It was within this operational framework that SAVDS served as a DST which enabled the first FAA-approved series of NASA-supported UAV science flights in the domestic National Airspace System without ground-based or chase plane-based visual observers. In this Phase 1 SBIR, SAVDS, Inc. seeks to further refine and improve its functionality by performing a feasibility test involving detailed analyses of SAVDS log files from the MIZOPEX Project and other past UAV missions equipped with the Sentinel radar. Advancements to SAVDS, as here set forth in this SBIR Phase I proposal, are envisioned as enabling future NASA Earth Science Missions that will ultimately involve fully autonomous UAVs. The long-term goal is to embed the data processing capabilities and sensor-and-avoid algorithms of SAVDS in the onboard flight safety systems of UAVs that will be collecting airborne earth science data beyond the range of visual observers.
Advances in structured heterogeneity together with nanomaterials tailoring has made it possible to create thermoelectrics using high temperature, polymer composites. While such thermoelectrics do not have the capability to approach the efficiency of top performing ceramic modules such as BiTe, they do provide two unique aspects of use in energy scavenging: the ability to conform to irregular large shaped areas easily, and the ability to integrate kinetic energy scavenging together with heat scavenging. During Phase I, the group at Wake Forest University demonstrated that the combination of thermal and vibrational power production is actually synergetic &amp;#150;the amount of power generated is greater than the sum of the individual components. This improvement in nanocomposite thermoelectric performance, coupled with effective kinetic energy scavenging makes the piezo-thermo-electric "PowerFelt&amp;#153;" applicable to a wide range of power collection scenarios. Although the goal of making a 1-m2 material was not completed, significant progress has been made and this capability will be available in Phase II. A sample of "PowerFelt&amp;#153;" was sent to the National Institute for Standards and Testing for independent testing. Their results confirmed that  "PowerFelt&amp;#153;" was significantly better than other power producing films and competitive or better than ceramics that cannot conform to the shape of the heat and vibration source. The material was successfully field tested at the Stennis Space Center at their liquid nitrogen supply facility.
Space Micro has developed the architecture for a radiation hardened memory subsystem that targets DDR3-and-beyond generations of DRAM. The architecture combines server platform error correction and memory buffer-on-board schemes with Space Micro proprietary techniques for radiation hardening and size, weight, and power reduction. During the NASA Phase I effort, Space Micro demonstrated two key elements of the architecture: (1) a scalable error correction coding (ECC) scheme that optimizes the robustness vs. efficiency vs. chip count tradespace, and (2) a Rad Hard By Design (RHBD) timing circuit for advanced DRAM fly-by routing. Space Micro has developed a Phase II plan for developing a server platform-like bridge chip that integrates ECC, interface logic, and timing circuitry into a high performance, low size, weight, and power (SWaP) memory subsystem suitable for next generation spacecraft computing.
There is a great need for better understanding of the continuity of atmospheric processes on multiple scales ranging from several kilometers to the order of a meter. Although the general features of this process are well-established, they are poorly quantified. This lack of understanding leads to significant uncertainties in the parameterizations used in numerical models of weather prediction, pollution transport and diffusion, etc. Improvement of the models is heavily dependent upon available data, increasing the need for improved remote satellite and terrestrial based measurements as well as affordable, capable, and easily operated in situ measurement systems. The complementary nature of these two measurement techniques ensure that recent work toward the revolutionary use of unmanned aircraft systems for in situ measurements has the potential to greatly enhance data gathered through remote sensing and significantly affect the study of the atmospheric boundary layer. 

Black Swift Technologies proposes the creation, testing, and validation of a new in situ atmospheric sensing instrument, the Coordinated Atmospheric Profiling System (CAPS).  This will be realized as a coordinated multi-aircraft system with each unmanned aircraft consisting of tightly integrated airframe, avionics and sensors specifically designed to measure atmospheric parameters (i.e., temperature, pressure, humidity, and 3D winds).  Each aircraft will be cost-effective, simple, rugged, and easy to operate while performing atmospheric experiments with the required level of accuracy for scientific missions.  Furthermore, the system will be designed with the intention of extending multi-aircraft functionality to other Earth observing missions through the use of a removable nose cone with well documented power and data interfaces. This further enables simple connection to the autopilot and on-board computer to enable intelligently optimized data gathering and coordination.
Aurora proposes to transition UMD methods for insect-inspired, lightweight vision- and optical sensor-based navigation methods for a combined air-ground system that leverages the unique capabilities of airborne systems  to achieve a progressively refined  map of the exploration region which can be accessed by agents within the autonomous team for localization, and by scientists and other ground observers.
Research during the Phase&amp;#150;I developed requirements, performed analyses and basic research that provided proof-of-concept demonstrations for navigational capabilities that will enhance the autonomous planetary and asteroid robotic exploration.

Techniques derived from recent research were explored to demonstrate a concept for autonomous bio-inspired vision aided navigation to achieve navigation in GPS and magnetometer denied environments, generate obstacle maps and a 3 dimensional map of the environment based on optical flow and navigating to the origin of a map only based on optical flow input. This innovative research is providing a demonstration of the possibility of developing low size, weight and power solutions for vision based navigation by leveraging research on bio-inspired methodologies. 

During Phase-II further maturation of the algorithms, implementation on a higher fidelity simulation and prototypes and a conceptual design for a flight system will be pursued.
Innovative low cost, lightweight, durable structural concepts that feature simple robust designs, efficient packaging, and assembly are critical to the development of pressurized inflatable systems for NASA future space explorations. Advanced development of high-temperature resistant fibrous material concepts that do not require parasitic thermal protection systems is essential to meet these goals. CFDRC research team proposes a high performance Structural Inflatable Heat Shield (SIHS) featuring a flexible-deployable thermal protection system (FTPS) that simultaneously performs as mass-optimized hot structure capable of supporting the mechanical loads associated with atmospheric entry. The proposed innovation facilitates reduction of heat shield mass fraction by balancing the vehicle entry parameters with heat shield diameter to take maximum advantage of the shield's mechanical and thermal capabilities. Phase I effort will focus on identification and testing of high performance, high-temperature materials. An integrated test and analysis techniques will be utilized to fully characterize the hot materials for light-weight deployable structures and to fully capture the combined effects of processing, microstructure fiber geometry, temperature-related properties and performance. Phase II will focus on fabricating a subscale prototype of FTPS-based inflatable structure, and conduct extensive strain and thermal testing and analysis of the SIHS under different thermal and structural loading conditions.
Advanced composite materials processable by cost-effective manufacturing play an important role in developing lightweight structures for future exploratory missions. With growing demand for improved mission performance and reductions vehicle mass, advances in polymer systems with extreme thermo-mechanical properties are critical. 
The primary objective of ATSP Innovations' Phase I work will be to fabricate and test low cost aromatic thermosetting copolyesters (ATSP): (1) for high performance composite structures for high temperature applications, (2) with high resistance to microcracking at cryogenic temperatures for use in next generation spacecraft missions. Our team partner, the University of Illinois at Urbana-Champaign (UIUC) will assist ATSP Innovations to perform advanced characterization and provide technical support for this project.  
ATSP Innovations and UIUC have developed ATSP for high performance composites that are stable at high temperatures and have an intrinsic resistance to microcracking. The liquid crystallinity of the polymer results in a local matching of CTE between fiber and matrix yielding minimal thermal residual stress in composites and higher fracture toughness than current resin systems. These capabilities allow the ATSP to address a wide range of current and future applications (at both cryogenic and high temperature regimes) critical to future NASA missions. 
The synthetic development of ATSP was a major innovation in the field of polymer science. ATSP shows excellent performance as adhesives, flame resistant foams, and tribological wear coatings. ATSP resins possess the unique attribute among high temperature thermosets of solid-state bonding in a fully cured state to produce chemically contiguous specimens by Interchain Transesterification Reaction (ITR). This may open new modes of fabrication with relevance to NASA missions and the wider aerospace industry.
The proposed work will develop lightweight multifunctional composite materials based on high hydrogen content polybenzoxazine (PBZ) composites that provide excellent radiation shielding capabilities as well as high strength, stiffness, and toughness. This approach provides a novel path to addressing NASA's need for lightweight radiation shielding materials that can also serve as structural members and provide protection from micrometeoroid impact.  
Polybenzoxazines are organic thermosetting polymers that can be tailored at the molecular level to optimize characteristics that are particularly advantageous for radiation shielding applications, such as high hydrogen content.  Polybenzoxazines are also easily synthesized from inexpensive raw materials and the precursor, either monomeric or polymeric, can lead to cross-linked, lightweight, and thermally stable polymers.  Our project will address the radiation shielding needs identified by NASA by developing lightweight composites containing a high hydrogen content polybenzoxazine resin matrix and ultra-high molecular weight polyethylene (UHMWPE) reinforcing fibers.  UHMWPE fibers are the preferred reinforcing fiber for radiation shielding applications due to their high hydrogen content.  Recent developments in PBZ chemistry now allow for crosslinking at lower temperatures that will not be detrimental to the polyethylene fiber structure.
Plasma techniques are proposed for the extraction of oxygen from the abundant carbon dioxide contained in the Martian atmosphere (96 &#37; CO2).  In this process, CO2 is directly decomposed in an energetic plasma forming O2 and CO, which are immediately separated.  The Phase I project will clearly demonstrate the feasibility of achieving these goals by focusing on key aspects of the technology, such as efficient microwave plasma conversion at relevant pressures and processing rates as well as effective techniques for O2 separation from product gases.  System mass and energy efficiency of this novel technology will be compared to those for SOA processes.  The Phase II program will advance the technology through a more in depth development effort to the point where a fully functional prototype will be assembled and tested.  Successful culmination of this effort will result in a self-contained, energy efficient technique that can be utilized by robotic precursor missions to Mars to stockpile oxygen in support of future manned missions to the planet.
We propose the development of a 6-inch wafer bonding process to allow bonding of a multi-junction inverted metamorphic (IMM) tandem solar cell structure to an upright single-junction Ge solar cell.  The process will use SU8 epoxy to provide the mechanical connection between the substrates with an embedded metallic grid to provide electrical conductivity across the bonded interface.  This process will enable the manufacture of next-generation, five-junction cells with the potential to achieve efficiency &gt;37&#37; under AM0 illumination in high-volume production.  The proposed process will be designed for 6-inch substrates and will be low-cost, scalable, and high-yield.  Compared to conventional wafer fusion approaches, this technique will be much more tolerant of the rough surfaces typical of metamorphic materials and eliminate the need for any pre-bonding surface polishing or preparation.
Exploration of planetary environments with current robotic technologies relies on human control and power-hungry active sensors to perform even the most elementary low-level functions. Ideally, a robot would be able to autonomously explore novel environments, memorize locations of obstacles or objects, learn about objects, build and update an environment map, and return to a safe location. All of these tasks constitute typical activities efficiently performed by animals on a daily basis. The primary objective of the proposed research is to develop a biologically-inspired neuromorphic application that will translate the above-mentioned functionalities into an autonomous robot or unmanned aerial system (UAS). The Phase I effort implemented a neuromorphic system capable of exploring an unknown environment, avoiding obstacles, and returning to base for refuel/recharge without the use of a Global Navigation Satellite System (GNSS). This system was successfully tested in a Mars-like virtual environment and a simple robot. Leveraging Phase I results, the Phase II effort will develop visual processing based on passive sensors in order to find, identify, localize and interact with objects and use this information to enhance navigation capabilities. Neurala's neuromorphic application will also allow for human guidance through an intuitive user interface. Low-power hardware will be evaluated to facilitate real-time performance in robots and unmanned platforms.
Lithium-Ion batteries have been a main source of energy for many aerospace applications over the past decade. Future space missions are facing a number of challenging requirements, including significant increase in specific energy, approaching 500 Wh/kg, and energy density of 700 Wh/l at cell level. Compared to state-of-the-art technology today, a reduction in mass and volume are necessary, along with improvements for functioning in harsh space environments and an increase in reliability. Yardney Technical Products, Inc., a world leader in cutting-edge battery technology, in collaboration with Purdue University, proposes developing lithium-sulfur battery technology. This will have a cathode based on a novel, sulfur mesoporous carbon composite. In addition, the proposed Phase I research will include lithium dendrite suppressive electrolyte for a significant improvement in safety.
We propose the fabrication of large format, long wave infrared (LWIR) mercury cadmium telluride (HgCdTe or MCT) detector arrays where the cutoff wavelength is extended to 12 micron at cryogenic temperatures for use in missions to near earth objects, comets, and the outer planets.  The MCT detector arrays will be a high performance improvement to meet the detector needs for future NASA missions.  The MCT material for these detector arrays will be grown by molecular beam epitaxy on cadmium zinc telluride (CdZnTe or CZT) substrates to produce high quality semiconductor material with low defect densities. In this Phase I proposed effort EPIR, Inc. (EPIR) will fabricate a prototype focal plane array (FPA) where a 12 micron cutoff LWIR MCT detector array on a CZT substrate will be hybridized to a small format readout integrated circuit (ROIC) for capability demonstration purposes.  EPIR will deliver this prototype FPA to the government for further evaluation.  Should this effort progress to Phase II, then LWIR MCT detector arrays will be fabricated for hybridization to large format 1k x 1k ROICs for implementation into future planetary science space missions.
Proposed is an architecture for large (&gt;200 m2 surface area) photovoltaic (PV) arrays, deployable from compact stowage with one single, continuously smooth sweep of motion and directly scalable to sizes at least an order of magnitude larger to provide surface areas beyond 4000 m2 -- the area associated with 1 MW power production, the upper limit of projected solar electric propulsion (SEP) needs in 10-20 years.  In particular, examined is the integration of a version of the "spiral fold" (an origami-like surface mechanism to wrap without stretching a tessellated sheet on a hub) and wrap rib technology (supporting ribs that also wrap around the hub when stowed) with some additional concept elements to increase stiffness when deployed and the robustness of deployment.  Kinematic conflicts between components with geometric mismatch in a real-life hardware context re resolved, metrics for stowage and structural performance are assessed, and a streadmlined concept design is defined to satisfy all targeted specifications.  TRL level is advanced from 1 to 3.
The overall objective of this Phase I project is to develop a hybrid approach in FUN3D, referred herein to as the Linearized FUN3D, for rapid aeroelastic and aeroservoelastic (ASE) design and analysis.  The Linearized FUN3D solves a linearized Euler equation with a transpiration boundary condition using the FUN3D steady N-S solution as the steady background flow to efficiently generate a Reduced Order Model (ROM) in the form of the frequency-domain Generalized Aerodynamic Forces (GAF) matrices due to the structural modes, control surface kinematic modes and gust excitation.  The Linearized FUN3D can generate an accurate unsteady aerodynamic solution in the small perturbation sense about a nonlinear steady flow condition.  It also can avoid the moving mesh problem associated with applying the exact N-S boundary condition which requires additional computational resources, and becomes very complex in dealing with the discontinuous displacement in mode shapes such as the control surface modes for which generating a computational mesh could be a very tedious effort.  

In order to enable the Linearized FUN3D to perform frequency-domain open-loop and closed-loop aeroelastic analysis and to generate a plant model in terms of state space equations, several modules in ZAERO, ZONA's flagship commercial software for aeroelastic, ASE, and gust analysis, will be incorporated into the Linearized FUN3D.  One can directly import such a plant model into MATLAB to design a flutter suppression and Gust Loads Alleviation (GLA) control system using the modern control design schemes available in MATLAB. 

The accurate flow field prediction of the wing pressures when a spoiler is deployed is currently beyond the capabilities of the existing aeroservoelastic codes.  The wind tunnel measured unsteady pressures on the Benchmark Active Controls Technology wing will be selected to validate the proposed Linearized FUN3D for unsteady aerodynamic prediction due to spoiler oscillations.
The Light Microscopy Module (LMM), developed and managed by NASA Glenn Research Center (GRC), is producing fascinating results. LMM will yield even more astonishing results with the addition of enhancing subsystems. Techshot is developing one such subsystem, the LMM-Dynamic Stage (LMM-DS), which will satisfy a host of new experiments. However, GRC has many more researchers awaiting enhancing subsystems for conducting experiments that could lead to new materials with significant commercial potential. Capitalizing on Techshot's rapid progress with the LMM-DS, its vast array of mixing and separations technologies, and its experience with microfluidic systems, Techshot proposes development of a Finite Internal Temperature Slide (FITS)&amp;#151; a hollow microscope slide capable of taking temperature measurements of a sample along the length of a slide without significant optical interference. Additionally this technology will apply heating to the sample by passing a current through the resistive path used for temperature measurement. This allows for more accurate, varied and controlled temperature gradients to be applied across a sample volume while maintaining optical clarity. FITS is a direct result of a need expressed by current NASA funded Principal Investigators  who intend to use the LMM for experiments in which temperature, and/or temperature gradients, must be precisely controlled.
The objective of this proposal is to integrate three unique energy harvesting technologies utilizing our existing research strengths that will be of interest and utility to NASA applications and environmental conditions. By developing multiple technologies, NASA will be able to harvest energy from multiple waste energy sources, namely environmental vibrations, thermal energy, and solar flux. These devices were initially developed and demonstrated separately, but will be enhanced, matured, and integrated during Phase II. The prototype resulting from this effort will be capable of harvesting energy in a variety of environments which support NASA's broad mission.
The objective of the proposed research and development effort is to demonstrate the feasibility of an innovative approach to high-performance hybrid propulsion for upper-stages.  The missions for these propulsion systems include launching small- and nano-satellites and conducting hypersonic flight test operations.  The focus of the research effort will be on achieving high specific impulse by means of an innovative approach to nozzle design. The technology will be experimentally demonstrated in a series of hot-fire tests during the proposed research program.
NanoSonic proposes to design and develop light-weight, low-modulus, and durable Metal Rubber sensors for aeroelastic analysis of inflatable/flexible entry, descent, and landing (EDL) systems, which would in effect increase the systems aerodynamic stability by contributing to optimize its design.  More specifically, a network of small Metal Rubber strain sensors would provide a non-invasive mechanism to monitor loading of the inflatable deceleration and landing systems.  The in-situ Metal Rubber strain sensors would be utilized to monitor drag and instability of the system at varying Mach flow regimes by analyzing dynamic structure forces and also billowing effects (or similar shape-change / inflation effects) of the inflatable system as it goes through EDL operations.  The novel Metal Rubber sensors have proven the ability to monitor aerodynamic events, particularly shear and normal forces, based on their response to applied strain. These previous sensor technological advancements will be modified to develop the proposed sensor system for monitoring dynamic loading of the inflatable structure.  Lightweight Metal Rubber sensor appliques can be attached onto the inflatable base material or integrated in/under the system coating matrix for in-situ non-invasive monitoring.
CRG has recently developed a new class of shape memory polymers (SMP) that are electrically activated, as opposed to the more mature thermally activated SMPs. Electrically activated shape memory polymers (EASMP) open a new design space of unexplored functionality beyond what has been considered for thermally activated materials. This project will combine the advantages of EASMP with the design of state-of-the-art gearbox isolators and interior panels to provide the ability to tune these components for specific operational frequencies. With the use of EASMP integrated components, by semi-actively altering the interior panels or gearbox isolators' frequency response, it will be possible to better target and control particularly irritating tones related to the aircraft's flight mode. CRG proposes to advance EASMP maturity which is applicable across many other application areas and has the benefit of alternative stimuli boasting ultra-low power requirements and more potential for faster switching times. This material will be refined and further developed to meet the operational performance requirements for the rotorcraft isolator application.
Analytical Services &amp; Materials, Inc. (AS&amp;M) is proposing to develop and validate the procedures and modeling necessary to simulate, using computational fluid dynamics (CFD), an entire wind tunnel circuit.  The application of CFD in wind tunnel circuit analysis is in its infancy and its use would allow for the design of better facilities and the development of better modifications of existing facilities to improve their efficiency and expand their capability.  A better understanding of the facility flow characteristics obtained by the simulation would improve wall correction methodology and data accuracy from the facility.  The proposed Phase I program will validate the methods against calibration data from the NASA Langley 14 x 22-ft Low-Speed Tunnel.
Development of energy storage capable of operational temperatures of 380:C and 486&lt;SUP&gt;o&lt;/SUP&gt;C with a specific capacity 200 Wh/kg for use as a power source on the Venusian surface and for planetary probes in similar high temperature atmospheres and where ambient pressures of 90 atmospheres are to be expected.  This proposal provides for further research and development of the Li(Al)/CoS2 high temperature energy storage chemistry to develop high temperature space energy storage, which will enable the in situ exploration of the atmosphere of Venus and deep atmospheres of Jupiter or Saturn for future NASA missions. This energy storage will provide power for thermal control systems, high temperature electronics and sensors, and high temperature motors and actuators.
The approach has a parallel path of evaluation of low melting point electrolyte for 380:C operation and optimization of the 486:C Venus energy storage chemistry. The final task is battery level characterization at various temperatures and discharge rates, with implementation of the previously completed design of a robust battery/cell container and ceramic to metal seals. The development includes the delivery of a prototype battery to JPL for testing.
The purpose of this SBIR program is to adapt NanoSonic's HybridSil&amp;#174; nanocomposites and combine high erosion resistance, low ice adhesion, and passive anti-icing functionality with Metal Rubber sensor technology to enable in-flight icing measurement and mitigation for next generation aircraft.  

During Phase I, NanoSonic successfully demonstrated novel sensor design concepts coupled with HybridSil&amp;#174; low ice adhesion passive anti-icing nanocomposite coatings.  NanoSonic realized outstanding passive icing protection through icing wind tunnel testing, completely preventing ice formation in select conditions and with excellent ice shedding measured to -20&amp;#176;F.  Low ice adhesion with outstanding erosion resistance was realized, retaining low ice adhesion properties following 500 mph rain erosion exposure.  NanoSonic demonstrated exceptional icing event sensing capabilities in the icing wind tunnel, responding in near real time to environmental condition changes with negligible drift or hysteresis in test conditions spanning -4 to 26&amp;#176;F, 100 to 200mph windspeeds.   Sensitivity to observe ice accretion onset and build, with distributed sensing of thickness and airspeed, was demonstrated in near real time.

NanoSonic will build on these results to optimize, qualify and transition the technology through extensive development, testing, and prime partner interaction during Phase II.
Sustainable Innovations is developing a technology for efficient separation and compression of hydrogen gas. The electrochemical hydrogen separator and compressor can actively remove hydrogen from a mixture and compress it to high pressure for storage or use. In applications where helium is used as a purge gas prior to the use of liquid hydrogen or use of cold hydrogen from cryogenic storage boil-off, the compressor system is suitable for separation of the hydrogen from the helium in the resulting mixed stream. This technology allows a significant portion of either gas to be recycled and conserved.  In applications requiring recycling of helium where abundant hydrogen is present, it is practical to utilize the energy content of a portion of the hydrogen to power the electrochemical separation of hydrogen from the helium. This novel application leverages hydrogen that was destined for flaring and oxidizes it electrochemically to power separation of hydrogen from helium, thus allowing recovery of the helium and delivering net power.
High power electric propulsion systems have the potential to revolutionize space propulsion due to their extremely high performance.  This can result in significant propellant savings on space vehicles, allowing the overall mass to shrink for launch on a less expensive vehicle or to allow the space vehicle to carry more payload at the same weight.  Many of the electrical propulsion systems operate in pulse mode, pulsing hundreds or even thousands of times per second.  Creating reliable valves that can operate in pulse mode for extremely long life and at low power are critical in these applications.
WASK Engineering will develop a normally closed, piezo electric operated valve for application to pulsing electrical thrusters.  The benefits of such a valve includes 1) demonstrated ability to operate at frequencies from 0 Hz to 4,000 Hz, 2) ability to throttle continuously from 0-100&#37; open, 3) extremely fast response, 4) low power usage, 5) infinitely variable valve operating waveforms, sine wave, square wave, saw tooth, custom wave form, etc., 6) no EMI generated, 7) very small size provides options when locating valve, 8) demonstrated ability to operate at pressures exceeding 1,000 psi, and 9) very low part count for reliability.
A transducer element that is hearty enough for a Mars lander mission needs to be developed so that a six-axis force and torque transducer is possible.

The technical objectives are:
1. A transducer element capable of surviving temperatures from -135?C to +125?C.
2. The transducer element in objective 1 with temperature compensation to minimize span and offset drift from -80?C to +70?C.
3. The transducer element in objective 2 constructed so that it will sense properly in an atmospheric vacuum of 1E-5 torr.
4. The transducer element in objective 3 made of low-outgassing materials that are compatible with an interplanetary sample-collecting mission.
5. The transducer element in objective 4 instrumented with redundant sets of strain gages.

In order to achieve the objectives, ATI Industrial Automation has divided the project into these tasks:
* Six degree of freedom transducer design and fabrication,
* Load fixture design and fabrication,
* Instrumentation and temperature compensation of transducers
  - using semiconductor strain gages and
  - using metal-foil strain gages,
* Calibration of instrumented beams and redundant instrumentation,
* Performance characterization of both transducer instrumentation types at temperature and vacuum.
Launch vehicles experience extreme acoustic loads during liftoff driven by the interaction of rocket plumes and plume-generated acoustic waves with ground structures. Currently employed predictive capabilities are too dissipative to accurately resolve the propagation of waves throughout the launch environment. Higher fidelity non-dissipative analysis tools are critically needed to design mitigation measures (such as water deluge) and launch pad geometry for current and future NASA and commercial launch vehicles. This project will develop and deliver breakthrough technologies to drastically improve acoustic loads predictions. An innovative hybrid CFD and Computational Aeroacoustics (CFD/CAA) method will be developed where established RANS/LES modeling will be used for predicting the acoustic generation physics, and a high-order accurate unstructured discontinuous Galerkin (DG) method will be employed to propagate acoustic waves across large distances using ideally suited high-order accurate schemes. This new paradigm enables: (1) Improved fidelity over linear methods; (2) Greatly reduced numerical dissipation and dispersion; and (3) Improved acoustics modeling for attenuation, diffraction, and reflection from complex geometry. A proof-of-concept was developed and successfully demonstrated during Phase I for benchmark applications as well as SLS prototype model launch environments. Phase II will deliver production CFD/CAA predictive capabilities with 4th-order spatial and temporal accuracy for near lossless acoustic propagation throughout the launch environment, which will provide NASA engineers with more than a two-fold increase in the range of resolvable frequencies over current methods.
The proposed work investigates an approach that would allow an annular ion engine geometry to achieve ion beam currents approaching the Child-Langmuir limit.  In this respect, the annular engine, whose design inherently allows for significant increases in perveance by resolving the span-to-gap problem, can achieve the projected high current densities necessary for high thrust, high power applications. The case for high power gridded ion thrusters is compelling if not only for risk reduction in contrast to lower TRL Hall thruster variants such as the nested channel systems. This point cannot be over emphasized as there is now significant effort and resources applied to Hall engine development.  Yet there still remains some uncertainty as to how high power variants or magnetically insulated variants will actually perform in space. Interpretation of high power Hall engine operation in ground test facilities is also not completely well understood.  This is in contrast with gridded ion technology whose facility corrections are well understood.  The current investment in high power gridded ion thruster technology is minimal.  This effort seeks to address this gap in technology development and in the process continue the advancement of a credible risk reducing technology for high power mission applications.
Very extensive R&amp;D efforts over the past several decades resulted in several classes of high temperature composites offering potential for future hypersonic vehicles hot structures.  Of particular interest is a hybrid carbon/SiC matrix composite utilizing carbon fiber.  This class of composite, which utilizes Phenolic prepreg to form the initial composite structure, lends itself to the fabrication of large very complex structures.  Typically, these composites are densified via PIP processing.  However, there are deficiencies in this material system.  The nature of PIP processing results in an appreciable amount of open porosity, requiring a CVD SiC external coating for oxidation protection.  The application of CVD SiC to large structures is quite limited due to cost factors.   Also, since the composites are fabricated using 2D fabric, the transverse mechanical properties are typically low.   This proposal offers a highly innovative approach to alleviate the above mentioned shortcomings.  First, it utilizes nanotechnology at the composite molding stage, enabling enhanced in plane and transverse mechanical properties.  Secondly, it offers a highly unique, non CVD external coating technology.  It enables the fabrication of large, complex parts with greatly reduced manufacturing cost when compared with conventional CVD SiC.
High peak power short pulsed lasers have been considered to be an enabling technology to build high power transmitters for future deep space high rate space communications. However, to achieve a high peak power at a high repetition rate over 100 MHz and with a short pulse width and &gt;25&#37; wall plug efficiency still remains an issue unsolved. PolarOnyx proposes a novel approach targeting to make 10 MHz to over 100 MHz high repetition rate high power fiber laser at 1550 nm and resolve the issues of modulation induced chirp, pulse distortion and nonlinear effects by using COTS components and employing our proprietary technologies in specialty fibers, spectral shaping and pulse shaping techniques. Space qualification will also be addressed in laying out the pathway towards space deployment. A tabletop demonstration will be carried out at the end of Phase 1. A prototype will be delivered at the end of Phase II.
As the power density of advanced engines increases, the need for new materials that are capable of higher operating temperatures, such as ceramic matrix composites (CMCs), is critical for turbine hot-section static and rotating components. Such advanced materials have demonstrated the promise to significantly increase the engine temperature capability relative to conventional super alloy metallic blades. They also show the potential to enable longer life, reduced emissions, growth margin, reduced weight and increased performance relative to super alloy blade materials.

MR&amp;D is proposed a program focused on improving the impact resistance of CMCs using 3D woven reinforcement. This approach was shown in the Phase I program to hold promise for increased performance is of specific interest to Rolls Royce as a candidate material for vanes and blades in their turbine engines. MR&amp;D will expand the capability of its analysis tool which was developed during the Phase I program by incorporating failure criteria tailored for 3D woven preforms as well as executing analyses to predict the exact locations of the fiber tows after weaving. 

Along with impact testing, an expansive testing program to characterize multiple 3D fiber architectures will be executed. The impact testing and associated non-destructive evaluation will be conducted at the University of Akron using state-of-the-art techniques to record the damage caused by the projectile in real time as well as detailed post-test evaluation. Material characterization tests will be conducted at Southern Research Institute and The Ohio State University. All of the data resulting from this extensive test program will enhance the analytical tools accuracy and utility.
A compact, lightweight, and low power diode laser sensor will be developed for atmospheric methane detection on small unmanned aerial vehicles (UAVs). The physical specifications of this sensor will be considerably smaller than current NASA laser sensors. The smaller sensor specifications will enable use of carrier UAVs that are similiar in size to a large model aircraft. Using smaller UAVs for measurements will result in large cost savings. The proposed sensor will use an open path optical system that will provide superior spatial resolution in the measurements.
Innovative Imaging and Research and the University of Houston Clear Lake have teamed to develop a widely extensible, affordable, energy efficient, smart lighting device known as Lambda-Net.  Smart building technologies, such as Lambda-Net, are becoming critical to energy savings and sustainability for terrestrial applications and space-based habitats.  Our device incorporates a smart-mobile device or other comparable sized integrated computing/sensing device into each LED fixture. Smart-mobile devices are ideally suited to perform energy saving lighting control as they contain inexpensive, mass produced, highly integrated imaging, computing and communication technologies. The low cost digital cameras within these packages become highly capable imaging photosensors using calibration techniques developed for NASA satellites and the commercial remote sensing industry. Novel algorithms utilize lighting information measured by the photosensors to individually tailor the intensity and spectral content of the light generated from each LED fixture within the lighting system to reduce energy usage, increase lighting efficacy and improve circadian rhythm influenced activities such as sleeping and concentration.  Advanced spatially distributed occupancy sensing and lighting control further reduces energy usage.  Integrating sensing and computing into each light fixture also provides the infrastructure to create a robust sensor network. Network communication is achieved through Wi-Fi, Bluetooth and other communication means, such as the power lines that provide electricity to each fixture. This resulting sensor network enables a wide range of terrestrial and space-based applications including monitoring: building/habitat temperature, humidity and air quality; occupant health and safety; building/habitat space utilization and astronaut activity including deep space adaptation in addition to providing high quality spatially selectable, spectrally programmable illumination.
Photodetectors and focal plane arrays (FPAs) covering the middle-wave and longwave infrared (MWIR/LWIR) are of great importance in numerous NASA applications, including earth remote sensing for carbon-based trace gases, Lidar mapping for earth resource locating, and environment and atmosphere monitoring. Existing MWIR/LWIR photodetectors have a low operating temperature of below 77K. The requirement for cryogenic cooling systems adds cost, weight and reliability issues, making it unsuitable for satellite remote sensing applications. This STTR project aims to develop a new plasmonic photonic antenna coupled MWIR/LWIR photodetector and FPA with significantly enhanced performance and a high operating temperature. In Phase I, we developed a preliminary plasmonic photonic antenna enhanced MWIR/LWIR photodetector and demonstrated significant enhancement in photodetectivity and operating temperature. Antenna directivity is also tested and agrees with the simulation. The phase I results not only demonstrated the feasibility of achieving high performance MWIR/LWIR photodetector using the proposed innovation, but also show its promising potentials for high operating temperature FPA development. Motivated by the successful feasibility demonstration and the promising potentials, in this STTR Phase II project, we will develop a prototype of the plasmonic photonic antenna enhanced MWIR/LWIR FPA with a high operating temperature and demonstrate its earth remote sensing capability.
The goal of the proposed effort is to use selective laser melting (SLM, an additive manufacturing technique) to manufacture a hot fire-capable, water-cooled spool piece that features an advanced regenerative cooling technique that combines high heat flux performance with low pressure drop. SLM enables us to "print" the spool piece in days, despite the complexity of the regenerative liner's inherent flow passage complexity. This reduction in manufacturing lead time, combined with the fact that SLM manufacturing costs are driven in large part by the amount of raw powder used during fabrication, results in a substantial cost reduction for future regeneratively-cooled rocket engines. Additionally, the proposed advanced regenerative cooling approach features a heat-pickup efficiency that is at least two orders of magnitude higher than traditional milled channel liners and/or brazed tube bundle chambers.

As a result of our Phase I activity and confidence in our commercialization path, we will be making a capital investment to stand up an SLM manufacturing capability in house.  We plan to augment that investment with an internally-funded trade study that we will use to derive main combustion chamber performance requirements for a future expander cycle engine.  Those requirements will feed into Phase II design requirements and, ultimately, to supporting our commercialization opportunity presented by the Affordable Upper Stage Engine Program.
When ice accretes on a wing or other aerodynamic surface, it can produce extremely complex shapes.  These are comprised of well-known shapes such as horns and feathers but also include other shapes such as the scallops that are associated with swept wing icing. The development of the larger ice shapes is generally believed to be influenced or built up from smaller scale surface structures such as roughness elements which can grow into the precursors of feathers or scallops seen on larger swept wing ice accretions. Feathers and scallops are often comprised of complex interlocking geometries that can contain a large number of voids. Hence it is important to characterize the geometries of these ice shapes, not only to ensure an adequate representation of the geometry for subsequent aerodynamic effects studies but also to provide data to validate icing codes, understand the basic physics involved with the ice accretion, and provide a basis for modeling the ice accretion. To address the above issue, we propose to use an X-ray computed tomography (CT) imaging method to demonstrate that X-ray CT scanning can be used to measure 3D ice features of the form seen in aircraft ice accretions. We also propose to conduct a preliminary trade/design analysis to establish directions for a more detailed Phase II study that would address specific recommendations to integrate X-ray CT imaging with icing wind tunnels which can be used at NASA Glenn and commercial aerospace companies. It is anticipated that the proposed imaging method could provide a radically new way to visualize and characterize extremely complex 3D ice shapes.
Terminal Velocity Aerospace, LLC (TVA) proposes to improve utilization of the International Space Station (ISS) by providing a system for on-demand return of experiment samples to Earth. TVA is presently developing a small reentry device (RED) capable of returning small payloads from space, with initial prototype development funded by a separate contract. The device, named RED-4U, is sized to accommodate a payload mass and volume equivalent to four CubeSats, commonly referred to as units or "U." The payload accommodations and concept of operations for RED-4U are currently generically defined, but are readily suitable to the ISS small payload return mission. In the proposed Phase I R&amp;D effort, TVA proposes to (1) design, fabricate, and demonstrate RED-4U payload accommodations specifically for high-frequency sample return from ISS; and (2) detail the concept of operations for RED-4U use on ISS.
Thermal Stir Welding (TSW) provides advancement over the more conventional Friction Stir Welding (C-FSW) process because it separates the primary processes variables thereby allowing independent control of metal stirring and forging from the stir zone temperature. However, the feedback for precise control of the stir zone temperature, and hence the process parameters to sustain that temperature within a narrow range, does not currently exist on the TSW machine at the NASA Marshall Space Flight Center (MSFC). At present, the current state of the art for the selection of process parameters for both TSWing and C-FSWing parameters is highly empirical and by nature is based on phenomenological knowledge. In response to this need, Keystone is proposing this Phase II STTR project to demonstrate the feasibility of closed-loop control of the TSW process and to enable the establishment of a analytically derived processing map to accelerate process understanding and selection of parameters for a given material and pin tool design. The close-loop control system will enable sustainment of a steady-state temperature at the stir rod as a function of spindle RPM and the travel velocity for a given z-axis loading and stir rod design. Use of this theoretically derived processing map will provide guidance in the optimization of the process parameter domain for solid-state welding of a given material. This capability will in turn enable rapid process qualification of the TSW process and components produced by the process.
ZeCoat Corporation will develop and demonstrate a set of revolutionary coating processes for making broadband reflective coatings suitable for very large mirrors (4+ meters). Decades of research and flight missions (Hubble, GALAX and FUSE) have utilized metal fluorides such as, MgF2 and LiF, applied to Al to achieve FUVOIR coating requirements. While metal fluoride-protected Al remains the best option for meeting broadband reflectance requirements (90-nm to 2500-nm), ZeCoat offers a means to build upon the best known and proven coating recipe (the GSFC 3-step process) by: 1) utilizing ZeCoat's unique precision motion-controlled deposition system to uniformly apply a 5-nm layer (a requirement of the GSFC recipe) of coating material to a large coating area, 2) protecting mirror assemblies from damaging high temperatures by heating only the mirror surface using radiant heat (the GSFC process requires a 220C metal-fluoride deposition temperature), 3) using an FUV reflectometer (120-nm to 180-nm) integrated into the coating chamber to optimize the coating process for FUV reflectance and 4) investigating the feasibility of using a layer of Sn to protect LiF from degradation due to atmospheric moisture and organic contamination during ground storage and  re-evaporate the Sn once the observatory is placed in-orbit.
A light-weight, user-friendly, algorithmically or remotely controlled microscope, not purchased from a microscope company, coupled to fluid sample processing and sample changing systems is proposed. It is an easy-access light microscope consisting of a novel illuminator-condenser with no moving parts, a sample-processing remotely controlled translating stage using hollow slides, a high-definition color video camera, including multiparameter image processing and analysis. This system will be especially useful when the U. S. Light Microscopy Module on ISS is out of service in 2017-2018.  In phase I research Techshot will produce a functioning laboratory prototype of this system by meeting the following technical objectives (1) Determine the detailed requirements of identified ISS microscopy users and implement these requirements in a design, (2) Build a laboratory prototype of the microscopy system installed in an EXPRESS locker insert, and (3) Operate the laboratory prototype for at least three ISS user experimenters.  The tested prototype will serve as the basis for Phase II research, in which a version designed for space flight will be built and tested.
Reliable monitoring of the microcrack formation in the complex composite structure components in NASA spacecraft and launch vehicles is critical for vehicle operations. Early diagnosing and reporting vehicle capability has tremendous impact on mission readiness, safety, and life cycle cost. Microcrack formation in complex composite structure components can be challenging from a monitoring and evaluation point of view by traditional non-destructive evaluation methods, especially in the early stage. FBS, Inc proposes to develop a nonlinear guided wave circular array system for the SHM of microcrack formation in complex composite structure components of spacecraft and launch vehicles. The innovation here is the combination of guided wave circular array with nonlinear characteristics for microcrack SHM. Guided wave circular array has the capability of inspecting large areas with a small number of sensors and minimum wire connections. Magnetostrictive sensors will be used to build the array as they are flexible, sustainable to environmental temperature changes, and inexpensive. Nonlinear higher order harmonic guided waves will be emitted when fundamental guided waves impinge onto a microcrack. The nonlinear receiver will be built at the center of the circular array. The transition between fundamental to higher order nonlinear guided waves can be used to quantify the microcrack formation in complex composite structures.
The National Research Council (NRC) has identified the need for motors and actuators that can operate in extreme temperature environments as a technical gap to exploring deeper into our solar systems. Bear Technologies has been exploring motor design for more than 5 years. A number of designs are blended to create the basis of the proposed innovation. The research focuses on a fundamentally different motor design that explores the use of flexures to amplify the forces created by the electro-magnets.   In this way, the design can be much simplified, eliminates wear, free play and the need for lubricants.   Bear will focus on investigating low stress flexure designs and relatively high force electro-magnetic drives that can produce the forces needed for a high torque motor.   If proven this flexure component will be an enabling technology for the extreme environment high torque motor.
In this project, Ultramet will develop a three-dimensional (3D) laser-directed chemical vapor deposition (CVD) additive manufacturing system to build free-form refractory metal structures for liquid rocket propulsion systems. By combining Ultramet's decades of experience in refractory metal deposition by CVD with the computer control of directed laser energy, nearly unlimited expression of part shape and metal alloy composition can be realized for next-generation rocket propulsion component fabrication. 3D additive manufacturing is currently revolutionizing many industries by offering unconstrained complex build geometries, reduced cost, reduced lead time, and reduced material usage compared with conventional manufacturing techniques. By developing laser CVD technology for refractory metals, Ultramet will bring these inherent benefits to a class of materials that are notoriously difficult to form and thus are expensive to implement. By depositing successive layers of metal directly from reactive parent gases, the system will be able to build components from rhenium, tantalum, niobium, tungsten, and their alloys with complex internal features and assembly part count reductions. In this project, Ultramet will design and build the required laser-directed CVD reactor, achieve layered deposition, and map the process conditions for the formation of rhenium metal structures.
An optical communications receiver requires efficient and high-rate photon-counting capability so that the information from every photon, received at the aperture, is processed. This is particularly true in space platforms, where the information contained in every additional photon detected directly translates into lower system size, weight, and power (SWAP). To address this need, a near-infrared (NIR) high gain, low excess noise avalanche photodiode (APD) array will be developed for photon counting flight receivers. 

The proposed APD array technology is capable of a single photon detection efficiency (SPDE) greater than 50&#37; at 100's Mhz count rate. It will be shown possible to discriminate photo-generated events from dark-initiated events, so that when the APD is configured with a low noise readout circuit, with sufficient bandwidth detection circuits, that low false alarm rates (FARs) can be achieved.
We propose to design, build and test a multi-color (red, green, blue) particle optical extinction monitor suitable for use in either land or airborne applications.  The monitor will also contain a fourth measurement cell to allow for real-time subtraction of interferences caused by gas phase interferents such as nitrogen dioxide.  The instrument will fit into a rack-mountable box that less than 18" high (10U).  Its time response will be less than 2 seconds and its precision better than 1 inverse megameter in 1 second. The accuracy of the measurements will be within ?5&#37; of the values obtained using measurements of polystyrene latex spheres.
An ideal NDE data acquisition and analysis tool would be a versatile and precise device capable of providing support for a large number of inspections using numerous inspection methods such as JENTEK's Meandering Winding Magnetometer (MWM) inspection, Standard Eddy Current Testing (ET), Ultrasonic Testing (UT), and other digitized NDT methodologies. Such a "super" instrument could address NASA's need for improved nondestructive evaluation (NDE) of complex built up structural components for space flight hardware, as well as provide new capability for other challenging material constructs. A leap in capability will be demonstrated that is suitable for applications including multi-layered coatings, composites, thin metal layers, thermal protection systems, tiles, felts, micrometeoroid shielding, composite overwrapped pressure vessels, and difficult to inspect locations.
For this proposal a "super" instrument is defined as an instrument that has (1) many parallel channels with high data rate capabilities, that (2) each perform at the highest signal to noise and bandwidth performance made possible by the latest generation digital and analog electronics components, and (3) digital structured waveform generation and deconvolution capability. This proposed Phase I SBIR will demonstrate the capability of JENTEK's new 8200 instrument for two selected NASA needs; one for rapid imaging of complex built up structures, and a second for an inspection that cannot be addressed by conventional NDE methods. This Phase I will also lay the foundation for modifications in Phase II that address specific identified technology gaps needed to provide a leap in NDE capabilities, and will demonstrate an integrated prototype to TRL 5 that specifically addresses the need for "astronaut crews to make important assessments quickly" while also reducing their inspection related burdens. The final system will not only support JENTEK MWM arrays, but also other NDE methods such as UT.
Fibertek proposes to develop laser technology intended to meet NASA's need for innovative lidar technologies for atmospheric measurements of methane.  NASA and the 2007 NRC Earth Science Decadal Study have identified methane lidar as a key technology needed to address global change research.  Under this SBIR opportunity, we propose to develop an injection-seeded Erbium-doped YAG (Er:YAG) laser transmitter for methane lidar that can be used to increase performance of an existing GSFC methane lidar SNR by 20-40 times and enable future International Space Station (ISS) and satellite platform missions.    In addition to targeting space flight applications, the technology could also be used for future global hawk (GH) mission.   Key innovations of this technology include:
* Average output power &gt;5W at 10kHz pulse repetition rates
* Direct generation of near-transform-limited single-frequency output at a 1.65?m methane absorption wavelength with appropriate linestrength for high-altitude aircraft or spaceflight measurements.
* High reliability and compact size, weight and power (SWaP)
* Potential for high efficiency (4-8&#37; wall plug efficiency)
Prime Photonics proposes design and development of a surface acoustic wave (SAW) based temperature gradient sensor for instrumentation of thermal protection systems (TPS).  This device will utilize a passive, wireless interrogation approach to produce a robust measurement platform compatible with high temperature environments.
There is an extraordinary need for a universal biomedical analyzer that has broadly flexible capabilities for cell studies, small animal experiments, and crew member health.  The goal of our rHEALTH X device is to create a single palm-sized device with tripartite capabilities:  non-invasive measurements, cell cytometry analysis, and multiplexed nanostrip tests.  Currently, there is no single device that is able to provide comprehensive non-invasive measurements, let alone combine it with the rHEALTH's significant wet laboratory analytical capabilities.  We have developed the existing rHEALTH technology in collaboration with NASA and here, in this Phase I proposal, we intend to further push the envelope and add a fully non-invasive module.  The module will include measurements of heart rate, SpO2, body temperature, respiratory rate, and EKG.  The module will be housed in the back of the rHEALTH X and will be fully detachable for wireless/wearable applications.  At the end of Phase I, we will develop a TRL 4 non-invasive module.  For Phase II, we will integrate the module with our existing rHEALTH technology into the rHEALTH X.  We will bring it to TRL 7, so that it can be flight-certified and flown on the International Space Station (ISS) in a timely manner.
The Mars ascent vehicle (MAV) is required to endure a long space transit time, high-g loading during planetary entry, and high launch loads, all at low temperatures of approximately -40 Deg C.   Additionally, low-temperature motors like the MAV are often tested at room temperature, since testing at temperatures of -40 Deg C or lower is both difficult and expensive.  Since testing at higher temperatures results in higher burn rates for typical propellants, and thus higher working pressures, ambient tests result in a motor case that is heavier than required for a low temperature mission, because ambient testing results in a higher maximum expected operating pressure.  Our proposed technology alleviates that problem by using a plateau-burning composite propellant that will substantially lessen the burn rate sensitivity to temperature.  As such, the MAV operating pressure in ambient conditions will more closely resemble those on the Mars surface, allowing for a lighter motor case resulting in reduced weight, smaller volume and greater propellant mass fractions.  Additionally, our plateau burning formulation will include a low temperature binder with a high density fuel additive, in order to alleviate the loading stresses at low temperatures and further increase the motor density-Isp.  This may allow us to eliminate the need for the MAV launch erection equipment currently baselined for the MSR mission.
This SBIR Phase I effort will demonstrate the feasibility of developing a tunable, high-power, narrowband seed laser source integrated with a broadband, waveguide-based second harmonic generation (SHG) module to allow in situ alignment, component testing and calibration across the tuning range of fiber-based lidar systems for measuring atmospheric oxygen concentrations. The lidar is being developed as part of a dual-wavelength remote sensing system for high precision CO2 measurements.  Active laser-based spectroscopic remote sensing can map changes in CO2 concentration over the entire globe.  However, the measurement of CO2 concentration varies depending on properties such as humidity, temperature, and pressure.  To remove these variables, measurement of a stable, well-mixed gas such as oxygen is required as well.  Generation of a broadly tunable SHG source with integrated laser for downstream seeding will further this approach.
Systems &amp; Processes Engineering Corporation (SPEC) and Texas A&amp;M University (TAMU) propose a space hardened, compact, low power, high definition six-dimension (HD6D) LADAR for remote sensing. This modular situation awareness HD6D LADAR can be configured by platform and mission to support operational ranges from 8km to 30 km, while meeting CubeSat form factors of .5U to 3U, respectively. The .5U CubeSat configuration has a 3.2Mpps HD6D Micro-LIDAR with integrated high resolution, 5 Mpixel, 30fps, RGB camera and can achieve a 4km effective range in single pulse mode or 8km range in integrated image mode (for 0.1 reflectivity targets). The long range Gen IV HD6D configuration can be used for descent imaging.  It has a 12.8Gig pixels per second acquisition rate, 100x faster than competitors, and a clear air range of 20km.  Current Gen IV LIDARs have a 30 degree field of view, using pixel sizes of 0.7mr or 0.15mr.  Built around the space qualified Vertex-5QV FPGA, using pipeline processing to calculate the stabilized x,y,z amplitude point cloud, merges the point cloud with the RGB image, and produces HD6D binned images (x,y,z,R,G,B).  The LIDARs have range accuracy of 3mm at close range, 35mm at acquisition ranges.
In previous work for NASA, Ultramet and ARA Ablatives Laboratory developed and demonstrated advanced foam-reinforced carbon/phenolic ablators that offer substantially increased performance under high heat flux conditions and reduced weight relative to conventional ablators. The two-piece structure consisted of an ablative-filled foam front surface backed by Ultramet's previously established and highly insulating aerogel-filled foam. Arcjet testing was performed at NASA Ames Research Center to heat flux levels exceeding 1000 W/cm2, with the results showing a significantly reduced ablation rate compared to conventional chopped fiber ablators, and ablation behavior comparable to FM5055 at just one-third the density. It is apparent that the foam helps retain the char layer by physical reinforcement and/or that the network of interconnected passages allows pyrolysis gases to escape with less disruption of the char layer. In Phase I, Ultramet teamed with ARA Ablatives for ablative infiltration of Ultramet foams and Materials Research and Design for ablation analysis, to continue optimization of foam-reinforced ablatives by focusing on two primary areas. The ablator formulation infiltrated into the foam was successfully modified to increase heat flux capability consistent with NASA Earth return requirements (1500-2500 W/cm2 or higher). The density can be varied as needed to meet heat flux requirements while minimizing weight. In addition, a single-piece foam structure was demonstrated, rather than separate ablative- and aerogel-filled foam sections. In Phase II, the lightweight hybrid ablator will be optimized for a specific NASA mission, material and structure requirements will be predicted through modeling, and performance will be demonstrated through high heat flux testing at NASA ARC and the Air Force LHMEL-II facility. Scaleup potential will be demonstrated through fabrication of a heat shield module suitable for construction of large modular heat shields.
Mars sample return ascent vehicles require a velocity change exceeding 4 km/s within minutes of launch and higher propellant mass fractions than are offered by current pressure-fed satellite propulsion systems. Pump-fed systems are potentially low-mass, but a suitable high-pressure nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) bipropellant rocket engine remains to be developed. The state of the art in NTO/MMH combustion chambers is iridium-lined rhenium (Ir/Re) manufactured by Ultramet and used by Aerojet in its HiPAT engine. In previous and current work, Ultramet has demonstrated the potential for fabrication of refractory metal and ceramic matrix composite (CMC)-lined carbon/carbon (C/C) components, thereby combining the benefits of the refractory liner with the substantially reduced weight and cost of C/C. The shortfall of using C/C as the lightweight structure is the disparity in thermal expansion, causing highly stressed components. In this project, Ultramet will demonstrate a processing route to integrally bond liners of a zirconium carbide (ZrC) CMC and of rhenium to C/C that will be applied to the fabrication of a Mars sample return ascent engine combustion chamber. Phase II will culminate in the design and fabrication of a 1000-N, 500-psi refractory-lined C/C chamber that will be delivered to NASA. To facilitate testing within project funding resources, a 22-N 500-psi refractory-lined C/C chamber will also be designed, fabricated, and hot-fire tested at one of the major propulsion system integrators (Aerojet, Moog-ISP, or Northrop Grumman), all of which have expressed interest in teaming on the project.
Our approach to high-pressure carbon dioxide storage will directly address the challenges associated with storage of compressed carbon dioxide -  the need to reduce power consumption, mass and volume while limiting acoustic impact.  Successful implementation will reduce gas compressor power by over 50 &#37; and required maximum tank pressure by over 80 &#37; while maintaining storage tank footprint and total standard volume of gas.  This is accomplished through the use of our high gas capacity physisorptive support architecture employing tailored zeolite sorbents. Added benefits include facile regenerability, equal applicability to other gases including oxygen and nitrogen, improved thermal management to control heats of desorption and adiabatic cooling during filling and empyting cycles. In addition to the energy savings, we expect that more compact, efficient, and less intrusive compression devices can be utilized.  
This approach is based on a novel regenerable high capacity physisorptive media storage system that will adsorb CO2 from a compressor system and store it at a relatively lowered pressure. On demand, the CO2 can be desorbed at a constant rate and released.  For example, we can store an equivalent volumetric amount of CO2 at about 500 psi, compared to the current 3600 psi.  There is a potential for substantial weight savings as well &amp;#150; while we add the mass of sorbent and support, mass reductions from use of thinner wall tanks and smaller compressors are likely to be larger, specific savings will be addressed as part of the proposed task plan.
At the end of Phase I we will have demonstrated our approach in our in-house bench scale equipment, bringing the technology to TRL 3 with detailed performance information needed to go to TRL 4 in Phase II, including the delivery of suitable equipment to a NASA facility.
Newer vertical lift configurations consider speed as an important design parameter with forward speeds upwards of 230 Knots, which is well above the acceptable incompressible flow regime. In such high speed vertical lift configurations, even though the aircraft may be cruising at compressible Mach numbers, incompressible flow pockets can occur in the wake of the fuselage. Hence, in contrast to most helicopters currently in use, these configurations need to be analyzed across a wide range of speed regimes including incompressible, compressible and mixed regimes.

The present proposal offers to extend the design tool ``RotCFD'' to viscous all-speeds with mixed incompressible and compressible regions. In general, the algorithms used in CFD are designed for incompressible flow or compressible flow, depending upon the primary usage. RotCFD, being an Integrated Design Environment (IDE) for rotors, can be developed to seamlessly work in both regimes without additional input besides the operating speed from the design community. Additionally, this proposal offers to extend RotCFD to include grid generation with bodies in relative motion, such as tilting nacelles and wing tips, which happens in transitioning flight. 

The proposed extension of RotCFD for all-speed regimes and flows with mixed
regimes, if proven successful, will offer the vertical flight scientific community a moderate fidelity, robust and efficient design tool. With the added potential to simulate relative motion of components, the tool will provide an analysis capability for all operational regimes: hover, conversion and cruise.
The value of measuring sleep-wake cycles is significantly enhanced by measuring other physiological signals that depend on circadian rhythms (such as heart rate and temperature) and environmental conditions that are known zeitgebers, such as light exposure. As a result, a more complete picture of crewmember circadian rhythms and the environmental factors that entrain them will aid in determining adequate sleep levels and the countermeasures necessary to achieve them. In order to maximize safety, performance, and research value, crewmembers are in need of a device that unobtrusively measures sleep-wake cycles alongside environmental factors. This device must measure and communicate these signals while requiring very little crew overhead, a low energy budget, and a radically long battery life. 
Orbital Research Inc. (Cleveland, OH), with academic and commercial partners, proposes to design and prototype a Circadian Rhythm Measurement System (CRMS). Orbital envisions the CRMS to be a compact, light-weight unit worn on the upper part of the non-dominant arm. In contrast with more common wrist-worn devices, this positioning will provide additional battery space for energy storage and access to rich biological signals (heart rate and skin temperature). A consumer fitness device marketed by Orbital's commercial partner that makes use of upper-arm positioning has proven to be comfortable and inconspicuous to tasks involving the hands. The Orbital CRMS effort will focus on extremely energy-conscious design and minimally obtrusive user experience. The final product will measure sleep/wake cycles alongside heart rate, skin temperature, and light exposure without required intervention for 2 weeks or longer, transmit daily (or more frequent as needed) reports to an ISS computer automatically, and will provide feedback to the user upon request. Orbital will heavily leverage its existing technology and expertise to achieve these design goals.
Over the past decade, research into active combustion control has yielded impressive results in suppressing thermoacoustic instabilities and widening the operational range of gas-turbine combustors. Active Combustion Instability Control (ACIC) controls the combustion process such that the heat release profile is modulated to dampen the naturally occurring thermoacoustic instabilities. A major challenge to effective implementation of active combustion control is the availability of valves and actuators that provide adequate flow modulation control authority. The majority of the published work revolves around valves designed to modulate the main combustor flow. At present these valves are not designed to operate in a harsh environment and as such are required to be located outside the main flow path, reducing their control authority. To effectively meet the challenge, valves and sensors that are smaller, more responsive and robust must be developed. Ultimately the control valves are co-located with the fuel injection manifold. The trade-off for the harsh environment operation is the ability to maximize the flow modulation control authority. The objective of this research is to integrate the required control authority into an operational environment. This research continues the development of a light weight fast-acting fuel control valve for harsh environment operation. In the Phase 1 effort, the valve demonstrated the ability to modulate fluid flow at 1,000 Hz.  This demonstrated the valve will allow the precise time dependent fuel control required for lean-burn combustor operability. In this Phase II research a Prototype valve is designed, fabricated and flow tested using commercially-available driver circuitry to  demonstrate valve operation in harsh thermal environments.
Instruments employing X-ray, gamma ray and particle detection are utilized in different sectors from medicine to industry and from basic to applied science. The solid-state detector array with detection ASIC is the primary technology of space-based high-energy astronomy missions that are managed by NASA in partnership with the international community1,2. A readout integrated circuitry (ROIC) specifically designed for photon resolving X-ray detection has been developed by Black Forest Engineering on prior NASA SBIR funding3. The BFE322 ROIC, bump bonded to a CdZnTe (CZT) 16x32 detector array, demonstrated single photon sensitivity, accurate X-ray energy determination, X-ray event time stamping, and low power dissipation (&lt; 10 &amp;#956;W per pixel) at ambient temperature operation; this represents a significant advancement in detection capability. The proposed Phase I improves ROIC performance by using low 1/f noise 250 nm CMOS, in-pixel amplifier tuning to match detector capacitance and rad-hard-by-design (RHBD) to provide &gt;500 kRad radiation tolerance. The Phase I design will be a 32x32 pixel format with 600 ?m pixel pitch compatible with CZT and silicon detector arrays. The ROIC will be fabricated and hybridized to CZT on Phase II and demonstrated using a PocketQube or CubeSat mini-satellite test flight to establish a TRL&gt; 6.
Illinois Rocstar LLC proposes to develop and demonstrate the use of an integrated computational environment and infrastructure for electrochemical device design and simulation: ICED. This environment integrates the user's personal computational environment with high performance simulation applications for materials and processes. The current state of the art for electrochemical device design utilizes empirical or highly simplified models, homogeneous materials, and relies heavily on experimentation. ICED will enable device researchers to utilize advanced models implemented in state of the art simulation software, taking advantage of modern compute hardware, providing a truly predictive and exploratory research and design platform.

To demonstrate the feasibility of the system, Illinois Rocstar will develop a detailed three-dimensional model for nanomaterial electrode performance, including modeling of the electrode microstructure, electron conduction, and ion transport in the solid and liquid phases. This model will be integrated into a device-scale simulation with existing simplified models of all device components. The model and simulation tool will be validated against experiments conducted by our SBIR partner, Xerion Advanced Battery Corp.
Makel Engineering, Inc. (MEI) proposes to develop a miniaturized Airborne Chemical Microsensor Instrument (ACMI) suitable for real-time, airborne measurements of trace carbon dioxide, sulfur dioxide, and methane for use on unmanned aerial vehicles (UAVs.)   The potential of UAVs to carry instrument packages to support atmospheric science has been demonstrated over the past decade.  The rapid expansion of available UAV types and increased mission capability (payload, flight duration, and system cost reductions) offers wide range of potential applications.  The instrument package to be developed in the program will adapt low cost and low power chemical microsensor technology which has been demonstrated for fire detection and exhaust emission monitoring to airborne measurements.  The fast time response and miniaturized system will provide a lightweight, low cost instrument for package for a wide range of deployments including aerostats (balloons and kites) to UAV such as Dragon Eye and SIERRA. Phase I of the program will fabricate and test a prototype system to demonstrate capability of the instrument.
Dexterous performance degradation resulting from donning an extra-vehicular activity (EVA) glove limits the capability of astronauts to perform certain tasks in space.  This measurable performance loss has led to a number of design revisions, but barehanded performance with an EVA glove on is still far from achievable.  Exoskeleton concepts have also been considered to add some of the lost dexterous capability, but technology and design challenges have limited their practical utility.  As such, InnoVital Systems, Inc., in collaboration with the Space Systems Laboratory of the Aerospace Engineering Department at the University of Maryland, proposes to develop an innovative EVA glove exoskeleton for increased performance capability.  The proposed concept will employ the team's novel, miniature pneumatic artificial muscles to drive the multiple degrees of freedom of the hand to restore the functionality lost by wearing the EVA glove.  Building upon our experience in actuation, control, and space suit systems, as well as biomimetic applications, we will perform design, analysis, and fabrication in Phase I of the project, which will end with preliminary prototype testing and feasibility demonstrations.  Phase II will focus on further design refinements, controls system development, and full-scale prototype development and testing.
The goal of the Phase I effort is to design, develop and demonstrate a novel solid-state ceramic-based voltage isolator and demonstrate its potential to provide a highly radiation tolerant digital voltage isolation solution applicable to a wide range of NASA mission requirements.  The related design success QorTek has will lead to development in Phase I of a completely new gate drive technology with many advantages and benefits to the entire spectrum of NASA and commercial applications.  The Phase I design goals are focused primarily on early COMSOL Multiphysics based Finite Element Analysis (FEA) of the proposed ceramic device, as well as electrical circuit design and SPICE modeling of a high-side MOSFET gate driver system incorporating the new ceramic isolator.  This preliminary development early in the program will enable the main objective of Phase I which is to fabricate initial isolator ceramic-based gate driver prototypes and undertake basic electrical test characterization of their performance.   An all-inclusive electrical design targeted to isolated MOSFET gate driver applications will also be developed as a functional demonstration platform prototype. The purpose of the Phase I prototypes is to demonstrate, through hardware functional testing and device characterization, that the ceramic gate driver technology provides a feasible size and performance equivalent replacement for similar COTS non-rad hard isolation solutions.
The Interdisciplinary Consulting Corporation proposes a technological advancement of current state-of-the-art acoustic energy harvester for harsh environment applications.  Due to the advancement of propulsion systems and increasing power requirements, the development of a renewable energy source is ideal to overcome the related issues seen in systems powered by batteries (limited lifespan, recharge issues, accessibility and replacement).
We propose the innovation of a mesoscale, acoustic energy harvester with a Helmholtz resonator and a piezoelectric composite backplate using high temperature materials.  Additionally, a high temperature power rectifying circuitry will be developed to convert the output of the time-varying output of the energy harvester into a useable form.  The target application is to power feedback or embedded sensor systems to enable self-sustaining functionality to the devices.
NASA's future spacecraft require advanced thermal management technologies to provide effective cooling for multiple instruments and reject heat through multiple radiators.  To meet this need, we propose to develop a reconfigurable two-phase pumped loop that can accommodate a complex network of evaporators and multiple radiators.  The pumped loop has two performance features: 1) reliable refrigerant circulation with a mechanical pump even when the refrigerant flow exiting the radiators is a two-phase flow with significant vapor quality, and 2) reliable flow distribution among evaporators to minimize flow maldistribution due to heat load variation.  These features are achieved by a combination of an innovative loop configuration and Creare's proven enabling components.  In Phase I, we will prove the feasibility of reliable refrigerant circulation through building and testing a proof-of-concept pumped loop with key features, optimizing the pumped loop design and predicting its performance.  In Phase II, we will build and test an integrated pumped loop with multiple evaporators and heat sinks and demonstrate its performance in a representative thermal environment.
Ongoing work in advanced air-vehicles, such as ultra-light-weight truss-braced and elastically tailored concepts is beginning to provide the insight necessary to meet NASA's N+3 transport system goals.  Unfortunately, contemporary analysis methods are unsuited for aeroservoelastic analysis of such configurations suffering from accessibility, usability, fidelity or resource constraints.  Design tools have typically been developed using configuration dependent low-fidelity approaches that are unsuitable to reliably analyze advanced configurations.  Contemporary aeromechanics solvers (i.e. viscous compressible Computational Fluid Dynamics coupled to Finite Element structural models) can analyze advanced concepts, but require significant user input to support advanced configurations, not to mention extensive computational resources.  What has long been needed is an approach that bridges the middle ground to enable aeroservoelastic analysis at the "appropriate level of fidelity for the problem at hand", while reliably permitting the novel application of aeroelastic knowledge to new concepts, in addition to supporting wind-tunnel and flight tests by enabling the efficient investigation of flight dynamics, flutter, stability and control.  By exploiting Continuum Dynamics Inc.'s extensive experience developing fully-coupled aeromechanics methods, we propose the development of a new rapid, reliable, variable&amp;#150;fidelity first-principles physics-based aeroservoelastic analysis to support concept evaluation, wind-tunnel/flight testing and design.
The "piston errors" and aberrations of the mirror segments used in large telescopes, are typically measured with on-board optical instruments, usually a dispersed Hartman sensor (DHS) and/or dispersed fringe sensor (DFS). Calibrating and testing of the wavefront sensors are typically performed using custom-built fused silica phase plate arrays. The manufacture and assembly of each custom phase plate array is time-intensive and expensive.

Proposed is a gradient index (GI) phase plate array (PPA), which integrates the corrections of the DHS, an intermediate smoothing phase plate, and the DFS. This reduces the number of phase plates required, from three to one, and allows for the PPA t be used in the pupil plane, allowing for more precise calibration. The monolithic construction of the innovation significantly reduces development time and cost.
The primary objective of the Phase I investigation is to develop and demonstrate an innovative solution that can enable very high precision pointing accuracy (&lt;0.08 degree nominal; &lt;0.03 degree extended goal) at fast slew rates; providing part of a advanced Smallsat/CubeSat precision attitude determination and control system (PADCS) that can meet emerging very stringent missions requirements.  The Phase I program aim is to design and fabricate initial prototype hardware, including power electronics and Reaction Wheel Assembly (RWA) modifications as to demonstrating such positional accuracy capability, power cost (peak and average power consumption), slew rates and mass/volume cost of the new solution.  A critical objective of Phase I will be to develop at the decoupled control architecture for the new multi-stage Attitude Control System ACS controller that will be modeled, simulated, and then converted to hardware prototype for Phase I assessments.  This goal is to integrate this prototype controller into a multi-stage (ACS) design hardware emulation testbed and evaluate actual performance before conclusion of the program.
Modern aircraft gas turbine engines utilize highly loaded airfoils in both the compressor and turbine to maximize performance while minimizing weight, cost, and complexity.  However, high airfoil loading increases the likelihood of flow separation at lower mass flow rates.  Dielectric Barrier Discharge (DBD) plasma actuators have been shown to be a very promising technique for compressor stall control.  DBD devices can either be installed directly on rotor/stator surfaces or the compressor endwalls to control rotor tip flow.  A fundamental challenge in driving DBD actuators is providing appropriate electrical waveforms to the devices.  Creare proposes the development of an innovative compressor stall system which enables (1) substantially higher produced thrust than existing DBD actuator systems, (2) implements a unique excitation waveform that optimizes thrust production by DBD actuators, and (3) provides the potential ability to control spike-type compressor stall through controlling compressor tip leakage flow.
NASA has a need for airborne or space-based observatories and remote sensors in order to penetrate the opaque atmosphere between 1 and 10 THz. For observations &gt;2 THz, technologically mature microwave sources typically have microwatt power levels which are insufficient to act as LOs for a heterodyne receiver.   LongWave Photonics is proposing to develop a compact, frequency agile, frequency locked, single mode quantum cascade laser (QCL) system.  The distributed feedback grating (DFB) QCL arrays pack multiple devices on a single semiconductor die with individual devices lasing at different frequencies.  The source will be frequency agile over 150 GHz with center frequencies ranging from 2 to 5 THz range.  The DFB QCL array will be packaged in a high-reliability Stirling cycle cooler.  The source will be frequency locked to a gas reference cell which has multiple absorption lines.  The lines are much more closely spaced than the IF bandwidth of the detector, allowing continuous frequency coverage over the tunable range.  Phase I LO power is expected to be &gt; 1 mW with &gt; 10 mW in Phase II.  Methods for amplitude stabilization will be investigated.
Through the proposed NASA SBIR program, NanoSonic will optimize its HybridSil&amp;#174; derived yttrium silicates to serve as next-generation reinforcement for carbon and ceramic felt ablative TPS materials. This effort will leverage NanoSonic's rapidly evolving polymer derived ceramic technology, which has demonstrated thermomechanical durability in excess of 1900 oC, thermal conductivity as low as 30 mW/mK, erosion resistance to high velocity sand, and facile spray depositability under ambient conditions.  NanoSonic's yttrium silicate TPS reinforcing matrices will be molecularly engineered to drastically outperform current char-forming carbon / phenolic materials during planetary entry while weighing and costing less by providing nanocomposite matrices with substantially enhanced 1) thermo-oxidative durability, 2) impact resilience, and 3) readily tailorable high temperature ablative recession rates . The driving optimization factors for phase I TPS materials will include interfacial covalent coupling to surface functionalized carbon and ceramic felts, bulk morphology of the host matrix, and composition of the yttrium silicate polymorph. Thermal loading on promising TPS materials simulating current and future Exploration missions will be completed by the University of Washington's high enthalpy test facility. In support of a phase III transition, NanoSonic has generated significant defense prime interest and has an established pilot scale HybridSil&amp;#174; manufacturing infrastructure.
In this program, Freedom Photonics will design an innovative compact, diode laser pumped solid state laser to achieve specifications listed by the program. High efficiency will be achieved by simultaneously optimizing the pump laser and the solid state active region and cavity for high performance.
QuinStar Technology proposes to develop a high-efficiency, 4-W SSPA operating at F-band frequencies (106-114 GHz). This will be achieved by employing two major innovations. Firstly, we are employing state-of-the-art wide bandgap GaN (Gallium Nitride) devices. At millimeter-wave frequencies, these GaN devices have demonstrated power densities of 5 to 8 times higher than GaAs or InP devices. Further, we are proposing to operate these devices in a quasi-switching mode, which has demonstrated, in Phase I simulations, drain efficiencies approaching 70&#37;. The resulting MMIC, operating over the 106 to 114 GHz band, will produce an output power of one watt and an efficiency of greater than 33&#37;. Secondly, we are proposing to utilize a new low loss, H-tee combining approach to combine 4 of these high-efficiency chips to achieve 4 watts. The net result is a unique combination of high performance devices and innovative power combining. We anticipate that this work will result in an order of magnitude increase in the state-of-the-art of SSPA output power and efficiency at F-band. We anticipate that this work will be very important for NASA's Earth Science missions and for DoD W-band radar and communications applications.
Advances in spacesuits are required to support the ISS and future human exploration. Spacesuit development and ground-based testing tasks require sensing and analytical instrumentation for characterizing and validating prototypes. While miniature thermosensors measure reliably at low cost, and can be incorporated all around spacesuit prototypes, incorporating gas sensors at locations of interest inside a spacesuit has been a significant challenge &amp;#150; in particular for human subject tests &amp;#150; because of the size and cost of available instrumentation. The sensor probes and cables must not restrict the suit or human subjects' mobility, and must not disturb the gas flow. Intelligent Optical System proposes to develop luminescence-based sensing patches for non-intrusive monitoring of critical life support gas constituents and potential trace contaminants in spacesuits. Flexible sensitive patches inside prototype spacesuits will be interrogated via optical fibers, and will not disturb the gas flow or the human subject. This will give suit engineers great flexibility for choosing multiple sensing points, fitting the sensor elements into the spacesuit, and cost effectively relocating the sensor elements as desired.
The ssLAPSS expands on the SOP LAPSS by upgrading the light sources to enable future solar cell technologies while maintaining all of the current, proven calibration and test methods.  The ssLAPSS enables testing of current SOP 3-junction cells and also upcoming 4- and 6-junction solar cells. The ssLAPSS uses planar arrays of 6 different wavelength LEDs located in close proximity to the string under test in the solar array.  The individual LED intensity control gives great flexibility to meet power and spatial uniformity requirements.

The LED sources are selected to each illuminate one junction in a 6-junction cell.  The same LEDs will also be used for 3- and 4-junction cells.  This means that one ssLAPSS can measure the current (3-junction) and future (4- and 6-junction) cells.  This technology is also highly flexible so that cells with an even greater number of junctions or cells with different spectral divisions could be measure by producing a ssLAPSS with a greater number of LEDs or a different spectral mix of LEDs in the illumination array.

In addition to providing 3-, 4- and 6-junction cell capability at lower systems costs than the SOP LAPSS, the ssLAPSS also has many other benefits: it requires minimal clean room floor space, it can provide low light levels (LILT), it can measure arrays in horitozontal orientations, it can scale to any bus voltage or string length, it uses proven standards and test methods and it provides for easier calibration than the SOP LAPSS.

Four- and 6- junction LAPSS technology is necessary to evaluate, test and fly advanced solar cell technologies.  The ssLAPSS extends an essential, proven measurement method to the future of space power conversion technologies.
SIFT proposes to design and develop the Marshal system, a mixed-initiative tool for maintaining task models over the course of evolving missions. Marshal-enabled planning and scheduling systems will maintain task models so that they are in tighter correspondence with the current operating context. Marshal will provide a simple dialogue based interface to update models and affordances for incomplete or imprecise user inputs.  Marshal will actively diagnose user created plans to identify and rank queries so that users can maintain the most relevant task model constraints. 

Marshal's capabilities will stem from how it represents and reasons with a family of possible task model interpretations. As users add new constraints that may be incomplete, imprecise, or temporary, Marshal creates interpretations of the constraints. With user feedback, Marshal updates the interpretations to more closely match their intended task model.  With a family of models, Marshal can compute the expectation that user plans are consistent. Marshal also computes diagnoses explaining which assumptions about the user's intended model lead to inconsistency. From the diagnoses, Marshal populates a queue of potential plan flaws that the user can address at their convenience through natural and informative dialogues. As users interact with Marshal, it automatically maintains task models so that they can better serve mission planners as missions evolve.
In this project, KWJ proposes to develop a low power, fast response, lightweight miniature CH4 measurement system based on KWJ nano-TCD sensor for airborne measurement operation. KWJ has developed patented sub-&amp;#181;m dimension TCDs, with ultra low power consumption (&lt;10&amp;#181;W), &lt;1&amp;#181;sec response time, very high stability (&gt;10^9 measurements without re-calibration), and coupling with simple electronic circuits and algorithms. In Phase I, KWJ will fabricate nano-TCD CH4 sensor, improve the sensitivity such that 5ppm accuracy will be obtained, and characterize the sensor on a bench-top testing system to demonstrate CH4 detection with all target specifications. In Phase II, the prototype sensing system (1cmx1cm, 10g package) will be built and integrated with NASA UAVs for field testing.  The proposed sensor will be ideal for airborne gas surveys.  This sensor is part of a broader effort to develop smaller, faster, lower power and more cost effective alternative sensors for a wide range of applications. This platform will advance not only the research fields of atmospheric research, climate change, global change biology, and ecology, but for NASA's future spacecraft programs as well as KWJ's own terrestrial-industrial applications. This work has synergy within NASA and can collaborate with ongoing NASA SiC sensor developments in Phase II.
Significant challenges remain for the designers of life support equipment for spacecraft&amp;#151;primarily for the processing of aqueous fluids: oxygen supply, air revitalization, thermal management systems, water reclamation, medical fluids, and others. The main problem is that failure-prone processes are often employed to overcome unfamiliar microgravity fluidic phenomena using artificial buoyancy-inducing methods. The most obvious example is a mechanical centrifuge for liquid-gas separations aboard orbiting spacecraft. To improve NASA's spacecraft fluid systems design, InnoSense LLC (ISL) proposes to develop Superhydrophilic Coatings for Embedded Capillary Systems (SPHIL-EMCAP) with anti-microbial properties. In Phase I, ISL will design and fabricate a complex capillary solution for spacecraft fluid management. The geometric design will exploit the current state of the art in analytical and computational capillary fluidics. Devices will be coated with SPHIL-EMCAP and evaluated for substrate adhesion, water contact angles, wear, and environment robustness, before testing in the relevant low-g environment to assess the improved capillary control afforded by the superhydrophilic coatings. In Phase II, ISL will downselect materials and applications, and optimize SPHIL-EMCAP's performance by refining the prototyping process and optimizing the superhydrophilic coating formulation. We will perform extensive characterization toward manufacturing a miniaturized SPHIL-EMCAP.
NASA has an interest in the development of advanced instruments and components for Lunar and planetary science missions.  Instrumentation is needed for the exploration of inner and outer planets and their moons, comets, asteroids, etc.  As a consequence, instrumentation systems must withstand the extreme environments experienced in space and planetary environments; radiation, temperature, pressure, launch/landing stresses, etc.  

Specific areas related to instrument deployment for in situ sensors and sensor systems on a variety of space platforms including orbiters, flyby spacecraft, landers, rovers, balloon, other aerial vehicles, sub-surface penetrators, and impactors.   

The envisioned Phase I program will develop an innovative digital readout integrated circuit architecture that will increase resolution and provide improved sensitivity.  The low power design will incorporate provisions that mitigate effects of radiation and extreme temperatures.
Aurora Flight Sciences and the Massachusetts Institute of Technology (MIT) propose to develop a stand-alone 6-DOF load sensing system that collects biomechanical force and moment data while integrated with the Advanced Resistive Exercise Device (ARED) on the International Space Station by adapting and enhancing previously field-tested systems.  Our EDLS-ISS system includes a separate base unit tethered to two low-profile sensors, which can be non-invasively mounted on the surface of the ARED to serve as new footplates.

The EDLS-ISS is being developed for two reasons:
- Operational.  Force plates on the ARED will allow crewmembers to verify loading, and to record forces.  This device provides a simple, non-invasive solution that measures foot forces and displays this to the astronaut.
- Research.  Kinematic experiments on the ARED &amp;#150; for example, characterizing limb segment relative motions during a squat &amp;#150; require corresponding force and moment measurements.  Our EDLS-ISS system provides three-axis force and three-axis moment measurements for such experiments.
By providing a short-term operational solution and a sustainable long-term research solution, ELDS-ISS is an important tool for the spaceflight community.

During Phase I, we improved the design of the existing 6-DOF Microgravity Investigation of Crew Reactions in 0-G (MICR0-G) Adapt sensor module, previously developed by Aurora and MIT.  These improvements optimized the sensor for use on the ARED: decreasing the overall height of the sensors and separating the electronics into an off-board "base unit", increasing the footprint size to cover most of the surface of the ARED platform, updating the hard drive and electronics, providing a real-time user-feedback display, and developing ARED mounting options.  The anticipated result of our Phase II effort will be three complete EDLS-ISS systems, each of which includes a base unit and two sensor units.  Two systems will be flight-qualified.
Skin friction drag is directly proportional to the local shear stress of a surface and can be the largest factor in an aerodynamic body's total parasitic drag. The measurements of the local shear stress has long been a difficult measurement in an air-flow environment due to the interaction between the sensor and air flow. In order for modern researchers to further improve the efficiency of aircraft and other aerodynamic bodes, sensitive measurements in the smallest scale possible are required. To achieve this goal, the measurement community has turned towards micro-electrical mechanical systems which utilize microscopic moving parts to directly measure the shear stress. Unfortunately the cost, sensitivity, and packaging have proven to be insurmountable challenges in sensor development.
 Our company proposes a paradigm shift in shear stress measurements that will take advantage of the complete sensing package offered in MEMS without the need for moving mechanical parts or expensive manufacturing. Our patent pending sensor will allow us to measure the shear stress at a wall using microfluidic principles and fluid-structure interactions.  In our proposed sensor, highly sensitive electrochemical measurements measure the vibrations induced in a membrane by the external shear stress.  Because of the nature of electrochemical measurements, the relationship between size and sensitivity is reversed compared to MEMS sensing methods. As our sensor decreases in size, the current change induced in the system increases, resulting in a sensitivity limit imposed only by manufacturing limits. We believe that this sensor will have the ability to obtain real-time shear stress measurements across the range of external air flows. Due to the absence of moving parts within our proposed system, we believe that the sensor will be significantly more robust and durable for many different applications. At the conclusion of this project, we expect to move this technology from TRL-2 to TRL-4.
We propose the potential to develop significant improvements to size, weight, and prime power requirements of front-end cw lasers and associated frequency stabilization and offset-locking photonics and electronics that are utilized in laser-based remote sensing systems for the measurement of atmospheric CO2 concentrations and wind velocity.  The emphasis in the proposed program is to develop stable front-end sources for 2-micron wavelength systems, but it is anticipated that much of the design will be readily applicable to a broad array of short-wave IR wavelengths, e.g. 1.57 micron, by the use of alternative laser gain media.  Although the Phase I design and Phase II implementation will be aimed at airborne platforms, only designs that have a clear and practical path to future space-based implementation will be considered.  The Beyond Photonics team is uniquely qualified to explore the state-of-the-art in relevant lasers and frequency stabilization techniques and develop improved front-end systems that have a demonstrable path to robust, compact airborne and space-based applications.  Our team's deep experience with such systems lends a perspective that will yield significant gains in system compactness, efficiency, and autonomous reliability for a wide array of applications relevant to NASA's missions, and improve the viability for other commercial and military applications in eye-safe remote sensing.
Black Swift Technologies proposes the continued development, testing, validation, and delivery of the SuperSwift small Unmanned Aircraft System (sUAS), with a highly capable passive microwave radiometer to provide full coverage soil moisture measurements over an area of 400 acres per flight.  Tight integration of the sensor with the sUAS avionics and airframe will enable precise flight control for low altitude missions in the range of 15m-30m above ground level (AGL) required for the sensor to accurately map soil moisture down to ~5cm in depth at up to a 15m resolution.  The teams strong working knowledge of the regulatory environment surrounding sUAS will be used to inform the development of the system and associated concept of operations. This will facilitate safe and legal operation in the national airspace following FAA approval.
 
The continued SuperSwift system development will address the design issues identified in Phase I.  The stock airframe utilized in the Phase I study, the Tempest, while well qualified for use in preliminary flight testing, created additional challenges for integration of the soil moisture measurement payload.  Due to the requirements of the radiometer antenna the Tempest was modified during Phase I to accomplish initial flight testing, but had several challenges including external placement of the antenna, more complex manufacturing of the control linkages for the rudder and elevator, and a soil moisture electronics payload that is deeply integrated into the airframe and difficult to remove for testing and replacement. These requirements drove the team to design a modified fuselage to be built in Phase II that involves a modified removable nose cone to house the entire sensor payload and converts the propulsion to a twin engine design on the wings.
The NASA objective of expanding the human experience into the far reaches of space requires the development of regenerable life support systems.  This proposal addresses the development of an integrated air-revitalization system for the space suit used in Extravehicular Activities (EVAs).  The proposed innovations are: (1) a single CO2, trace-contaminant, and H2O management unit; (2) a single sorbent possessing the capability to remove CO2, trace contaminants, and H2O; (3) monolithic sorption unit to provide the following functions: (a) CO2 sorbent; (b) trace-contaminant sorbent; (c) H2O sorbent; (d) low pressure drop; (e) good thermal management (heat transfer and low heat of adsorption); (f) resistance to dusty environments; and (4) regenerable operation.  The overall objective is to develop a CO2/trace-contaminant/H2O removal system that is regenerable and that possesses weight, size, and power-requirement advantages over the current state of the art. The Phase 1 objectives were: (1) to demonstrate the technical feasibility of using a novel CO2 sorbent; and (2) to demonstrate effective CO2, ammonia, and H2O sorption and regeneration. These objectives were successfully accomplished. The Phase II objectives are to optimize sorbent properties and performance, to design, construct, and test a prototype, and to provide guidelines for the integration of the proposed concept with the PLSS. This will be accomplished in the following tasks: (1) Sorbent Development and Optimization; (2) Testing in Subscale Systems at Hamilton Sundstrand; (3) Prototype Design; (4) Prototype Construction; (5) Prototype Testing; and (6) System Evaluation.
KalScott Engineering, and the subcontractor, Princeton University propose the development and demonstration of compact and robust methane sensor for small Unmanned Aerial Systems (s-UAS) by synthesizing state-of-the-art, laser-based detection methods with the rapidly increasing s-UAS market. The overall goal of this project is to develop and demonstrate (via flight test) laser-based flight-weight methane sensors. In Phase I, the sensor will be built and lab-tested, followed by initial flight tests on KalScott's Cessna 210. In Phase II, a refined version of the sensor will be built, and flight tested, first on the Cessna, and then on a small UAS.
Dualband focal plane arrays (FPAs) based on gallium-free Type-II strained layer superlattice (SLS) photodiodes have recently experienced significant advances.  We propose to develop a new class of devices capable of producing simultaneous and spatially-registered images in two spectral bands, namely, a fire channel in the 3 to 5 micron window and a thermal channel covering the range of 8 to 12 microns and beyond.  Such FPAs are known to be uniquely effective for detecting wildfires either locally from aircraft or globally from satellites in low earth orbit.  The performance of SLS detectors now rivals that of mercury cadmium telluride but at a fraction of the cost.  Their high quantum efficiency combined with the advantages of two-color imagery and data interpretation will permit the detection of wildfires with much reduced false alarm rates.  The same devices will also enhance NASA's capabilities in a host of other satellite and airborne Earth-observing missions devoted to long-term global observations of the land surface, biosphere, atmosphere, and oceans.  They will also be instrumental in supporting future Space Science missions aimed at studying distant galaxies and discovering potentially habitable planets orbiting other stars.
This project will develop advanced DC link capacitors using flexible ultrathin glass dielectric materials. The glass capacitor will be able to be operated in a broad temperature range (-150 degree C to 500 degree C), frequency (1 kHz to 1 MHz), and high voltage (&gt;1,000 volts). This SBIR project will be focused on examining the technical performance of the glass dielectrics at very high (&gt;200 deg C) and very low (&lt;-100 deg C) temperature for NASA space missions with harsh and extreme environment. The performance under high radiation will also be evaluated as required by NASA. The effects of these extreme conditions on the glass dielectric and high voltage performance will be systematically examined in terms of dielectric constant, dielectric loss, dielectric breakdown strength, and leakage current.
NASA has a defined need for energy dense and highly efficient energy storage and power delivery systems for future space missions.  Compared to other fuel cell technologies, solid oxide fuel cell (SOFC) based systems are better suited to meeting NASA's efficiency targets while operating directly on methane and oxygen reactants.  SOFC power systems for lunar landers and other exploration vehicles are an ideal application for this technology, as well as for power generation on the moon or on Mars.  NexTech Materials has established SOFC technology that offers high power density with direct internal fuel reforming and high single-pass fuel utilization, making it uniquely suited for achieving NASA's performance and efficiency requirements.  In this project, NexTech will establish a process model for an SOFC system that operates with oxygen and methane reactants, design a lightweight and high efficiency SOFC stack, refine the stack design via modeling and analysis, validate the design and performance predictions via stack testing.
Agriculture faces major challenges in the decades to come due to increasing resource pressures, severe weather and climate change, population growth and shifting diets, and economic development. Rice is one of the most important crops globally considering its role in the Earth system, food security, and providing livelihoods with more than 1 billion people depending on rice. Tools and systems that can help monitor production and support risk management are needed for decision making by many end users and governments. Futures are a tool used to manage or hedge risk, reduce volatility, improve food security, and maximize efficiency and profit on the open market. Currently, the rice futures market has little high quality and timely information available to make strategic or application specific decisions to reduce risk and maximize profit. The global rice futures market is thinly traded causing extreme price fluctuation orders of magnitude. The innovation of Rice Decision Support System (RiceDSS) is the seamless fusion of operational satellite remote sensing monitoring metrics of rice agriculture, rice yield modeling, and weather forecasts to generate near real time information on rice extent, growth stages, production forecasts and statistical uncertainty. RiceDSS uses a state-of-the-art open source framework with advanced automation routines, web-GIS, and mobile technologies to support visualization and delivery of information to support global food security programs and commodity markets.
In the near future we will see the development of space mission architectures where multiple spacecraft work cooperatively as a cluster to achieve mission objectives. Fault management (FM) is a critical challenge that must be addressed, especially when multiple spacecraft are working in proximity.  Automatic fault management reduces the effort required by the ground crew when faults occur, and it reduces the chance of collision by quickly recovering from faults. We are developing a Flexible Fault Manager for Distributed Systems (FFMDS) for these missions. FFMDS is a FM architecture that will include algorithms to be run on each cluster module for fault detection, isolation, and recovery; software to be used at a ground station to direct recovery actions; and protocols for communication of fault information between cluster modules and between modules and the ground station. The architecture is service-oriented, so that algorithms for fault detection, isolation, and recovery can be added to or subtracted from the system as appropriate.
CropGlass is adhered to the top of CIC coverglass in the crops and overlapping a small area of the cell.  Light enters through the top of CropGlass and is reflected back upward.  Total internal reflection keeps the light inside CropGlass and the majority of the light is directed laterally through CropGlass and then downward onto the overlapped cell area.

CropGlass is a very low risk technology, as it is made from entirely flight heritage materials, it is low profile and it has no moving parts.  Additionally, CropGlass leverages mature nano- and micro-fabrication techniques which will result in a low cost for high volumes.

CropGlass offers the ability to increase power or decrease cost without influencing other solar array design parameters.  Very large solar arrays will benefit most because of the huge power levels and cost of these programs.  Because CropGlass can be added to a complete array, this innovation will also be beneficial to completed solar array programs that experienced less than anticipated power or increases in needed power late in the manufacture of the solar arrays.

Competing approaches include reflective concentrators such as panel edge reflectors.  What makes crop glass unique is that it is flat, requires no deployment of optics and does not require a custom solar panel or blanket design.  No existing concentration technology offers such a low cost, low risk and flight heritage-based path to higher power and lower cost.

CropGlass concentrates light at less than 3x.  Past industry attempts at concentration above 10x have shown many engineering challenges at these high concentration levels.  These challenges include heat rejection, outgassing of concentrator material and power loss in off-pointing.  Conversely the industry has heritage of successful concentration at lower levels.
This program addresses the need for interfacial and in-depth temperature monitoring of thermal protection systems (TPS).  Novel, linear drive, eddy current methods are proposed that incorporate innovative sensor array constructs, physics-based models, and multivariate inverse methods to nondestructively assess temperatures for carbon-based TPS materials such as felts and PICA.  The sensors can be mounted behind the TPS material or embedded within the TPS with sensing fields that are projected through the material to the far surface interface.  Thermally induced changes in the electrical properties of the TPS material are then used to determine the temperatures.  In Phase I, the focus is on establishing feasibility by demonstrating correlations between electrical properties measured by the eddy current sensors and the TPS temperature.  It will also investigate adaptation of the sensor materials to support sustained and transient operation at high temperatures compared to typical operating conditions for standard eddy current sensors.  JENTEK's physics-based methods for diagnostics of layered media using MWM-Array technologies have been demonstrated in scanning configurations for coating characterization, corrosion detection and sizing with and without interference layers, and condition and thickness assessment of felt-based TPS materials.  These methods have also been extended to surface mounted sensing applications such as torque, fatigue, and heat treatment condition monitoring.  JENTEK delivered the MWM-Array solution used by NASA KSC on the Space Shuttle leading edge to detect damage of the reinforced carbon-carbon (RCC) thermal protection tiles; thus after establishing the property correlations with temperature, JENTEK is well-positioned to deliver a novel method for temperature monitoring of TPS materials and material condition monitoring at elevated temperatures.
As the MegaFlex solar array is scaled for power demands greater than 50kW over the next 20 years and deployed load requirements remain high or increase, advanced MegaFlex blanket support spar designs will be desired. The spars are the structural members that support the MegaFlex solar array deployed blanket.  When the solar array experiences a deployed load, the structural load path starts in the spars which carry the load to the hub assembly that then pass it on to the latched panel assemblies that act as the structural back-bone of the deployed array and carry the load to the solar array to spacecraft interface. Therefore as the MegaFlex blanket areas increase the spar loading increases which causes higher stress levels in the spars, unless they are appropriately scaled in size. However directly scaling the spars in size from their current design state is not the most optimized design for strength and mass. This is why AD proposes to develop a hierarchical set of MegaFlex spar designs with ATK. 

Successful performance of this proposed strategic plan has far reaching benefits which start with the scaling risk reduction of larger future MegaFlex solar arrays to support power demands beyond 50kW with high deployed loading requirements. The benefits continue with mass savings for these arrays obtained by the mass optimized future spars which will enable more payload for future HEOMD or other missions and or launch cost savings. Finally, development costs for future flight qualification of a MegaFlex solar array &gt;50kW in size with high deployed loading requirements will be saved because this work will already have been completed. All of these benefits support future HEOMD missions and others, which therefore further validates the merit of the proposed innovation and work to be completed on this SBIR.
To address the NASA need for an extravehicular activity (EVA) information display device, Physical Optics Corporation (POC) proposes to advance development of a new Projection/Reflection Heads-up Display (Pro/Ref-HUD) based on innovative integration of liquid crystal display (LCD) screen projectors, partially see-through optical reflectors and unique ergonomic designs. This approach enables the displayed image to meet NASA EVA requirements and is completely decoupled from the user's head while achieving full sunlight readability with automated rapid ambient light response. The Pro/Ref-HUD offers full-color, high-resolution collimated images, with large fields of view, highly suited to the space and weight constraints inside an astronaut's suit. In Phase I, POC successfully demonstrated the feasibility of the Pro/Ref-HUD system by designing, building, and testing a TRL-4 prototype. In this Phase II, POC proposes to develop a fully functional prototype to demonstrate sunlight readability and SXGA resolution, investigate thermal and radiation issues, and analyze ignition safety due to a 100&#37; oxygen operating environment as well as vacuum and extreme temperature environments. The results to be developed and demonstrated in Phase II will offer NASA capabilities to perform EVA operations with heads-up displays internal to the helmet enhancing crew situation awareness, comfort, and safety.
Advances in computer-aided mission planning can enhance mission operations and science return for surface missions to Mars, the Moon, and beyond. While the innovations envisioned by this program are broadly applicable, they serve an immediate and urgent need for missions to prospect for volatiles at the lunar poles (i.e., the NASA Lunar Resource Prospector Mission, currently in Phase A). These missions must be rapid and precise, covering multiple kilometers in approximately 10-12 Earth days to complete mission objectives in one lunar light cycle. This calls for the ability to drive intentionally and efficiently to precise drilling destinations. Polar operations encounter low angle lighting; this creates shadows which confront robot operations with challenges in power production, thermal control, and operator situational awareness. This demands robust path planning for efficient mission planning and execution.

The proposed work develops a computer-aided mission planning tool that balances the competing demands of efficient routes, scientific information gain, and rover constraints (e.g., kinematics, communication, power, thermal, and terrainability) to generate and analyze optimized routes between sequences of locations. Planner-computed statistics about the set of viable paths enable mission planners, scientists, and operators to efficiently select routes considering a range of priorities including risk, duration, and science return. This planner will serve an invaluable role in preplanning missions and as a tool for rapidly understanding the impact of changes in mission profile during the mission execution.
The overall goal of this SBIR effort is development of a space qualifiable, compact, frequency stabilized seed laser with low SWaP for routine use in NASA LaRC's High Spectral Resolution Lidar (HSRL) flight-based and future space-based systems.  In addition to refining process parameters to optimize performance, a major goal of the Phase II effort is risk mitigation through accelerated life testing and environmental component level testing to advance this highly efficient, waveguide-based Seed Laser System to TRL 6.  Successful development of this technology, due to its compact, efficient, and reliable design, will enable further uses of the HSRL-based remote sensing system both in current flight-based systems and in future space-based systems.
This program addresses the need for non-destructive evaluation (NDE) methods for quality assessment and defect evaluation of thermal protection systems (TPS).  Novel linear drive eddy current methods are proposed for NDE of carbon-based TPS materials, such as felts, rigid materials, and three dimensional woven fiber composites. Using a combination of physics-based models of layered media, including an eddy current micromechanical model extension for composites, multivariate inverse methods, high resolution imaging, and innovative sensor array constructs, the developed methods will independently measure the material characteristics of interest.  In Phase I, the focus was on adapting methods developed for carbon-based composite structures and laminates and demonstrating feasibility of these methods for felts, rigid materials, and three-dimensional woven composites.   In Phase II, the focus is on maturing this method, including the instrumentation hardware, models, and sensor designs, to provide scanning assessment and in-situ monitoring capabilities for TPS material condition assessment.  JENTEK's MWM-Arrays have a linear drive that permits both scanned type imaging and permanent installation for monitoring of anisotropic properties, temperature, and stresses at multiple depths.  The projected depth of the magnetic field into the test material can be adjusted through the sensor dimensions and excitation frequencies; this enables inspection of materials more than 1.0-in. thick and supports measuring far-side surface recession in ablator materials.  JENTEK delivered the MWM-Array solution used by NASA KSC on the Space Shuttle Leading Edge to detect damage of the Reinforced Carbon-Carbon (RCC) thermal protection tiles; thus JENTEK is well-positioned to deliver a practical TPS NDE solution.
Systems &amp; Processes Engineering Corporation (SPEC) proposes a Wind Measurement LIDAR whose sensor assembly is composed of SPEC Gen IV LIDAR seeker, with 12.8 Mpps imaging rate, modified with a laser with ultra-narrow band seed, AOM and modulator, to allow air current Doppler detection beyond 3km.  The sensor output is Doppler shift in 3D pixels (voxels) in a 90 degree cone. The specifications were sized to detect energy sources are vertical uplifts, wind direction, wind gradients and transient gusts for optimal path determination for energy conservation in UAVs with less than 1mps accuracy at 10Hz sampling.  
The Gen IV LIDAR is the latest member of SPEC's family of LIDARs and features 2 inch aperture, 10km range in clear air, range accuracy of 3mm at close range 30mm at acquisition range, and deep waveform capture capability.  The LIDAR can use scanner with fields of view from 30 to 90 degrees, and features pipeline processing for real time image output.  In the fully miniaturized version the unit is 3.5 inches diameter by 8.5 inches long.  The Doppler modifications would increase this length by 1 inch.
The National Airspace System (NAS) in the United States will become a complex array of commercial and general aviation aircraft, unmanned aircraft systems, reusable launch vehicles, rotorcraft, airports, air traffic control, weather services, and maintenance operations, among others.  The Federal Aviation Administration (FAA) projects that by 2025 air traffic will increase by more than 50 percent with 1.1 billion passengers a year and more than 85,000 flights every 24 hours contributing to further delays and congestion in the sky. This increased system complexity necessitates the application of systematic safety risk analysis methods to understand and eliminate where possible, reduce, and/or mitigate risk factors.  The product of this effort is the development of an Uninhabited Aerial System (UAS) safety analysis model (USAM).  USAM is ground-breaking technology that combines research NASA has already conducted on future UAS flights and UAS performance profiles with technologies developed specifically for UAS flight risk analysis and NAS-wide simulation analysis.  The combination of these technologies answers this important question by leveraging on existing work in creative ways and adapting it to the needs of the UAS aviation safety community.
CO2 sensing using absorption bands near 1570nm is very attractive by taking advantage of the mature fiber-amplifier technology derived from fiber-optic telecom heritage. This necessitates sufficient power scaling in 1.5 micrometer fiber-amplifiers, either in the pulsed-mode, or in the cw-mode for modulation spectroscopy. In this SBIR program we propose the design, optimization, experimental evaluation and prototype development of a high-power, high wall-plug efficiency, 1571 nm fiber-amplifier laser transmitter, compatible with multi-line cw intensity-modulated integrated-path differential absorption spectroscopy, with the size, weight and power (SWaP) optimized for airborne and directly supports and enables space-qualifiable roadmap for Earth Venture (2015) and ASCENDS missions. We leverage innovations in high-power 1.5 micrometer fiber-optic technology and fiber-amplifier architecture, while using high-reliability 1.5 micrometer silica-fiber based passive/active components. Our expectation is that at the end of Phase 2, a TRL-6 level hardware can be developed and delivered for an airborne mission, and which is also compatible with a space-flight maturation roadmap.
Busek proposes to develop and life-test a flight-weight, 5N class green monopropellant thruster in Phase II. The most important feature that sets this thruster apart from other similar devices will be the use of an innovative, long-life catalyst. This proprietary catalyst, constructed without any bed plate or ceramic substrate, has the potential to suppress catalyst-related performance degradation problems that often plague monopropellant thrusters. The Phase II thruster in essence will be a matured version of the highly-successful Phase I prototype, with the addition of high-temperature nozzle material.  To further demonstrate the design's scalability, a 100N class thruster will be developed and demonstrated at the end of Phase II.
NASA's future science missions to investigate the structure and evolution of the universe require efficient, very low temperature coolers for low noise detector systems.  We propose to develop a highly efficient, lightweight Active Magnetic Regenerative Refrigeration (AMRR) system that can continuously provide remote/distributed cooling at temperatures of about 2 K with a heat sink at about 15 K.  The AMRR system uses three novel design features to achieve a large cooling capacity and very high thermal efficiency: a vibration-free, reversible cryogenic circulator; innovative micromachined regenerators; and lightweight superconducting magnets.  The superconducting magnet uses low-current superconducting wires and a unique winding arrangement to enable an AMRR system to achieve high thermal efficiency. In Phase I, we selected an optimum superconducting material for the magnet and developed its electrical and structural support subsystems.  Based on the performance characteristics of the magnet, we optimized the magnetic field and showed by analysis that the AMRR system driven by such a magnetic field will be able to achieve high efficiency.  In Phase II, we will build and characterize a superconducting magnet, assemble a brassboard AMRR system with a circulator and an active magnetic regenerator, and demonstrate the system performance under prototypical conditions.  In Phase III, we will assemble a fully integrated Engineering Model AMRR system and demonstrate its performance.
The goal of this proposed program through Phase III is to build a space-worthy Drug Stability Analyzer that can determine the extent of drug degradation.  It will be able to monitor the drug active pharmaceutical ingredient (API) and its degradation product concentrations as a function of time, as well as determine if a drug is suitable for use.  This will be accomplished by designing and building a rugged, small, low mass, low power, easy to use analyzer that can identify and quantify API and degradation products with little or no sample handling in 1 minute.  Feasibility was successfully demonstrated during Phase I by measuring acetaminophen, azithromycin, epinephrine, lidocaine, and their degradation products in mixtures and during reaction with a 1-4&#37; limit of detection.  The API's were also successfully measured in commercial products.  During the Phase II program a prototype Drug Stability Analyzer, suitable for space deployment will be built and used to measure the degradants of all the ISS medical kit drugs (&gt;100) with an accuracy goal of 2&#37; and a precision goal of 1&#37; within 1 minute.  The Drug Stability Analyzer will be transitioned from a TRL 3 to a 7 (ground tested).
Building upon the successful proof of concept work in Phase I, Luna Innovations Incorporated is proposing to design, build, and test a sensing tether for marsupial rovers.  This tether will be capable of monitoring its own distributed tension, curvature, length, and shape, enabling greater flexibility in robotic exploration and sample-gathering missions conducted on remote planets and moons.  By providing information about elevation changes, potential points of harm and deployed length, the sensing tether will add crucial information during the course of the mission.  The distributed tension and curvature measurements are particularly useful, as they indicate when the rover has become stuck, descended a slope or lost traction. Luna's sensing tether has the ability to measure its own path as it stretches between the marsupial rover and its base, giving position and orientation information not just on the tether, but also on the attached rover.  Made from a single strand of custom optical fiber, Luna's shape fiber is lightweight and flexible, easily fitting inside existing tether packages.
Flight-critical systems rely on an ever increasing amount of software&amp;#151;the Boe- ing 777 contains over 2 million lines of code. Most of this code is written in the C programming language. We need a scalable static formal program verification tool that is able to prove the functional correctness of flight-critical software, limiting any failure of flight critical software to hardware faults.
This project seeks to leverage the matching logic verification framework. Matching logic is generic in an operational semantic of a given programming language, so we also seek to give a semantics of a subset of C, called CIL, which is guaranteed to be deterministic. While we already have a semantics for the entirety of C, CIL is more representative of flight-critical software, and the simpler, deterministic semantics will result in a more efficient, and thus more scalable, static program verification tool. We are also building a new unification- based rewrite engine that will result in a more powerful version of the Matching Logic Framework.  In order to make the tool more commercially feasible, we will develop new techniques in pattern inference, so that loop invariants and some pre/post conditions can be determined automatically.  We will perform a thorough evaluation of our tool on a large-scale piece of software with similar characteristics to a flight system.
Busek is developing a high throughput nominal 100-W Hall Effect Thruster.  This device is well sized for spacecraft ranging in size from several tens of kilograms to several hundred kilograms.  It could be fueled by either xenon or iodine.  The latter yields performance like xenon, but stores at low pressure and high density, make it especially attractive for volume limited spacecraft.  The available specific impulse will be 1400-1600-s. The target thruster efficiency is 45&#37;.  At 100-W and 1500-s, the thrust will be 6.1 mN.  The lifetime of the thruster may exceed 10,000 hours, yielding a throughput of greater than 14.9 kg.
 
In Phase I, the thruster was designed. Design considerations included efficiency, specific impulse, temperature, lifetime, mass, volume, and cost.  Careful attention to the magnetic field resulted in a "magnetically shielded" shape, which should minimize or entirely eliminate ion wall losses.  Testing with a nominal 200-W thruster showed the feasibility and desirability of both permanent magnets and a diamond discharge channel.  Permanent magnets save mass, volume, and power.  Diamond reduces ion sputtering by 50&#37; with respect to conventional materials.

In Phase II, the 100-W thruster and a compact cathode to accompany it will be manufactured, tested, and improved.  Performance, lifetime, and plume properties will be evaluated.  Testing will include both xenon and iodine.  Year 2 development will focus on maximizing throughput.  Integrated testing will include a compact, low cost, power processing unit. The technology will reach TRL 5.

The program is responsive to NASA topic S3.03, Propulsion Systems. Both the "Electric Propulsion" and "Micro-Propulsion" sub-topics are relevant.  The proposal also addresses several of NASA's Grand Challenges, including Efficient In-Space Transportation, Space Debris Hazard Mitigation, and Economical Space Access.
This SBIR Phase II proposal overcomes technology barriers for developing highly efficient all electric aircraft systems for the future, with limited impact to the environment. Turboelectric propulsion for aircraft applications is envisioned, and cryogenic and superconducting components are sought. In particular, low AC loss superconducting wires for the stator windings and superconducting wires with filaments less than 10 micrometers in diameter are of interest. There is an intense push in the aircraft industry to ultimately develop an all-electric aircraft, with liquid hydrogen and fuel cells being considered as the prime generation source for aircraft propulsion. The U.S. is in competition with Europe for the development the next generation all-electric aircraft.  Superconductivity especially magnesium diboride (MgB2) superconductors are considered an enabling technology that is being investigated by NASA, Air Force, Rolls-Royce, Airbus and EADS.  This means the need for a low cost, low AC loss (fine filament superconductor) that can operate in the 10-25K temperature range in 0-2 tesla fields for superconducting stators for motors and generators.  This wire is need by 2016-2017 time frame so all cryogenic motors and generators can fabricated and tested in the NASA test bed.  In the Phase I Hyper Tech has shown that fine filament MgB2 wires can be fabricated and there is potential for low AC losses in the 60-400 Hz range for stators.  In the Phase II Hyper Tech will continue to work on developing, manufacturing, and testing fine filament MgB2 wire.  The wires will also be twisted to reduce coupling losses.  The wires will be tested for their superconductor and engineering current density and AC losses.  The result of this work will be a low AC loss MgB2 superconductor wire for enabling all-electric aircraft development and allow the U.S. industry to lead the world in this needed and rapid developing technology.
This Phase II SBIR project deals with the design, development, and testing of a "Plasma Fairing" to reduce noise on the Gulfstream G550 landing gear.  The plasma fairing will use single dielectric barrier discharge (SDBD) plasma actuators to reduce flow- separations and impingement around the landing gear, which are the dominant sources of landing gear noise.  The Phase I project successfully demonstrated the feasibility of the plasma fairing concept on a generalized tandem cylinder configuration that shared important features of key sections of the G550 landing gear, specifically the relationship between the strut and the torque arm.  The Phase II extends the concept to a more complex geometry: G550 landing gear.  We will develop aeroacoustic simulations using University of Notre Dame's state-of-the-art plasma actuator model and Exa Corporation's flow solver PowerFLOW, coupled with experiments in an anechoic wind tunnel with both aerodynamic and acoustic measurements on a scaled G550 nose gear model to design and optimize a Plasma Fairing configuration that provides significant noise reduction on the G550 landing gear.  We anticipate a technology readiness level (TRL) of 5 at the end of the Phase II project.
Leveraging a rapidly evolving state-of-the-art technical base empowered by Phase I NASA SBIR funding, NanoSonic's polymer derived rare earth silicate EBCs will provide a paradigm breaking advancement for NTPs by extending the operational utility of NTP rocket thrust chambers and nozzles. Unlike competing deposition technologies severely limited by substrate size and dimensions, NanoSonic's rare earth silicate coatings may be spray deposited under ambient conditions onto large area complex substrates and converted to mechanically robust, thermally insulative EBCs on a production basis.  In fact, legacy spray equipment employed for hardcoat deposition within the marine, automotive and aerospace industries has been used for successful EBC deposition. Simulated NTP testing completed by the University of Washington on coated Inconel 625 substrates indicate five candidate EBCs have exceptional environmental, dimensional, and adhesive durability within flow conditions representative of NTP rocket engines. In fact, zero spallation, erosion, or any other form of coating degradation was observed at the thermal limit of testing of 1,950 C. All candidate resins may be transitioned to 200-gallon batch production quantities within an established manufacturing infrastructure.
Spacecraft and remote vehicle operations demand a high level of responsiveness in dynamic environments.  During operations it is possible for unexpected events and anomalies to disrupt the mission schedule, and in the case of critical faults, even threaten the health and safety of the spacecraft.    The planner's relatively slow response time to unexpected events (changes in resource levels, failed activity indications, flight software fault indications) during dynamic and critical operations means that it does not suffice as a sole solution to the vehicle autonomy when the primary purpose is to keep it safe and ensure mission success.  Mission success can also be enhanced through the use of a sequence engine that provides reactive capabilities. Traditional sequence engines execute commands without regard to the overall safety of the vehicle.  Through the use of a reactive sequence engine that utilizes State Machine technology vehicle further enhances safety and the probability of mission success.
 
The Integrated Scheduler-Planner And Reactive Executive (I-SPAREX) architecture utilizes a layered software architecture (an approach proven successful on previously flown autonomous demonstration missions such as EO-1) and incorporates an existing goal-based, planning solution as well as an advanced, real-time, decision-making sequence engine. Specifically, we plan to study and demonstrate the feasibility of integrating NASA JPL's CASPER (Continuous Activity Scheduling Planning Execution and Re-planning) as the Continuous Planning Layer (CPL), and VML 3.0 (Virtual Machine Language) as the Reactive Sequencing Layer (RSL) providing programmable heuristic control.  We choose to focus on CASPER and VML in this proposal, given the demonstrated flight heritage of both components.
The proposed innovation is a power conversion technology that will help achieve NASA's Fundamental Aeronautics Program (FAP) goals of reducing emissions and increasing fuel efficiency for high speed flight.  NASA's objective to increase the specific power of high efficiency electric components in order to make a 10 mega-watt onboard power generation and/or utilization feasible for propulsion requires the development of sub-scale technologies to support the development and validation of newer turbo-electric aircraft and embedded boundary layer electric propulsion systems.  Compact and lightweight turbine generators scaling from the kW to MW class are needed to transition high speed aircraft to hybrid electric propulsion systems. Metis Design Corp is developing a lightweight, compact, gas turbine generator that draws on recent innovations in the fields of permanent magnet generators and turbomachinery, to achieve a target power density of over twice the state-of-the-art and the potential to scale to 100's of kW.  The proposed turbine engine uses a lightweight, two-spool configuration that eliminates the need for the heavy reduction gearbox required by state-of-the-art systems.  Phase II of this SBIR effort will develop a detailed design, then fabricate and test the complete turbine generator sub-system in a laboratory environment.
NASA requires instrumentation technologies that can be applied to measure flow under extreme temperatures where traditional sensing methodologies cannot be used.  The proposed Phase II SBIR research effort will seek to create wall shear sensors that can be applied to measure signals at temperatures in excess of 1,100
A novel design for an in situ air sampling sensor for CO2 and trace gases is proposed. The sensor, named AirCore, provides the advantages of existing in situ sensors (e.g. high resolution) but eliminates possible biases in analysis that often originate from imperfect measurement condition. The AirCore provides a significant savings in cost and weight while increasing the capabilities of existing in situ sensors. The AirCore system consists of the AirCore gas sampler and the support system to accomplish its high altitude (nominally 70,000+ ft.) mission. This support system includes the sensor launch and recovery components. The AirCore can be launched and recovered by a limited crew, which reduces the operational cost of the system.
Solar-blind ultraviolet (UV) imaging is needed in the fields of astronomy, national defense, and bio-chemistry. United Silicon Carbide, Inc. proposes to develop a monolithic, solar-blind UV image sensor with 320 x 256 pixels on a 25 micron pitch with a frame rate of 50 frames per second and pixel fill factor over 80&#37;. A silicon carbide (SiC) integrated circuit technology that is compatible with production in commercial silicon fabs will be used to fabricate the sensors. SiC is an ideal choice because of 1) its material properties that lead to high UV quantum efficiency while being inherently insensitive to visible and near IR light, negligible dark current up to high temperatures, and excellent radiation tolerance and 2) technological maturity demonstrated by commercially available 4-inch wafers and previous demonstrations of SiC integrated circuits by NASA, United Silicon Carbide Inc. and others. Monolithic integration improves sensor reliability and performance over hybrid approaches and the manufacturability of the n-channel JFET fabrication process provides a clear path to commercializing the technology.

In addition to producing monolithic solar-blind UV sensors, the underlying SiC integrated circuit technology being developed has numerous harsh environment analog sensing and electronics applications.
Deployable Space Systems, Inc. (DSS) will focus the proposed SBIR Phase 2 program on the development and demonstration of an automated robotic manufacturing infrastructure designed to mass-produce DSS's Integrated Modular Blanket Assembly (IMBA) common photovoltaic Standard Power Modules (SPM's). The proposed development and demonstration will implement automated manufacturing processes for CIC-ing, glassing, stringing, laydown, and validation testing of interconnected photovoltaic devices onto an ultra-lightweight IMBA/SPM modular flexible blanket assembly through simple and commercially available pick-and-place robotic manufacturing techniques / equipment.  Robotically automated manufacturing of IMBA/SPM photovoltaic panel assemblies will provide game-changing affordability / cost-savings when compared to current labor intensive manufacturing processes.  Unlike the current industry approach which is only focused on increasing the device area to only minimally reduce panel assembly costs, the proposed automated manufacturing will attack the highest/most labor intensive cost components of manufacturing a panel assembly, namely; CICing, glassing, stringing, panel laydown, and validation testing.   DSS's modular IMBA/SPM photovoltaic flexible blanket assembly coupled with automated manufacturing promises to provide ultra-affordable, high-performance, and repeatable high-quality photovoltaic panel assemblies for future NASA Space Science and Exploration missions, and particularly for ultra-high-power SEP missions.
Deployable Space Systems, Inc. (DSS), in partnership with MOLLC will focus the proposed NASA Phase 2 effort on the development and demonstration of our innovative Multi-A.U. SOLAROSA technology.  SOLAROSA, named for Stretched Optical Lens Architecture on Roll-Out Solar Array, is a new lightweight, high-performance space solar array that enables missions through low-cost, lightweight, compact stowage volume, radiation hardness, high voltage capability, scalability to ultra-high power, and LILT/HIHT environment operability.  SOLAROSA is a fusion of the proven Stretched Lens Array (SLA) concentrator technology with DSS's innovative ultra-lightweight Roll-Out Solar Array deployable structural platform.  The proposed Phase 2 program is specifically focused on technology development and demonstration of multi-A.U. operability, large beta axis off-pointing operational capability, and high radiation environmental survivability.  The proposed Phase 2 program provides NASA/industry a near-term and low-risk solar array that provides revolutionary performance in terms of high specific power, affordability, lightweight, high deployed stiffness, high deployed strength, compact stowage volume, reliability, high radiation tolerance, high voltage operation capability, scalability, and LILT/HIHT operation capability.  The predicted performance metrics for the SOLAROSA technology are incredible improvements over current state-of-the-art, and in many cases are mission-enabling for future NASA Space Science and Exploration missions, and particularly for NASA deep space solar electric propulsion (SEP) high-voltage and high radiation missions.
Fault Management (FM) is critical to mission operations and particularly so for complex instruments &amp;#150; such as those used for aircraft and spacecraft. FM software and methodologies, however, too often have nagging limitations that restrict utility, and research and development continues to grapple relative to advancements in the complex systems they monitor. Modern spacecraft, for example, may have thousands of sensors and hundreds of systems/subsystems (and extensive cabling) but relatively few FM co-solutions. Theoretically, the overall FM challenge is in monitoring, modeling, and managing the huge numbers of signals and then determining how to detect them and set appropriate handling actions.

For complex systems FM is not trivial, and automated FM is tasked with catching potential failure conditions within interconnected networks before consequences elevate. Ensuring fault coverage while maintaining system reliability under these circumstances is a daunting challenge for even the most capable team, and from anecdotal evidence, it is apparent that FM remains partly elusive.

Our SBIR project herein involves the research and development of an innovative FM software solution called "DyMA-FM" (Dynamic Multivariate Assessment for Fault Management). As software, it uses model-based reasoning in a distributed processing environment for real-time detection and response to fault conditions.

Building on the Phase I successes, in the course of this Phase II we will further develop the DyMA-FM concept as an innovative full prototype FM software application, having a tiered hierarchical architecture design leveraging advances in mathematical modeling. Thus, as per the intent of the Phase II, we believe we have a well-defined and innovative FM system capable of meeting the NASA requirements and representative thematic goals of: (1) verifiability, (2) transparency, and (3) fault coverage. Phase II, then, will allow us to advance the development further and fully.
NASA has drawn attention to an impending need to improve energy-efficiency in low supersonic (M&lt;~3) platforms. Aerodynamic efficiency is the foundation of energy-efficient flight in any regime, and low drag is one of the fundamental characteristics of aerodynamic efficiency. For supersonic aircraft, drag can be broadly decomposed into four components: viscous or skin friction drag, lift-induced drag, wave or compressibility drag, and excrescence drag. The relative impact of these four drag forces depends upon vehicle-specific characteristics and design. However, viscous skin friction drag stands out as particularly significant across most classes of flight vehicles. Therefore, effective techniques to reduce skin friction drag on a vehicle will have a major and far-reaching impact on flight efficiency for low supersonic aircraft. In an effort to address the need for increased aerodynamic efficiency of low supersonic vehicles, PM&amp;AM Research, in collaboration with Texas A&amp;M University, propose to build upon our successful Phase I effort to mature/develop our novel energy deposition technologies, using basic, well-demonstrated energy-deposition techniques along the surface in supersonic flow to control/compress/forcibly-move the boundary layer fluid by creating a low-density "bubble-like" region, thereby reducing the viscous skin friction. Once matured, this solution will reduce the drag experienced by a low supersonic platform, allowing vehicles to exhibit increased aerodynamic efficiency.
Technological advances (GPWS, TCAS, FMS, WAAS, ESV, ADS-B) improved flight safety but engendered more complexity and increased pilot/computer interaction and workload with aviation accident rate unchanged for the past decade. Cockpit interactions would be safer and more efficient thorugh Voice Communication. Though Voice Recognition systems are becoming widely used, in flight environment conditions usage has been limited due to the unique challenges of elevated noise levels, specific cockpit lexicon, limited cockpit hardware, and lack of standardization.  SouthernAir Aviation Inc. has developed a NextGen Voice Activated Cockpit Management system with applications for flight procedures, emergency procedures, control of aircraft systems and flight management systems.  From simple to complex architectures, the system syncronizes software applications and aircraft systems in a unified model of both language and safety critical development environment to voice activate functions using NextGen Voice Recognition with heuristic pilot response.  Procedures are enabled through wireless Bluetooth connection or wired communication. Additional tools of the system include a novel HMM Model comprising a decision management algorithm and synthetic lexicon for parsing and contiguous recognition.  All the performance requirements are met within a 2&#37; time-slice of a 700MHz Power PC processor and within 1 GB of memory.  Unique key capabilities include: Automatic Lexicon Development, Phonetic Distance Analysis, Coarticulation Handling, Accent Tolerability.  The NextGen advanced performance relies on allophone parsing and reduced recognition error with data processing in real-time, ideal for critical emergency situations. This system is remarkable in that it achieves very high recognition rates (98&#37;) with a very large command set (131,000 unique words and thousands of word combinations).

We gratefully acknowledge NASA SBIR Phase I Support.
Refueling spacecraft in space offers tremendous benefits for increased spacecraft payload capacity and reduced launch cost.  However, there are several key challenges with space refueling associated with the storage and handling of liquid cryogens in space.  To meet these challenges, we propose to develop a reliable, compact, efficient cryogenic mixing pump with no moving parts.  The mixing pump will prevent thermal stratification of the cryogen and simplify pressure control for storage tanks.  The mixing pump uses an innovative thermodynamic process to generate fluid jets to promote fluid mixing, eliminating the need for mechanical pumps.  Our innovative mechanism will be able to self-prime and generate a high-pressure rise.  The device will significantly enhance the reliability of pressure control systems for storage tanks.  In Phase I, we demonstrated the feasibility of our approach through building and testing a proof-of-concept mixing pump, optimizing the mixing pump design by analysis, and developing a preliminary layout design of a prototype pump.  In Phase II, we will build and test a laboratory-scale cryogenic mixing pump, demonstrate its performance in a representative cryogenic environment, and deliver the pump to a NASA research lab for further evaluation.
We propose a radical new approach for to the design and fabrication of a fiber-less Interferometric Optical Gyroscope (IOG) that enables the production of a radiation hard, very small IMU with better performance, higher reliability, high level of robustness and lower cost. We estimate that an order-of-magnitude improvement in cost and size to performance ratio of IOG sensors and their corresponding assemblies can be achieved when compared to the conventional Fiber Optics Gyroscope (FOG) implementations, enabling high level of performance in a MEMs compatible IMU size. Such a system will be of great advantage for all future NASA applications that focus on small satellites and payloads
The Phase II project will lead to the design, construction, and field-testing of a prototype PHOCS instrument for atmospheric column retrievals of oxygen and carbon dioxide. The carbon dioxide wavelength range may also be extended to add methane and carbon monoxide measurements depending on laser performance. The prototype will include the improvement to heterodyne spectroscopy invented in Phase I. The project will move Mesa Photonics' technology toward commercializing compact, portable instruments that combine high spectral resolution with high sensitivity and rapid data acquisition.

The requirements for implementing a successful Phase II prototype are straightforward responses to the lessons learned in Phase I. The Phase II work plan will implement the following hardware improvements:
?	Mount the light collection optics on a commercial solar tracker that has a built-in GPS to simplify setup at different locations.
?	Replace the current external cavity laser used for the oxygen spectral range with a laser having two orders of magnitude better wavelength repeatability and an order of magnitude faster wavelength switching speed.
?	Eliminate the electronic noise canceller. Phase I results showed that fluctuations in collected sunlight intensity is the dominant PHOCS noise source. Laser excess noise is small in comparison. The Phase I invention does a much better job of improving sensitivity than does the noise canceller.
?	Switch from a narrowly tunable laser to a widely tunable one for carbon dioxide measurements. As with oxygen, the improved laser will allow fast measurements of selected absorption lines.
?	Consolidate the signal processing electronics onto a custom-built, compact, low-power circuit board and replace the commercial lock-in amplifier with new dual, single-board lock-in amplifier that Mesa Photonics has developed.
The Phase II project will develop a suite of diagnostic sensors using Direct Write technology to measure temperature, surface recession depth, and heat flux of an ablative thermal protection system (TPS) in real time, which can be integrated to support TPS evaluation and in-situ diagnostics during planetary entry.  Standalone heat flux sensors and those fabricated by direct deposition will be developed and demonstrated for integration within TPS materials for use in extreme re-entry conditions.  The intent is to use the sensors for real time temperature/heat flux measurements to validate new materials and systems, as well as for flight structures where space and accessibility are limited.  Methods for incorporating thermocouples, heat flux and recession sensors using Direct Write technology will be developed to provide accurate sensing capabilities.  Notably, recession tolerant heat flux sensors will be designed and fabricated to demonstrate feasibility of this new heat flux sensor technology and subsequent instrumentation capability for TPS.
Constructing, maintaining, and adapting operational procedures for manned space operations is a complex task, requiring the procedure author to satisfy constraints resulting from the system configuration, current state, and a set of procedural constraints imposing additional restrictions on these procedures. For operations on NASA's International Space Station (ISS), these procedural constraints may be of several different types. Notes, Cautions, Warnings, and Inhibits are all relevant types of procedural constraints. Phase I of the Constraint-Checking Editor for Procedure Tracking (ConCEPT) established the feasibility of constructing a constraint-checking system for procedures represented in the Procedure Representation Language (PRL). Using automated translation and Constraint Satisfaction Problem (CSP) generation technologies developed on previous projects, ConCEPT assists users in identifying conflicts and inconsistencies in PRL procedures as they are developed. The user edits a PRL procedure in the Procedure Integrated Development Environment (PrIDE), using procedure steps that have been annotated with procedural constraints. As the procedure is being developed, ConCEPT automatically and continuously gathers appropriate procedural constraints and checks them against the procedure. ConCEPT then alerts the user to any violated constraints. Phase I defined relevant scenarios of use and established feasibility by demonstrating a proof-of-concept system to relevant NASA flight controllers.
Studies in ground-based analogs of Isolated and Confined Environments (ICE) have identified sensory monotony and social isolation as threats to crew psychological well-being.  Further, the lack of real-time communications in future missions will impact crew interactions with their support systems, i.e. family, friends, and colleagues, are critical.  ANSIBLE (A Network of Social Interactions for Bilateral Life Enhancement) leverages evidence based strategies to 1) augment asynchronous communications using Virtual Environments (VEs) and facilitate novel interaction methods beyond email, 2) use the inherently immersive and stimuli rich nature of VEs to counteract sensory monotony, and 3) leverages VEs and intelligent Virtual Agents (VAs) as companions and advisors to combat social monotony and detect changes in astronaut psychosocial states can increase astronaut self-awareness, suggest countermeasures, and provide rehearsal scenarios to maintain and enhance interpersonal skills.  Along with Dr. Morie, SIFT will leverage its prior work with human communication models and unobtrusive detection of psychosocial dimensions, to enhance VE and VA technologies. The resulting tool will advance  the future social landscape that connects the flight crew with Earth, and can be used pre, during, and post flight to connect crew and ground, providing a sense of social consistency and permanence.
Mass and volume efficient solar arrays are sought by NASA, DoD and commercial space to enable high power missions from 20-50 kW in the near term and eventually up to 350 kW. Currently, the maximum power available from conventional solar arrays, for a given spacecraft, is limited by either the weight or stowage volume of the honeycomb panel substrates. Flexible substrate arrays can enable higher power spacecraft by improving specific power (W/kg) and specific volume (kW/m3) as well as improving the deployed natural frequency. Typical designs for flexible substrate array require a stiff boom mechanism to deploy the array and provide the deployed structure. Heritage flexible substrate arrays have used metallic slit-tube or coilable longeron booms. To be feasible, large, next-generation flexible substrate solar arrays require deployable booms that are more thermally stable than metallic slit-tubes (STEMs), and less expensive and lighter than coilable longeron booms (i.e. AstroMast).  To address this need, CTD has developed the Stable Tubular Extendible Lock-Out Composite Boom (STELOC Boom).  The STELOC Boom can provide stiffness equivalent to coilable longeron booms with a significantly reduced volume, mass and cost.  The Phase I program demonstrated feasibility of the STELOC boom as the deployment actuator and primary structural component of a 15 kW solar array wing.  The proposed Phase II program will advance the STELOC Boom to TRL 5 through the design, fabrication and testing of a flight-like Engineering Development Unit.
U.S. space exploration missions have long considered returning to the Moon and exploration of Mars that challenge life support systems. For these long duration missions, NASA is interested in replacing the iodine water treatment system with ionic silver. Although iodine treated water has been used successfully with the International Space Station, its use requires that the iodine be removed before being consumed by astronauts due to its adverse effects on the thyroid. For long duration exploration missions, minimal mass systems are desired that lessen logistical supply requirements for storing and distributing potable water. In particular, it is imperative that an effective biocide is used that prevents microbial growth, biofilm formation, and microbially induced corrosion in the water storage and distribution systems. To address these needs, Reactive Innovations, LLC successfully demonstrated a Phase I program that developed an electrochemical silver ion generator to produce an effective biocide solution for disinfecting water throughout the water storage and distribution system. A follow-on Phase II program will further develop and optimize this cell and control system. This biocide delivery system will be demonstrated in a relevant environment showing its long life performance for preventing biofilm growth.
We propose to design, build, and test a sample acquisition drill weighing less than 1 kg. The drill uses a novel method of core or powder acquisition, and is suitable for both use by both robotic platforms and astronauts. The core acquisition bit can be used for either a rock core, icy-soil or loose regolith acquisition. The continued development of robust sample acquisition and handling tools is of critical importance to future robotic and human missions to Mars, the Moon, Asteroids, and other planetary bodies. For these missions, consolidated or unconsolidated core samples (as opposed to, say, scooped regolith or collected drill cuttings) are of particular interest. We will conduct testing in the laboratory and in the field to demonstrate the drill's effectiveness both in relevant environments, in relevant operational scenarios.
An improved efficiency amplifier for high power pulse applications at P-Band will be investigated that will support space based RADAR systems.  Current P-Band pulsed amplifier technologies use Silicon Bi-polar and LDMOS device technologies that have increased internal device parasitic characteristics that lead to lower gain and more difficult power matching over GaN technologies.  Integra Technologies has experience with all three device technologies.  Integra also has the design and manufacturing processes in place to optimize transistor design and amplifier design for P-Band pulsed applications.
	 The phase I effort resulted in successful demonstration of  an Integra GaN device at P-Band frequencies using Class AB bias and Switch Mode matching techniques to achieve greater than 80&#37; efficiency at 160W.     The phase II device investigation will include geometry modifications to optimize the operating voltage, chip size, and cell dimensions for the P-Band RADAR application. Ultimately, the optimized GaN device will be scaled into a 1kWatt output stage with an appropriate driver device to enable a greater than 40dB gain amplifier.  The amplifier will include material selections and layout techniques for reliability under high RF energy signal levels and low pressure environments.
In this STTR program, Structured Materials Industries (SMI) and partners propose to develop an electrically contacted zinc magnesium oxide (ZnMgO) nanowire array for highly efficient UV focal plane arrays.  The properties of ZnMgO make it a very promising material for optoelectronic devices.  In particular, the wide bandgap  (3.37 eV) and large exciton binding energy (60 meV), and the ability to fabricate stable, uniform ZnMgO nanowires make the material attractive as a sensor material.
Based upon the feasibility demonstrated in the Phase I research, Optimal Synthesis Inc.(OSI) proposes to develop a software tool that can be used validate aircraft flight deck user interfaces over the entire flight envelope. The approach is based on a mathematical formalism derived from hybrid systems theory. The correctness of information content in user interfaces is analyzed by a special observability test that takes into account of the limitations in human cognition and psychology. A possible mismatch between an operational mode perceived by the human operator and the one active in the aircraft is detected using an algorithm that compares the inferred intent of the human operator to that of the machine. Metrics-based performance evaluation will be carried out to demonstrate the benefits of the prototype software developed under the Phase II research.  The feasibility of employing the software on the flight deck as a real-time pilot aid will also be analyzed in the Phase II research.
The innovation is a high-frequency single-stage pulse tube cryocooler (PTC) that operates at a heat rejection temperature of 150 K. It employs a flexure-bearing cold compressor operating at that same heat rejection temperature. High frequency, low temperature pulse-tube cryocoolers are a promising technology for future NASA missions. Such missions will require cryocoolers providing cooling capacities in excess of 0.3 W at 35 K with heat rejection capability to temperature sinks as low as 150 K at input powers up to 20 W. Presently there are no cooling systems operating at this heat rejection temperature.
Icing is one of the most significant hazards to aircraft.  A sizing supercooled liquid water content (SSLWC) sonde is being developed to meet a directly related need for in-situ measurements of both total supercooled liquid water content and droplet size distribution.  This data will support the development of remote sensing instrumentation to detect icing conditions, support aircraft certification activities for flight into known icing conditions, and support the development of new icing-related operational weather forecast products.
	Phase I demonstrated the feasibility of the SSLWC sonde's measurement technique.  The sonde airframe was designed, built, and tested, mathematical models relating the sonde's raw data to the target variables were completed, a data processing algorithm was developed and implemented, and a proof-of-concept sonde was built.  
	Phase II will involve refining the sonde design, adapting the mathematical algorithms into their final application environments, conducting additional studies of sonde elements in an icing wind tunnel, and undertaking two field missions to obtain intercomparison data between the SSLWC sonde and other accepted approaches to such measurements.  At the end of Phase II, the SSLWC sonde will be proven to the point that it can be marketed with confidence for the application areas outlined above.
In this Phase I research, ZeCoat Corporation demonstrated a low-stress silicon cladding process for surface finishing large UVOIR mirrors. A polishable cladding is desired for SiC optics so they may be figured in less time, and so they may be polished to levels suitable for UVOIR astronomy.  ZeCoat has filed a provisional US patent application for the technology.  The proposed process is directly scalable to SiC mirrors several meters in diameter. The process is based on a novel, low temperature, ion-assisted, evaporation technique (IAD), whereby the coating stress of a silicon film may be manipulated from compressive to tensile, in order to produce a near-zero net stress for the complete layer. A Si cladding with little intrinsic stress is essential to allow thick coatings to be manufactured without cracking.  A low stress coating also minimizes substrate bending that would otherwise distort the figure of very lightweight mirrors.
Environmentally durable material systems capable of operating at temperatures from 1500 to 3000?C while maintaining structural integrity are enabling for future hot structure hypersonic vehicles.  State-of-the-art ceramic matrix composite CMC's and other established refractories lack stability at these high temperatures.  The plasma transferred arc (PTA) additive manufacturing (AM) process has demonstrated over 4000?C melt synthesis of select eutectic materials which have exhibited cyclic oxidation protection at 2600?C.  These novel materials will be further investigated as possible monoliths, graphite fiber reinforced and as a conformal coating on C-C components.  The PTA AM synthesized materials will be fully characterized to 3000?C for hypersonic vehicle applications with coupons delivered to NASA.
In October 2011, NASA initiated the Nuclear Cryogenic Propulsion Stage (NCPS) program to evaluate the feasibility and affordability of Nuclear Thermal Propulsion (NTP).  A critical aspect of the program is to develop a robust, stable nuclear fuel.  One of the nuclear fuel configurations currently being evaluated is a cermet-based material comprised of uranium dioxide (UO2) particles encased in a tungsten matrix (W).  To prevent excessive fuel loss from reaction with the hot hydrogen gas and uranium hydride formation, dense, fine-grained tungsten claddings are needed.  Recently, advanced additive manufacturing techniques (EL-Form and Vacuum Plasma Spray Forming) have been developed that enable the deposition of coatings and near-net-shape refractory metal components with high density and tailored microstructures.  The Phase I investigation produced fine-grained W claddings using EL-Form and VPS processing techniques.  Testing showed the W claddings were well bonded to surrogate nuclear fuel element materials, and the W claddings were vacuum tight.  During Phase II, the techniques developed during Phase I will be optimized, and W claddings on full size cermet fuel elements will be developed and characterized.  Subscale and full-size test articles will be produced and delivered to NASA-MSFC for hot hydrogen testing in the Compact Fuel Element Environment Test (CFEET) facility and the Nuclear Thermal Rocket Element Environment Simulator (NTREES).
The key innovation in this project is the implementation of an Imaging Fourier Transform Spectrometer (IFTS) for in situ metal additive manufacturing process monitoring. In this Phase I STTR project, Mound Laser &amp; Photonics Center, a developer of laser based additive manufacturing processing, will collaborate with the Air Force Institute of Technology, with expertise and innovative hardware for spectroscopy, to implement the IFTS in a Selective Laser Melting (SLM) R&amp;D test bed to demonstrate advanced strategies for process control and in situ quality assurance such as: (1) automatic detection of the molten area in various layers, (2) in situ release of stresses induced by temperature gradients, and (3) real-time control of alloy composition and minimization of contaminants.  These capabilities with facilitate the manufacture of parts with complex geometries with improved microstructures and properties.

In Phase I we intend to: (1) prove the utility of the IFTS for monitoring SLM processing of metals and alloys, (2) determine surface temperatures with a statistical accuracy of better than 4 oC, systematic accuracy of better than 10 oC and a dynamic range of up to 2000 oC, and provide rapid (1 kHz), automatic identification of the molten area, (3) track changes in chemical composition due to evaporation, oxidation, and melt expulsion, (4) reduce data  dimensionality and correlate these IFTS sensor features with manufacture quality metrics, and (5) design the concept for a Phase II prototype sensor suite that focuses on key aspects of the IFTS datascape to inexpensively emulate the IFTS.  In Phase II, a prototype optical sensor will be developed for process control  of metallic additive manufacture of lightweight, reliable, low cost structures.
The NASA Science Missions Directorate seeks technology for cost-effective high-performance advanced space telescopes for astrophysics and Earth science applications. These applications require instruments with large aperture light-weight highly reflecting mirrors and precision optical surfaces to gain a better understanding of how the universe works. The hard and soft X-ray mirrors have stringent surface requirements.  If awarded a Phase I our plan would be to combine previous knowledge of OptiPro's UltraSurf metrology system with newly developed software. Our goal would be to create a robust solution for combining the measurement data of the mirrors with corrective machine grinding and polishing process toolpaths.  This proposal includes the investigation utilizing non-contact probes on OptiPro's machining platforms to quantify the potential opportunities for in-situ mirror measurements.  Understanding these surface irregularities and what in the manufacturing processes causes them is critical for improving the current TRL's. OptiPro Systems will develop a metrology system and software, that would provide feedback for manufacturing these precision mirrors and include final metrology measurement of global form error and mid-spatial content. Comparison of in-situ and off-line metrology will be key for improving the manufacturing processes. We envision that the work performed in Phase I would lead to a software and metrology solution to be built and delivered to NASA if awarded a Phase II.  OptiPro's technologically advanced optical manufacturing capabilities along with our support partnership with the University of Rochester Mechanical Engineering Department, gives us a very strong team and a clear path towards solving the difficult challenges for measuring these large complex mirrors and cylindrical shells. Our goal is to provide an innovative and complete manufacturing solution for the companies that are fabricating these optical components for NASA.
Project involves development of new flexible FR polyurethane (PU)insulation foams through a non-toxic environmentally friendly composite approach.  Foams have bound-in polymeric phosphonate FRs, with added synergists and smoke suppressants. Such foams will not leach FR. Foams have fine cell structure and excellent flexible foam properties.

Cone performance of the identified foam family (368 peak rate of heat release versus 1670 control - 78&#37; reduction in PHRR) clearly surpasses that of standard commercial flexible PU foams: 502 to 913 for CAL 133 compliant foams, 953 for BS5852 compliant foam, and 1154 for CAL 117 compliant PU foam.  Project foams easily comply with NASA 6001 open flame testing. Foams with under 3.0 pcf are available. Procedures for incorporation of significant Aerogel concentrations (5 pbw to 15 pbw), useful for cryogenic and low temperature insulation, have been identified and tested.  Results are based on over 200 foams made in small scale and 100 foams prepared as 5L molded foams. 

Phase II of Project involves scale-up of foams in the foam family, preparation of intermediate scale samples capable of more detailed application testing, performing such testing (Eg. cryogenic insulation testing),  and sampling of foams to potential customers identified by the project expert Commercialization Panel.  In working with foam vendors on intermediate scale sample preparation, potential commercial partners will be identified and assessed.  Large scale runs are also planned. Potential commercial partners will have the opportunity to gain experience with the foams in intermediate scale sample preparation.  Selected partners will have the opportunity to share their experience with the Commercialization Panel to focus on highest value applications and needed performance.  Such interaction will lead to partnering, licensing and joint venture discussions.
Despite the rapid commercialization of additive manufacturing technology such as selective laser melting, SLM, there are gaps in process modeling and material property prediction that contribute to slow and costly process qualification and product certification. To address these gaps, CFDRC and our partner Dr. Kevin Chou, University of Alabama, will develop multiple computationally efficient, high-fidelity simulation tools for the SLM process.  During Phase I the team will apply adaptive meshing to enable efficient thermomechanical simulations for centimeter size test coupon builds, leverage existing multiphase flow models to analyze particle size effects on material variations, apply phase field models to predict microstructure evolution, and evaluate model predictions against experimental characterization.  During Phase II, the modeling tools will be extended to improve computational efficiency and scalability to aerospace component dimensions by further leveraging parallel computing and other acceleration techniques.  The fidelity of the models will be enhanced to better predict distortion, residual stress, microstructure and defects from process conditions; and additional process data will be used to validate the resulting codes.  The resulting toolset will be capable of efficiently predicting these dimensional and microstructural properties of SLM components from process conditions, while addressing important design and build features such as overhanging sections and build supports.  The high-fidelity, physics based nature of the codes will allow straightforward application to new materials, and to guiding development of and verifying analytical physics models for process control.
In Phase II, Roccor proposes to build upon the results of Phase I to increase the technology readiness level (TRL) of the NASA JPL deployable external occulter.  An occulter, which is a satellite flying far from a telescope and employing a large screen or, starshade, to suppress the incoming starlight, is used for detecting and characterizing exoplanets.  Detecting Earthlike planets existing within the habitable zones of nearby stars is a key element of NASA's space exploration mission.  The NASA JPL starshade incorporates a deployable center ring-truss as a hub and flower-like petals that wrap around the hub for packaging.  As a result, it exhibits exceptionally challenging deployment kinematics.  Roccor's Phase II will contribute to maturing the design of the NASA JPL deployable starshade through system and component design and analysis and supporting ground-demo hardware thereby helping to position it for spaceflight should it be transitioned to a NASA flight mission.Roccor's broad Phase II focus is on maturing each of the deployable starshade system elements that support the petals including the unfurling control system, the launch control system, and the deployed strut system.  Innovative solutions have been conceptualized for each of these petal support functions as part the Phase I program.  
In Phase II, Roccor will emphasize developing and demonstrating the proposed petal unfurling technology culminating in a 1/3 scale fully functional and motorized hardware demonstration with 30 petal simulators, 3 of them being instrumented and strength-representative (e.g. fragile and narrow petal tips). Roccor will also further develop the launch control system and deployed strut-support system through extensive design and analysis.
HJ Science &amp; Technology proposes a programmable, low-cost, and compact microfluidic platform capable of running automated end-to-end processes and optimization of cellular engineering and synthetic biology applications.  In collaboration with Lawrence Berkeley National Laboratory and the Joint Genome Institute, we will establish the feasibility of the proposed microfluidic automation technology by engineering and screening cyanobacterial cells for enhanced production of free fatty acids (FFA), a metabolic crossroad for the synthesis of a suite of useful organic molecules including lipids, alkanes, and potential biofuels starting from carbon dioxide, a metabolic waste product. The ability to perform such automated synthetic biology experiments during NASA missions could enable the production of a broad range of materials on site, and optimization of bioregenerative systems in response to environmental changes. We will demonstrate the microfluidic automation capability for each of the key steps in cellular engineering: 1) construction of a plasmid containing genes for enhanced FFA production in cyanobacteria, 2) subsequent transformation into cyanobacterial cells/chromosomal integration, and 3) screening of expression products.  As such, we can assess the FFA levels as a function of the gene variant in almost real time, thereby greatly enhancing our ability to control and optimize FFA production.
TBD
Our aim in this project is to apply the state-of-the-art in science autonomy, including the PI's recent work at Carnegie Mellon in areas of automatic spectrometer targeting and spectra collection, science-guided path planning, and orbital terrain classification, to the creation of Intelligent Spectrometry for Robotic Explorers (ISRE). In our vision, ISRE will enable real-time, on-board analysis of spectroscopic data to guide spectrometer targeting. Spectrometer targeting involves both selecting rover navigational goals and directing a spectrometer foreoptic to accurately measure intended target rocks or soil. The expected result is that the most informative science targets will be automatically sampled and that quality of the science data return will improve while the required scientist effort and necessary communication bandwidth will be reduced. 

ISRE will employ algorithms to segment images into spectrally-similar regions using feature extraction and classification. These regions can be targeted for spectrometry and experiment-design techniques will be applied to determine the best sampling strategy for coverage and signal maximization without resource wasting oversampling.

The rover-collected spectra can then be unmixed into endmembers that can be associated with orbital observations or geologically interpreted by scientists. Classified spectra can be aggregated into maps, used to detect spectral distinctions including outliers, and interpreted to plan spacecraft actions more likely to produce informative results.

Our specific innovations are: feature extraction for image segmentation and spectral clustering; discovering exceptional (outlier) spectra, which may have significant scientific value; associating spectral endmembers with geologic terrain; rover path planning for science sample collection; and integration of algorithms into an open-source framework.
Communication technologies support all NASA space missions, among which autonomous communication technologies are extremely beneficial to future missions. Communication technologies will expand mankind's understanding of planet earth and the universe. As the needs to gather more data, even more advanced antenna technologies will be essential to deliver orders of magnitude more data. Low cost high data-rate flexible active digital beam forming phased array antenna (PAA) is one of the enabling technologies. Graphene is one-atom-thick planar sheet of carbon atoms that has mobility of charge carriers in excess of 200,000 cm2V&amp;#8722;1s&amp;#8722;1. It is the lowest resistivity substance known at room temperature. The extremely low resistivity makes graphene the next generation conductor that we are going to use as interconnects and antenna elements. Graphene also has supreme mechanical properties extremely suitable for flexible electronics. It is lighter, stronger, harder and more flexible than steel. Furthermore, it is a recyclable and sustainably manufacturable product that is eco-friendly. Another advantage of graphene antennas is that due to the reduced wave propagation speed of graphene, the size of antenna can be reduced to a factor of 10, which is critical for the routing and power dissipation for large number element arrays.  

Prototype of a fully graphene-based 4-bit 4-element digital beam forming PAA on flexible substrate such as Kapton, including antennas, field effect transistor (FET) switches and phase shifters will be developed. Performance features of the flexible PAA will be characterized including frequency/bandwidth, gain/efficiency, and power consumption. The flexible high-speed electronics will enable active PAA deployment for NASA's lunar mission, including pressurized rovers, pressurized habitats, surface navigation, EVA, and etc.
To support NASA's vital interest in developing much larger solar array structures over the next 20 years, MotionPort LLC's Phase I SBIR project will strengthen validated modeling analysis and simulation techniques by developing a vertical application to simulate the nonlinear dynamics of the various stages of deployable space structures.  This application which will support RecurDyn Multi-Body Dynamics (MBD) software, acquired by NASA in 2013, will increase efficiency and reduce errors, time and the need for advanced knowledge.  Currently, modeling complex flexible body non-linear structures can be time consuming and prone to error. Existing nonlinear structural analysis simulation software does not effectively simulate structural assemblies with significant motion. Creation of a custom vertical application for the simulation of deployable space structures would provide a large reduction in the specialized knowledge needed to develop models and would automate tedious tasks. 
  The proposed innovations of this Phase I SBIR project are:
  1. A focused vertical software application for the dynamic simulation of the rollup, deployment and maneuvering operation of large solar array structures consisting of a set of functions that are layered on commercial Multi-Body Dynamics (MBD) simulation software that also has the capability of the nonlinear simulation of flexible (Finite-Element [FE] or mesh-based) bodies; and
  2. Development of an active, nonlinear controller that will reduce the deflection of a roll-out solar array (ROSA) during spacecraft maneuvers. This development includes the creation and use of a unique simulation environment that couples the controller simulation with the nonlinear structural response of the ROSA.
  The Phase II project will add capabilities and improve integration of functions, including new support of the simulation of lanyards and tape springs. Additional type of deployable space structures can be simulated, including antennas.
This Phase 2 program builds on a successful Phase 1 effort that demonstrated practical engineering methods as well as continuing development paths to build smaller high performance gyro systems suitable for small satellite applications.  This program will execute a logical follow-on endeavor by (a) using existing components that satisfy the specifications matrix, and (b) developing new components that are required to complete the task of fabricating small optical gyro heads.  We have clearly defined tasks and realistic milestones with risk management embedded.  Designed to fit within a 1U satellite chassis to adapt to the growing cube sat application space, a clear plan has been laid out to generate an IRU system that addresses deployment issues such as mass, harness routing, and 3-axis cluster versus split head configurations.  The gyro design is a keen compromise between leveraging shorter wavelength subcomponents to improve performance naturally, smaller mechanical size to minimize thermal effects, and optoelectronics placement options for form factor flexibility.  We recognize power management as the critical parameter for devices within small satellites, therefore an effort has been allocated to develop a solution concept for miniaturized and power-efficient control electronics to address the goal of &lt;2W consumption, although its implementation is beyond the scope of this Phase 2 program.
The LCCE-2 Program builds off the successes of the USAF "Low Cost Cryocooler Electronics for Space Missions" Program, extending the performance of the developed LCCE to include active vibration cancellation and advanced input power bus circuitry. The former is important for imaging payloads because the exported vibration from the cryocooler can be a major contributor to the overall image jitter. The latter will provide the ability to safely operate the cryocooler system off of virtually any spacecraft power bus from all perspectives, meaning that the cryocooler system will be protected from transient effects from a "dirty bus," and the cryocooler will not impart back onto the power bus large amplitude current ripple that would otherwise affect the performance of other devices on the bus.
Deployable Space Systems, Inc. (DSS), in collaboration with the University of California, Santa Barbara (UCSB), Department of Mechanical Engineering, will focus the proposed NASA STTR Phase 2 program on the materials optimization, structures optimization, creep / relaxation phenomena characterization and analytical modeling, and manufacturing process optimization/development for the Mega-ROSA/ROSA solar array. The ROSA technology (termed for: Roll-Out Solar Array) is a new/innovative mission-enabling solar array system that offers maximum performance in all key metrics and unparalleled affordability for NASA's Space Science &amp; Exploration missions. ROSA will enable NASA's emerging Solar Electric Propulsion (SEP) Space Science &amp; Exploration missions through its ultra-affordability, ultra-lightweight, ultra-compact stowage volume, high strength/stiffness, and its high voltage and high/low temperature operation capability within many environments. Multiple identified end-users provide strong commercial infusion paths for the ROSA solar array upon the successful execution of the proposed Phase 2 program technology advancements.
Our proposed innovation is a robust manufacturing process for free-form optical surfaces with limited mid-spatial frequency (MSF) irregularity error. NASA and many others have a direct and critical need for high quality free-form optical components. Free-forms can improve the optical performance of many types of optical systems when compared to aspheres.    MSF error is a major concern with free-form optics as the standard method for manufacturing free-forms (sub-aperture tool polishing) can lead directly to large MSF error. Simply, MSF error is a height error on the surface in the spatial regime between roughness (micro) and irregularity (macro). MSF errors dramatically degrade performance in optical systems.    Our free-form manufacturing process is differentiated by full-aperture polishing step, called VIBE, and by the proposed smoothing step. The VIBE step does not create MSF error as the sub-aperture process does. The smoothing step will reduce any inherent MSF error. In this manner, we will manufacture free-form optical surfaces without MSF errors.     Our technical objectives are three fold: 1) Determine most feasible smoothing parameters, 2) Determine feasibility of smoothing for free-forms for reduced mid-spatial frequency error, and 3)Determine the effectiveness of using a computer generated hologram (CGH)  for free-form measurements.     To accomplish these objectives we have set out the following work plan. First we will design the free-form surface and the associated CGH (with feature for easy alignment).  Next, we will perform a study on smoothing to determine the optimized smoothing parameters to remove mid-spatial frequency errors on free-form surfaces. Then, we will manufacture precision free-form surfaces using the optimized parameters. During each step in the manufacturing process (generation, VIBE polishing, smoothing, sub-aperture figure correction, and something) we evaluate both the irregularity and mid-spatial frequency errors.
The use of lithium (Li) metal as an anode material has emerged as one highly attractive option for achieving high specific energy due to lithium having the highest capacity (3876 mAh g-1) of all potential anode materials.  However, the reliable use of these exceptionally high capacity anodes in a commercial cell has not been achieved due to safety and reliability concerns resulting from thermal runaway and short-circuit issues due to dendritic growth on the metal anode from lithium plating during charge-discharge cycles.  Solid-state electrolytes (SSE) have been identified as one option to address this cell failure mode, but SSE technologies must be developed that combine high conductivity and mechanical properties conducive to smooth Li plating with feasible manufacturing processes.  Also, the Li anode must be combined with an ultra-high capacity cathode in order to reach NASA's aggressive cell-level energy goals.

To address this need, Solid Power proposes to utilize a Li-metal-compatible solid-state battery design to far exceed the specific energies achieved by state-of-the-art (SOTA) Li-ion batteries in a format that also provides for intrinsic safety and abuse tolerance. Phase I will demonstrate the feasibility of surpassing 600 Wh/kg and 1000 Wh/L at the cell level which will give a 3-5X improvement over the best battery technologies planned for NASA missions today.
A thermophotovoltaic (TPV) system is a promising energy conversion device that generates the electric power from short wave infrared (SWIR) thermal radiation. However, it's low power throughput and poor conversion efficiency restricts the usage in practical applications.  One solution for resolving these issues is to utilize a metamaterial emitter whose thermal emission band is spectrally matched to the energy conversion band of the TPV cell.   However, typical frequency selective emitters (SE) emit only in a narrow frequency band, limiting the total power throughput of the TPV system.  This proposal thus aims to experimentally investigate wideband metamaterial emitters, whose emission band is spectrally matched and utilizes the entire energy conversion band of the TPV cell.  The innovative aspects of the proposed research are (1) to develop robust electromagnetic numerical simulation capabilities that incorporate experimentally measured material properties as a function of frequency, and device operation temperature into the design of the metamaterial emitter; (2) incorporate novel metal-nitride materials into the metamaterial structure, enabling optical property tunability through stoichiometric control, and wideband, spectrally matched thermal emission; (3) to fabricate and characterize a metamaterial emitter whose thermal emission band is spectrally matched to the energy conversion band of the target TPV cell. By improving not only the overall efficiency of TPV converters, but importantly the total power throughput, this technology will enable more efficient, compact electrical energy sources for a range of applications, which include power sources for rural and remote locations, solar power generation, waste heat recovery, and power sources for deep space exploration.
We have all seen people carrying portable oxygen tanks or concentrators to provide critical life support respiratory oxygen. Heavy, bulky, and for O2 concentrators, noisy, there clearly is an opportunity to improve the delivery of oxygen to the millions of users requiring oxygen therapy. This program affords us an opportunity to develop and demonstrate a noiseless, portable medical oxygen concentrator that can serve a large terrestrial market as well as future NASA exploration missions that need emergency oxygen for various medical scenarios. This product aims to improve the three largest user complaints with existing portable O2 concentrators, namely, that the systems are too heavy, too noisy, and they are too bulky restricting mobility. Reactive's medical oxygen concentrator will provide improved mobility for people that require O2 respiratory therapy enhancing the quality of their life.
Flexible photovoltaic array technologies require very thin and precisely controlled deposition of the polymeric films used to fabricate them. In most flexible blanket architectures, optically transparent silicones are utilized in the fabrication of the arrays, however due to their rheology and processing conditions there are limitations to how thin they can be applied. In this proposal, Vanguard proposes Thin and Automated Blanket Lamination and Encapsulation Systems (TABLES) that utilize automated drawdown methods and rheology control to render flexible blankets approaching 700 W/kg and only 13 mils thick (including cells). Further, the TABLES concept is easily adapted to a number of substrates and superstrates, rendering "LEO to GEO" packaging and automation simply through appropriate substrate choice.
The next generation of space systems can benefit greatly by reduced c-SWaP integrated gyroscopes. By using photonic integration, it is possible to fit the entire gyro onto a single chip and inside a package &lt;10 cm3, weighing &lt; 50 g, and consuming &lt;1 W of power. Furthermore, the fabrication of such chip-scale solutions reduces the cost per unit dramatically as ~thousands of optical gyroscopes can be made on each wafer and assembled using mature high-throughput semiconductor technology.  

Freedom Photonics has developed advanced photonic integrated circuit (PIC) and planar lightwave circuit (PLC) capabilities to realize this device.  By leveraging our technology, we can delivery &lt;0.05 deg/hr sensitivity optical gyroscopes with 10x lower weight, volume, and cost. These gyroscopes will have few components, require minimal assemble, and have no moving parts. The highly integrated devices are more resilient to shock and vibration, and can have longer gyroscope lifetimes with fewer component failures.       

In Phase I of this program, Freedom Photonics will determine the feasibility of meeting space-grade gyroscope specifications with a low c-SWaP solution leveraging our proprietary, commercially deployed photonic integrated circuit (PIC) technology. A hardware benchtop demonstration will be included.
Silicon Carbide based ceramic matrix composites (CMCs) offer the potential to fundamentally change the design and manufacture of aeronautical and space propulsion systems to significantly increase performance and fuel efficiency over current metal-based designs.  Physical Sciences Inc. (PSI) and our team members at the University of California Santa Barbara (UCSB) will develop, design and fabricate enhanced SiC-based matrices capable of long term operation at 2750 F to 3000 F in the combustion environment.  Our approach will build upon PSI's and UCSB's previously successful work in incorporating refractory and rare earth species into the SiC matrix to increase the CMC use temperatures and life-time capabilities by improving the protective oxide passivation layer that forms during use. As part of this work we will create physics based-materials and process models that qualitatively define methods of improving matrix properties and the interaction of the fibers, interphases and matrix with each other.

In the Phase I program the PSI team will focus on performing experiments and develop models predicting the effect of phase distribution, grain size, chemical composition, matrix density, and surface flaws on the oxidation behavior of the CMC matrix.  During the Phase II program we will iteratively improve the CMC performance by optimizing the composition and characteristics of the additives based on oxidation and mechanical test results.
During Phase I, Aurora Flight Sciences and the University of Massachusetts Lowell propose to demonstrate the feasibility of enhancing a commercially available out-of-autoclave (OOA) carbon prepreg material system (e.g. IM7/5320) via embedded structural health monitoring (SHM) and self-healing capabilities, which can be manufactured by an automated fiber placement (AFP) machine.  This proposed "smart" material will ultimately enable the cost-effective manufacture of large, lightweight core-stiffened composite cryogenic pressure vessels.  Carbon nanotubes (CNTs) will be transferred either directly onto the prepreg, or onto adhesive film plies that are subsequently laminated with the prepreg material.  Electrical conductivity measurements via the CNTs will provide embedded SHM capabilities, while localized Joule heating will accelerate self-healing polymerization reactions. The CNT-enhanced prepreg will also serve as a carrier layer to embed well-dispersed self-healing micro-/nano-capsules within the polymer matrix and which will allow for self-healing of microcracks resulting from impact damage and thermal cycling.  Self-healing efficiency will be characterized via mechanical testing. This smart material will ultimately be produced in spools of half-inch wide unidirectional prepreg slit tape, and laid down using Aurora's 7-axis, 16-spool automated fiber placement (AFP) machine. Trade studies will be performed on the AFP machine to determine the optimal processing parameters for laying down the smart material. The targeted demonstrator structure, a "smart" cryogenic pressure vessel, will detect microcracks caused by incident impact damage and rapidly repair the damage in situ.
NanoSonic has recently developed multifunctional shielding and self-healing HybridSil&amp;#63720; (HS) smart composites via the inclusion of innovative nanoshell inclusions.  These lightweight yet high-strength rapidly self-healing materials combined with NanoSonic's Metal Rubber&amp;#153; (MR) shielding nano-additives and are offered herein as protection systems for NASA vehicles, habitat modules, and pressure vessel structures.  The conductive aspect of Metal Rubber also enables damage detection.  This technology may overcome the current bottleneck of damage tolerance for current composites that form nearly undetectable cracks upon impact that impart drastic effects on the structural survivability.  HS-MR self-healing composites offer both self-healing and damage detection, as well as the added functionality of very high levels of electromagnetic shielding effectiveness (EMI SE) without the need for additional heavy layers.  MR exhibits EMI SE of greater than -100 dB upon exposure to a blow torch, repeated cold flexing at -50 ?C, and irradiation under a 60Co source.  During Phase I, TRL 5 shall be reached upon demonstration of damage tolerant, self-healing structural composites with assistance from our radiation expert STTR partner, CSU, and commercial space partner.  During Phase II, TRL 7 shall be achieved upon demonstrated damage detection and self-healing in a representative flight environment with our defense prime partner.
New measurement technologies are required to support science campaigns to better quantify rapid loss of permanent floating ice volume in the Arctic Ocean, accelerating loss of the Greenland glacial system, recurring drought conditions in the U. S. continental interior, and increasing frequency and intensity of severe storms in both coastal zones and in the nation's central corridor. While balloon measurements offer persistence and relative low cost when compared to aircraft systems, they lack the ability to reposition, station-keep, or navigate along or across observed gradients. Similarly, aircraft offer the ability to target regional phenomenon, reposition, and navigate to areas of interest but are costly to operate and lack the persistence of balloons. The StratoCruiser balloon gondola concept offers unprecedented mobility and the reel-down payload support for executing unique in-situ studies of large-scale convective events. Combining the persistence of balloon platforms, the vertical measurements of soundings, and the mobility of aircraft the StratoCruiser will enable new understanding of stratospheric phenomenon. The StratoCruiser carries the unique Harvard&amp;#150;designed reel-down payload and winch system. The winch allows the suspended payload to be lowered from a vehicle at rates of 5-10 m/s up to a distance of 10 km. These soundings provide in situ detection of radicals, isotopes, ozone, reactive intermediates, long-lived tracers and condensed and vapor phase H2O and HDO.
High power solar arrays with capabilities of &gt;100kW are needed for projected NASA missions.  Photovoltaic arrays using deployable membranes with thin cells have trended to higher efficiency cells to minimize deployed area and deployment structure mass and complexity, however, the cost of high efficiency cells make these arrays prohibitively expensive.  Amorphous cells that are in production for terrestrial application have $/Watt cost less than 10&#37; of space cells, at about the half the efficiency.   This SBIR develops the Photovoltaic Assembly with Reconfigurable Array Structure - PARASol - a centripetal force deployment and tensioning approach that enables affordability of multi-100kW arrays with commercially available thin film CIGS cells, which can be adapted for space environment compatibility.  PARASol implements CIGS cell modules using Vanguard's THINS solar cell encapsulation technology to achieve high mass and stowed volume metrics (&gt;500W/kg, &gt;200kW/m3), and mount the CIGS-THINS modules onto a Membrane Solar Array (MSA) that can be rolled and folded into a compact envelope and deployed without cumbersome external deployment structure.  In phase I we will develop the design and structural analysis of a 250kW PARASol MSA, selecting from flower-, umbrella-, or origami-like deployments, and evaluate figures of merit for the array when implemented with a combination of centripetal force and elastic or shape-memory integral ribs to deploy and tension the array. We will evaluate the alternative gore sizes and shapes to determine the maximum PV packing factor we can achieve.  We will develop a plan for scaling up the technology and qualifying for space, addressing the key challenge of demonstrating and characterizing such a large array in ground-test with gravity off-loader.  The Phase I completes with a subscale demonstration using a scalable version of the test fixture, leading to a plan forward towards flight experiment in Phase II.
The prevalence of off earth landing missions both proposed and undertaken has been steadily increasing. With the proposal of missions, not only to Mars, but also to comets, asteroids and outer planet moons, the ruggedness and robustness of equipment must meet the challenges of ever harsher environments. As a part of these missions, researchers wish to analyze the materials which make up the surface of these bodies and search for organic material. Brimrose proposes to develop a novel, compact, fast spectropolarimeter that will be capable of operating in the short wave infrared. The analysis of polarized light can help discriminate and classify materials and identify objects of. Measurement of polarization state can also provide various characteristics such as surface properties, shape, shading, and roughness, and can be used to identify unique features that will allow more accurate discrimination between various materials than spectral data alone. Development of space-ready hardware and algorithms for the detection and analysis of polarized light in space based analysis applications is needed to enable high confidence material discrimination. The development of proposed full-scope spectropolarimeter will offer a dramatically improved optical solution for material analysis by performing fast spectral profile acquisition with an additional feature of complete polarization information.
The role of UASs in the DoD has been continuously growing and is expected to show much higher growth rates in operations in the near future. A pressing need for such platforms is the need to be able to satisfy multiple mission objectives, without "compromising" on efficiency. This need is further exacerbated by increasing fuel prices, that dictates higher aerodynamic efficiencies across the complete mission. Variable geometry aircraft, inspired by biological examples of high efficiency, are a natural choice for achieving this goal. This has become a particularly lucrative option with advances in smart materials and structures. However, there is much to be done in terms of actuation development and stable robust control to make such a concept practically feasible. To address this need, Intelligent Automation proposes an inflatable morphing wing aircraft concept based on pneumatic actuation mechanism to achieve several types of morphing. We also propose to develop novel adaptive control techniques that are provably stable in spite of transitions and aeroservoelastic interactions. These will be developed and demonstrated in flight tests to assure credibility of propose approach and enable rapid transition.
The technical innovation proposed here expands upon early research into the viability of additive machining (AM) for liquid rocket engine components and other emerging capabilities to initiate TRL 6 flight test evaluations of candidate applications that could enhance the affordability of a small launch vehicle (SLV) booster stage.  

University of California, San Diego (USCD) has achieved success in applying  3D AM to fabricate a 200 lbf-thrust LOX/kerosene engine.  Concurrently, the Garvey Spacecraft Corporation (GSC) team continues to make progress in the development and flight testing of key elements for a future low-cost nanosat launch vehicle (NLV).  These NASA-sponsored NLV designs, concept of operations (CONOPS) and cost metrics based on actual flight operations now serve as references for evaluating emerging technologies like UCSD's AM engine(s) to implement an SLV first  stage that achieves the aggressive cost, performance and sizing goals specified in the T1.02  subtopic description.  This is exactly the same approach that was followed under a previous NASA STTR that successfully demonstrated a TRL 6 for an advanced CMC-lined ablative engine chamber.  Phase I flight testing features a subscale host vehicle, while Phase II then follows with an SLV-scale prototype booster.
Busek and University of Utah propose to develop novel metal organic framework (MOF) material to efficiently capture oxygen in spacecraft cabin environment. The proposed novel MOF is postulated to be capable of separating oxygen from ambient air with high efficiency, and at the same time, be stable to moisture and resistant to decomposition. In Phase I, our team shall synthesize the proposed MOF and a MOF of known oxygen capture capability as the benchmark. The MOFs will be tested for their oxygen capture capability, gas selectivity, and reversibility.  The effects of water on capture capability will also be examined. The physical measurements will guide the syntheses.  At the end of Phase I, a preliminary sub-scale proof of concept will be explored for configuration optimization with relevant air flows.  In Phase II, we shall validate the subscale proof-of-concept device and further scale up toward a prototype MOF-based O2 capture system.
A significant technology gap for NASA astrobiology missions is the detection of organics at the sub ppm level without sampling.  Currently, NASA uses different sensing technologies such as Pyrolysis&amp;#150;GCMS to analyze planetary samples. These instruments require complex sample handling and can process only a limited number of samples.  It is critical to develop an effective instrument with extended and enhanced capabilities to enable future planetary multiple-mission needs. We propose to develop a new nonlinear Raman spectral sensing technology for trace organic detection at the sub ppm level.  The proposed technology will provide significantly increased sensitivity based on nonlinear Raman detection with Surface enhanced Raman scattering (SERS). It eliminates the sample preparation process, contamination and other related accessories. Our test samples will be soils from the Mojave, and Antarctic Dry Valley deserts which have measured organic concentrations of 10 to 250 ppm. We will mix unaltered soils with organics removed soils.  The detection of organics at the sub ppm level without sampling will be applicable to several future NASA missions, in particular future rovers for the upcoming Mars 2020 mission.   These mobile, fast and agile rovers are focused on collection for sample return and require non-sampling analytical instruments.
The small size of Unmanned Aerial Vehicle (UAV) platforms along with the need to reduce drag to increase flight time creates a need for low-profile antennas.  The oldest solution, a mechanically steered parabolic reflector, does not provide a low profile.  The modern electronically steered phased array is an alternative that does provide a low-profile antenna solution, but the cost of these antennas has prevented wider use.  Hybrid antenna solutions that are partly mechanically steered and partly electronically steered are an approach to maintain the low profile of a phase array at much lower cost.  Although existing hybrid solutions offer potential, there have been limitations in scan speed and Field-of-View (FOV).
FIRST RF has demonstrated the initial proof-of-concept capability of an innovative low-profile hybrid scan phased array antenna that reduces cost by nearly an order of magnitude relative to a conventional phased array for low profile applications and removes the limitations of previous designs in scanning and FOV.  This approach uses small mechanical actuators to reduce the parts count of the active components in the electronic steering portion of the aperture.  Unlike other hybrid scan solutions, which have asymmetrical fast and slow steering, this approach provides symmetrical fast electronic steering at angles near boresite with slower mechanical steering for large off-boresite angles.  The scan loss of this approach is actually lower than for fully electronic scanned phased array antennas, and the FOV is greater.  This technology is applicable for Unmanned Aircraft Systems (UAS) applications.
ProtoInnovations, LLC (PI) and the Massachusetts Institute of Technology (MIT) have formed a partnership to research, develop, and experimentally test a suite of methods for significantly improving the safety, mean travel speed, and rough-terrain access of wheeled planetary exploration rovers. We will accomplish this by developing algorithms for all-terrain adaptive locomotion. This will include algorithms for:
1.	Traction control, which will intelligently govern individual wheel commands as a function of terrain conditions in order to measurably decrease wheel slip; and,
2.	Embedding detection, which monitors the rover's inertial signature to rapidly and robustly detect instances of incipient embedding in soft, low bearing-strength regolith.
Our aim is to provide a novel approach for enhancing rover traction and reducing slip that will not only allow rovers to autonomously detect and avoid hazardous terrain regions, but also to travel with assured safety on terrain that is steeper and rougher than is currently possible. 
The result of this work will be systems that can rove with a reduced risk of catastrophic failure, while simultaneously increasing both the quantity and potential quality of science data products.  This latter capability is enabled by the fact that rovers will be able to travel for long durations without requiring lengthy human interventions, and will be able to travel to sites of greater scientific interest (and proportionally greater mobility difficulty) than what is possible today.
AxNano proposes a novel method for producing robust, high-volume, cost-effective carbon fibers in support of next-generation materials for structural composite space applications. AxNano will utilize a needle-less electrospinning method to form precise bundles of nano-fibers. The spinning and draw method will be designed to achieve the structural perfection needed for leaps in mechanical strength and stability of carbon fibers. This proposed work effort will establish an advanced manufacturing process, controlled at the nano/molecular scale.  Efficacy will be shown by producing articles at the coupon scale, which are expected to possess better mechanical properties - double those for current epoxy CFRP technology.  This new continuous carbon nano-fiber (CNF) manufacturing process will produce CNFs with reduced defects, increased uniformity, and much higher strength. This project aims at innovative nanomaterial based polymeric composites with potential to supplant conventional carbon fiber reinforced polymeric (CFRP) composites as lightweight aerospace structural materials for space applications.  Specifically the project addresses fundamental challenges in mass-manufacturing continuous and high-strength carbon nanofiber yarns, weaves and next-generation carbon nanofiber yarn-reinforced polymeric composites (CNFYRP).
XABC (Xerion Advanced Battery Corp) proposes a novel anode with three unique features, each designed to 1) control or 2) prevent dendrite growth. The first feature is a 95&#37; porous electrode architecture. This electrode is an open-cell, nanostructured conductive foam whose internal structures are conformal coated with lithium metal. Dendrites growing outward from an internal pore surface will propagate until they come into contact with an opposing wall inside the foam and further growth is mechanically frustrated. This prevents dendrites from propagating external to the anode, as the dendrites would be trapped within the structure of the foam. 

The second feature is a five micron mask that, when applied to the surface of the 3d foam, prevents electrodeposition of lithium metal near the surface of the electrode, hence preventing growth of lithium dendrites near the surface. 

The third feature is a novel, highly conductive ionic fluid rigid-rod polymer composite expected to achieve a conductivity of 8.3x10^-3 S/cm^2. This polymer has already demonstrated protonic conductivity of 8.3x10^-3 S/cm^2 and must be modified for use in a lithium ion battery. Rigid-rod polymers have a tensile modulus that is 37x &amp;#150; 62x stronger than a standard polyethelyene solid polymer electrolyte. This strength may physically deter or altogether prevent the growth of lithium dendrites. XABC believes that the novel combination of these three unique features will enable the stable cycling of lithium metal in a secondary cell. 

For Phase I, XABC proposes to fabricate and test the effect of both the polymer and masked 3d foam on dendrite suppression. For Phase II, XABC proposes to fabricate fully functioning negative electrodes with the features above.
Control of extremely lightweight, long endurance aircraft poses a challenging aeroservoelastic (ASE) problem due to significantly increased flexibility, and aerodynamic, structural, and actuator nonlinearities. To obtain the benefits of increased aerostructural efficiency, the controller needs to trim at a specified optimal shape while minimizing structural fatigue from gust disturbances. Tao Systems and Texas A&amp;M University propose to develop a distributed, passivity-based, ASE controller (DPASC) using sectional aerodynamic and structural output-only feedback. This scalable, decentralized approach has the potential to minimize the impact of aerodynamic / structural uncertainties and control surface free-play / saturation, while guaranteeing global asymptotic stability.
This project will further MBSE technology in fundamental ways by strengthening the link between SysML tools and framework engineering execution environments. Phoenix Integration has produced a commercial tool (MBSE Pak) which allows engineers to link SysML diagrams (in MagicDraw and Rhapsody) to ModelCenter, a general-purpose engineering integration framework. As a result, from SysML parametric diagrams, engineers can execute actual engineering analysis tools for the purpose of systems architectural design, requirements compliance, trade studies, etc. This proposal would extend this MBSE product in several specific ways. First, it would develop a systems analysis capability for improved management decisions including the ability to perform what-if studies of technology options, simulation of schedule and cost, and probabilistic discrete event simulation for risk analysis. Second, it would improve verification and validation of models through improved requirements compliance analysis, handling of time series data, and traceability of data pedigree for modeling artifacts. Third, it would connect SysML models to executable model libraries in which components can be executed in an ad-hoc manner (on any capable computer) from the library itself and include rich support for multi-fidelity modeling tools on  the backend. A representative system model would be developed as an example problem to illustrate the developed features and would be demonstrated to NASA throughout the course of the work.
The research objectives of this proposal are to: (1) To adapt the thermal-fluid science procedures for the prediction of weld defects to the prediction and control of surface defects and melt pool instability during the deposition of single tracks in SLM and to control the as-deposited microstructure. (2) Utilize physics-based analysis to predict variability caused in the individual SLM track cross-section geometry due to the statistical distribution of powder particles sizes and the potential non-uniform placement of powder particles during recoating. This will also include performing statistical analysis of the variability and to develop a probabilistic model to calculate levels of confidence and exceedance for the size and type of potential defects as a function of the SLM process parameters. (3) Determine the thermal cycling during deposition and use it to predict solidification microstructure and solid state transformations during deposition; and (4) Demonstrate feasibility of the analytical procedures for alloy IN718.
Thermal anemometry (a.k.a. hot-wire anemometry) has been a key experimental technique in fluid mechanics for many decades. Due to the small physical size and high frequency response of the sensors (resulting in excellent spatial and temporal resolution), the technique has been widely used for studies of turbulent flows. Even with the advent of nonintrusive techniques such as Laser Doppler Velocimetry (LDV) and Particle Image Velocimetry (PIV), hot wire anemometry is uniquely capable of extremely high frequency response and fine spatial resolution measurements.

ViGYAN proposes a fundamental change to the anemometer configuration, with two related aspects. First, the circuitry to power the sensor and establish its operating point is packaged immediately adjacent to the sensor, i.e. in the typical probe holder, removing the effect of the cable connecting the sensor to an external anemometer. Second, modern analog-digital conversion hardware will be employed to the maximum extent possible, potentially including directly driving the sensor. Data transmission will then be fully digital, immune to environmental variations or electrical noise. Further, direct excitation would permit the choice of operating modes (not just variation of operating point) by changes in software. The ultimate objective of the research is therefore referred to as a "Digital Bridge".
Phoenix Integration and MIT propose to create a novel autonomous optimization tool and application programming interface (API). The API will demonstrate the ability to link to many optimization algorithms, both open source and proprietary, as well as to framework tools that carry optimization algorithms within them. It will also allow users to connect their engineering models to it conveniently. The API will be available both as a cross-platform standalone product and as part of ModelCenter, an engineering integration and trade study environment. In addition to and included within the API will be techniques to perform optimization autonomously by providing a management layer which globally adjusts the run in an intelligent fashion. Thus, it will categorize problems to understand effective solution techniques for them, try many algorithms during a run, change the settings on single algorithms so they run more productively, adaptively learn which techniques worked and which didn't, and inquire of the user insight that may help the optimizer reach its destination sooner. A database of prior runs will be built to help facilitate these features. The management layer will also help the user understand errors that take place, log appropriately, and prevent failures.
We propose to develop a sensor for in-situ stable isotope analysis from a lander/rover on future planetary missions.  The system will enable the collection of valuable information applicable to biosignature investigations, i.e., the search for evidence of life within the solar system.  Current limitations to in-situ isotope measurements will be overcome by utilizing a hollow fiber optic based IR spectroscopy concept.  This concept enables high precision measurements within the ultra-small sample volume (&lt;&lt;1ml) of the hollow fiber and has proven to be three orders of magnitude more sensitive in terms of required sample size than current state of the art isotope sensors.  The proposed project will focus on transitioning the current lab-based technique to a small size, weight, and power (SWaP) device that can be operated unattended.  Significant strides will be made in this direction through the use of optimized hollow fiber technology developed at OKSI.  In Phase I, proposed concepts for improving the system performance, reducing the SWaP, and engineering a field-capable device will be proven and specific options down selected for full development in Phase II.  A complete prototype will be produced to measure Carbon (C) and Sulfur (S) isotope ratios from solid rock samples in Phase II.  The ability to generate simultaneous C and S isotope measurements from solid samples has great potential for assessing biosignatures relating to sulfate reducing organisms and organisms using simple C substrates (including methanogens, fermenters, and others).  The sensitivity afforded by the proposed system would open up this capability to smaller samples than ever before measured as well as provide a potential device for remote deployment.  This could be a significant development in the search for these biosignatures on other planets and near space objects as well as in the early Earth rock record.
New measurement technologies are required to support science campaigns to better quantify rapid changes in the Earth atmosphere system. A key factor in this heightened focus on risk and uncertainty is the growing recognition that the climate is changing far more rapidly than was thought just five years ago. Aurora Flight Sciences and Harvard University propose to miniaturize the Harvard Integrated Cavity Output Spectroscopy (ICOS) instrument for use in the unique reel-down payload pod of the "StratoCruiser", a proposed propulsive high-altitude balloon gondola. Combining the persistence of balloon platforms, the vertical measurements of soundings, and the mobility of aircraft the StratoCruiser will enable new understanding of stratospheric phenomenon.  The focus of the proposed effort will be to enhance the StratoCruiser reel-down payload capability through size, weight, and/or power (SWaP) reduction in the dual laser, 50 cm cell, ICOS instrument. The soundings from the StratoCruiser ICOS-based observing system provide laboratory quality, in situ detection of radicals, isotopes, ozone, reactive intermediates, long-lived tracers and condensed and vapor phase H2O and HDO over the US for a period of 4-6 weeks.
We propose development and demonstration of a dynamic aeroservoelastic modeling and optimization system based on curvilinear internal structural arrangements of variable topology.  This will allow combined sizing and topology optimization of complete airplane configurations including aeroservoelastic performance.
The Electrodeless Lorentz Force Thruster (ELF-160A) has the ability to efficiently ionize and electromagnetically accelerate a variety of propellants over a broad range of specific impulses from 1,000-6,000 seconds. 
The ELF-160A thruster creates a high-density, magnetized plasmoid known as a Field Reversed Configuration (FRC) employing a Rotating Magnetic Field (RMF). The RMF driven azimuthal currents, coupled with the enhanced axial magnetic field gradient produced by the FRC inside the flux preserving conical thruster, produce a large axial JxBr force that accelerates the plasmoid to high velocity.
The ELF-160A is completely electrodeless, the propellant is magnetically isolated from the thruster body, quasi-neutral, and there is zero contact between high temperature propellant and the thruster. Combined with a high ionization efficiency and rapid formation and ejection sequence, the ELF can operate on any gaseous propellant, and do so with a very long lifetime and with low thruster specific mass. The AFOSR-funded 200 kW ELF thruster was designed and testing using Nitrogen, pure Oxygen, and Xenon as its primary propellants and demonstrated no life limiting or erosion issues. The NASA developed 1kW class ElectroMagnetic Plasmoid Thruster (EMPT) demonstrated steady operation on a variety of propellant with over 100 Hrs of operation.
The focus of this proposal is to take the results from the ELF and EMPT programs and develop a new 30 kW-class thruster that is capable of long duration operation on any gaseous propellant. Phase I will develop the new systems required to transition this technology to a 30 kW, thermally stable, high temperature thruster and PPU system.
Thermoelectric devices offer a simple and reliable means to convert radioisotope thermal energy into useable electrical power.
Present thermoelectric devices based on bulk materials are limited by low conversion efficiencies, due to fundamental limitation of identifying materials with both a high electrical conductivity and low thermal conductivity. Nanowires provides a means to circumvent this limitation, and achieve combinations of properties not possible with bulk materials. To accomplish this task, SMI will demonstrate the formation of nanocomposite structures in a SiGe matrix by gas flow hollow cathode (GFHC) sputtering creating high ZT for the GFHC sputter deposited solid state nanocomposite thermoelectric materials. The potential for high deposition rate, and thick films for the solid state nanocomposite materials, on a range of substrates, by GFHC sputtering will be investigated and demonstated, along with a pathway forward to development of a high efficiency TE power conversion system prototype in Phase II.
The innovation proposed here is a high-performance, high-fidelity simulation capability for simulating liquid rocket spray combustion based on a novel spray-flamelet methodology which will be integrated into Loci-STREAM which is a CFD solver developed by the proposing personnel under funding from NASA over the last several years. A new spray-flamelet formulation will be incorporated into Loci-STREAM. The particular advantages of this formulation are (i) its consistency with the single-phase flamelet-formulation (already available in Loci-STREAM), (ii) its formulation in mixture-fraction space, overcoming the non-uniqueness of the classical mixture-fraction parameterization, and (iii) its applicability to finite Stokes-number, thereby accounting for particle evaporation, slip-velocity, and poly-dispersed spray-phase. The flamelet methodology already available in Loci-STREAM &amp;#150; in conjunction with Hybrid RANS-LES (HRLES) methodology &amp;#150; has facilitated an order of magnitude improvement in simulation turnaround times for NASA applications involving complex physics in 3D geometries. This project is aimed at extending this flamelet methodology to spray combustion resulting in a state-of-the-art design and analysis tool to enable accurate, fast and robust simulations of multiphase combustion in liquid rocket engines (involving liquid propellants such as LOX and LH2/LCH4/RP-1/RP-2), combustion stability analysis, etc. which constitute critical components of NASA's upper stage launch propulsion systems
This STTR project delivers a compact vibration-based Energy Conversion Module (ECM) that powers sensors for purposes like structural health monitoring (SHM). NASA customers include the ISS and the Orion deep space vehicle, both of which need wireless sensors to monitor and assess structural health. The ECM represents a significant advancement in the use of wireless and self-powered devices by enabling the miniaturization of vibration-based energy harvesting devices suitable for powering sensors.
Implications of the innovation
There exist two basic problems in reducing the size of vibration-based harvesters that plague all current commercially available devices&amp;#151;both are addressed here. The first is addressed by eliminating the problem of frequency matching in compact devices. The second is addressed by providing a broadband device capable of energy conversion across a range of frequencies.
Technical objectives
Our initial prototype is a TRL 4 unit that we used to demonstrate our ability to convert kinetic energy to useful electrical power. This prototype combines piezoelectric beam type transducers with artificially induced magnetic fields to force a nonlinear broadband behavior. Phase I shows feasibility through experimental tests and theoretical models that will establish that we can use this approach for compact sizing of low center frequency transducers.
Research description
Phase I transforms our prototype into a compact system and performs a variety of engineering feasibility tests under both typical ambient kinetic environments and the more high intensity environments that might be found in propulsion testing and launch facilities.
Anticipated results
Anticipated results include a reduction in the amount of battery waste generated by self-powered electronic devices that enables long-term wireless deployment. Phase I completes a TRL 5 prototype and validates system performance in relevant vibration environments. Phase II delivers a TRL 7 unit.
Deep-ultraviolet (UV) Raman spectroscopy is a powerful method to collect chemically specific information about complex samples because deep-UV (?? &lt; 250 nm) excitation shows an over 200-fold greater efficiency compared to commonly used 785 nm excitation and has the ability to avoid fluorescence background in the Raman spectra.  The availability of compact, robust, and reliable deep-UV laser sources has been always considered a major bottleneck problem on implementing this spectroscopic technique for NASA's space-borne applications. TIPD proposes to develop an ultrastable, compact, and long-lived deep-UV laser source for Raman spectroscopy based on our substantial experiences and facilities in developing single-frequency fiber lasers and solid-state deep-UV laser sources. Cooperating with the University of Arizona, we will develop an ultrastable and compact high power single-frequency single-polarization fiber laser system at 976 nm. The deep-UV laser source at 244 nm will be generated through two successive frequency doubling systems. In this phase I program, we will demonstrate deep-UV generation though frequency quadrupling of a 976 nm single-frequency fiber laser.  In phase II, a deep-UV laser prototype meeting all the criteria of NASA's applications will be developed.
The proposed Low Cost Nanolauncher (LCN) is an upper stage using a new, inexpensive propulsion system.  The Phase I program will combine several technologies with a simple design strategy to produce a flight-weight propulsion system that is easy to fabricate and operate.  Self pressurizing propellants will minimize complexity of the propulsion system and vortex cold-wall technology will be used to simplify the combustion chamber.  An inexpensive, light weight nozzle is being developed by Pennsylvania State University using carbon phenolics.  Commercially available components will be use where possible to further minimize costs.
The Phase I LNC will demonstrate these technologies through ground testing of a flight-like propulsion system.  A small launch vehicle second stage will be designed based on the experimental performance characteristics.  This work will form the basis for a family of vehicle stages from smaller upper stages to a main booster stage.  The low cost technologies and design methods employed in the LNC will reduce the cost of launching nanosatellites into orbit.
Eye safe 3D Imaging LIDARS when combined with advanced very high sensitivity, large format receivers can provide a robust wide area search capability in a very compact package.  This search LIDAR concept, when deployed on UAS, can provide target detection, tracking and identification of sufficient quality to enable search and avoid actions when other air traffic flies near UAS platforms in the National Air Space.  Current fiber laser technology, operating at a 1.5 micron wavelength, has sufficient pulse energy and pulse rates to illuminate large areas around the UAS platform.  The relatively low energy per pulse of the fiber laser is compensated by a new development in large format , compact receivers ( 2,000 x 32 or 1000 x 1000) which exhibit near photon counting capability in very small pixels (~ 15 microns).
A novel method for fabricating electronics containing both metals and polymers can be adapted to quickly and effectively produce micro-well sensors. The process revolves around creating a polymeric part through additive manufacturing, leaving voids and trace capillaries. Once the polymer structures are completed, molten metal is injected into these trace capillaries, which create a path to the voids in the printed parts. Capillary forces cause the liquid metal to wick into the capillary channels, filling the voids before solidifying. Unlike competing metal additive manufacturing techniques, the parts can be created with 100&#37; dense metal elements that have low surface roughness and are completely compatible with the surrounding polymer. 

The proposed objective is to adapt the process specifically for the fabrication of the micro-well detectors required by the AdEPT mission.

The overall objective of this proposal is to develop the liquid metal injection process for use with the high-resolution additive manufacturing methods made available through the UCF team, in order to allow for the creation of metal/polymer parts with sub-mm features. A further goal of the program will be to generalize the process in order to expand into other NASA projects, as well as enable a variety of commercial products.
TRUSS is a structurally efficient solar array concept that utilizes a TRAC rollable boom and tension-stiffened structure to exceed the program requirements for very large solar arrays.  TRAC provides simple strain-energy deployment with a constant cross section and constant strength along its length, improving the reliability and simplicity of array deployment.  The tensioning cables allow the structure to achieve mass efficiency much improved over the government reference array (GRA).  The roll-out deployment of the TRAC booms also simplifies the ground support structure needed for testing and qualification of full-size arrays, which will be animated to illustrate in-space and ground-based  deployments.
The technical objectives of this program are: (1) to develop a set of physics-based modeling tools to predict the initiation of hot corrosion and to address pit and fatigue crack formation in Ni-based alloys subjected to corrosive environments, (2) to implement this set of physics-based modeling tools into the DARWIN probabilistic life-prediction code, and (3) to demonstrate corrosion fatigue crack initiation and growth life prediction for turbine disks subjected to low-cycle and high-cycle fatigue loading in extreme environments.  This technology will significantly improve the current ability to simulate and avoid corrosion fatigue failure of engine disks or metallic structural components due to prolonged exposure to extreme environments at elevated temperatures.  Completion of the proposed program will provide probabilistic corrosion fatigue crack growth life assessment software tools for structural components subjected to aggressive hot corrosion environments.  Such a suite of software tools is unique and is urgently needed for designing and improving the performance of critical structures used in the space structure and propulsion systems in commercial and military gas turbine engines, and oil and gas industries.  This generic technology can also be used to provide guidance for developing new alloys or improving current Ni-based alloy designs for hot-section applications.
Lightning discharges within or near critical facilities can disrupt activities or result in damage. Although existing lightning locating systems can geolocate breakdown processes with accuracies of 10s of meters at heights above 1.5-2 km, they do not accurately report ground strike locations or provide estimates of current and charge transfer. In addition, conventional VLF/LF LLS networks do not currently report lightning channels descending towards or contacting ground with enough accuracy to address this problem. There is a need for a system that can improve location accuracy and detection efficiency. 
Under this NASA STTR program, QUASAR Federal Systems proposes to team with Professor Ken Cummins of the University of Arizona to develop a lightning detection sensor based on an SoA 6-axis EB vector sensor and unique location and characterization algorithm. 
In Phase I, we will perform a feasibility study of using a 6-axis EB sensor to address NASA "total lightning detection" needs in location accuracy and detection efficiency. This will include both analysis and limited field measurements. We will also identify a system architecture and key components for the Phase II prototype. In Phase II of the project, we will develop a scientific prototype to demonstrate the technology with field data.
We propose to develop and demonstrate BioComm, a bio-inspired autonomous communications system (ACS) aimed at dynamically reconfiguring and redeploying autonomous communication assets in accordance with both mission objectives and communication demands simultaneously. BioComm is embedded with ADaM (Anomaly Detection and Monitorin) capability, which enables human supervisors or operators to exploit, benefit from, and interact with BioComm systems with high confidence by alerting the operators of multiple, heterogeneous ACSs on anomalous system behaviors without requiring a deep understanding of the functions in the underlying systems. The proposed solution (BioComm-ADaM) is based on the unique combination of: (i) Digital Hormone Model augmented with Criticality-Sensitive Control with the goal of achieving rapid self-configuration and fully autonomous adaptive deployment, redeployment, and reconfiguration of NASA's autonomous communication assets under a broad range of mission scenarios; and (ii) Surprise-Based Learning capable of learning the expected or normal behavior of a wide range of autonomous systems, detect any behavioral anomalies or deviations from the norm, identify potential causes, recommend some feasible changes to a human supervisor, and execute the selected or recommended changes. 

The BioComm system adds a powerful new degree of freedom for self-adaptation, which is the "mobility" of autonomous communication assets based on their awareness of the "communication environment", thus allowing radios to adapt both their software parameters and physical locations or formations so as to best support space missions. Thus, BioComm will greatly expand the feasible dimensions of self-adaptation for communication parameters by further allowing the autonomous assets to "move" to "right" places when the autonomous adaptation of parameters alone is not sufficient in order to achieve  much greater and powerful autonomous end-to-end communication capabilities.
L&amp;#61655;Garde will develop a lightweight Ultra-Flexible Advanced Stiffness Truss (Ultra-FAST) that will prove to have greater material metrics and structural performance indices than the current state of the art for large space deployable trusses. The key to the success of the proposed technology has to do with the new design approach and new material development. First, customized components will be fabricated such as thin-walled longerons and short flexure hinges in Phase I. The proposed flexure hinges have higher effective compressive strain values in bending than traditional compressive materials. These two key components have low density values not greater than 1,800 kg/m3 and are made of high performance carbon fibers. The estimated total truss mass per length is approximately 0.167 kg/m. L/d=100 slenderness longerons made of thin-walled tubes will guarantee a high axial and bending stiffness truss because they have a higher area moment of inertia compared with traditional solid rods. An axial load will be applied in order to measure the axial stiffness and axial strength of the truss. Also, bending moment will be applied to measure the bending stiffness and bending strength.
Gas-Liquid separation is an acute microgravity problem. Existing devices use centrifugal motion on microporous membranes to separate the two phases. Centrifugal devices consume electricity and are prone to failure. The microporous membranes easily foul and have significant water loss. Novel membrane devices are proposed. Membranes can simultaneously disengage gases from gas-liquid dispersion and degas water. Membrane is compact, lightweight and with no moving parts, consumes no electricity during gas-liquid separation and provides enhanced simplicity. Product is novel nonporous high gas flux, high temperature perfluoropolymers. Gas-liquid dispersion/solution enters module and dispersed/dissolved gases permeate through membrane. Degassed water leaves device. Degassing of water is independent of water pressure.  Therefore operating at low pressure is desirable.  Non-porous nature minimizes fouling.  Thousands of systems have been sold over the last 10 years for degassing transformer oil. Water vapor losses are simultaneously reduced. Key innovations include development of fouling resistance high temperature hydrophobic Hollow Fiber (HF) system for degassing gas-liquid. By flowing gas-liquid feed on outside of wound HF, both gas and liquid feed are well mixed and exposed to membrane non-porous surface. Industrial partners have been established. Phase I will demonstrate gas-liquid separation and superior performance in fouling resistance and water loss compared to Microporous HF controls. Partners are positioned to actively participate in Phase II and commercialization.
NASA emphasizes the need to implement energy harvesting in its future mission activities. By harvesting energy from the ambient surroundings, there is less dependence on a primary power supply (e.g., combustion engines, fuel cells, batteries, solar cells, etc.).  Overall power consumption is thereby reduced, equipment weight goes down and logistical supply needs are simplified. Future NASA missions will need innovative energy harvesting methods that are cost effective with reduced mass, reduced volume, and that accommodate extreme operating conditions.  For this STTR application, Lynntech has teamed Dr. Ray Baughman (Director of NanoTech Institute, University of Texas at Dallas) to pioneer the use of artificial muscles (also known as coiled polymer actuators) as an advanced method for heat-to-electricity energy harvesting. Our primary application is to harvest waste heat from airplane engines, but it could be adapted for use in many other applications where waste heat is generated.
We propose to apply to planetary terrain mapping an alternative, multiresolution method, subdivision surfaces (subdivs), in place of conventional digital elevation maps (DEMs) and fixed-resolution meshes. The proposed research is innovative in that it presents a new setting for subdivs that demands novel extensions to subdivision algorithms, techniques and theory. The primary objectives of this work are to: (1) demonstrate suitability of subdivs as a representation for terrain data with highly varied spatial resolution and 3-D features; (2) demonstrate their ability to encode, and later re-register, local detail non-destructively through hierarchical edits; and (3) prototype a software user interface introducing new capabilities enabled by the subdiv representation. The expected benefits are: (a) higher-fidelity terrain visualization with reduced infrastructure requirements; (b) ability to visualize 3-D features, such as overhangs, missed in DEM's; (c) compact encoding with natural level-of-detail control for interactive viewing even on mobile devices; (d) greater algorithmic efficiency for non-visualization scientific computation; and (e) enablement of new software-tool capabilities for dynamic mapping of alternative local-terrain datasets, non-destructive experimentation, collaboration, and data traceability. The innovation also promises capability and reliability benefits to a surface robot by unifying terrain representations and enabling minimal upload of only incremental terrain details from the ground.
Embry-Riddle Aeronautical University (ERAU) and Honeybee Robotics (HBR) proposes to develop an integrated autonomous free-flyer robotic spacecraft system to support the exploration and subsequent resource utilization of asteroids as well as other planetary bodies and moons.
The proposed spacecraft will address the first step towards In Situ Resource Utilization from Near Earth Object bodies; namely it will prospect it with sample acquisition devices and characterize the NEO for ISRU potential. Embry-Riddle and Honeybee Robotics propose an innovative resource prospecting mission concept based on autonomous small marsupial free-flyer prospector spacecrafts. Such technologies are currently being developed at Embry-Riddle. The spacecraft will utilize unique technologies such as MicroDrills and Pneumatic Samplers previously developed under other SBIR projects by Honeybee Robotics. In particular, the proposal will focus on flight control and reconfiguration for guidance under extreme environments, vision-aided navigation approaches, and sampling systems design, testing and evaluation. The proposed system will be developed, simulated and evaluated during Phase I of the project, and experimentally validated and demonstrated during Phase II through flight testing on an autonomous research platform. The successful completion of the proposed research is anticipated to provide a theoretical and experimental framework to investigate the capabilities of a marsupial-based robotic system to explore and extract samples  from terrains that would be inaccessible to traditional rover-type vehicles and where traditional flight guidance and navigation sensors, such as GPS receivers and magnetometers, are not functional.
In the combined Phase I and Phase II programs Faraday and our MIT collaborators will demonstrate the feasibility of low-cost fabrication of high-efficiency, microchannel-plate reactors for the electrocatalytic reduction of CO2 to CH4.  The proposed concept is founded on FARADAYIC&amp;#174; Through-Mask Etching of metallic (e.g., stainless steel and titanium) substrates to form suitable microchannel electrodes, and on pulse-reverse FARADAYIC&amp;#174; Electrodeposition of copper for uniform coating of the cathode surfaces.  The electrocatalytic efficiency of the copper layer will be enhanced through the use of a literature-reported oxide-reduction process. Inclusion of a suitably large density of channels should result in substantial active area in a compact form factor, while entirely avoiding the complications of packed-bed type reactors.  Faraday plans to focus development toward the ultimate use of room-temperature ionic liquids (ILs), as they afford such advantages as negligible evaporative loss, generally high CO2 solubility and low CH4 solubility, and a broad potential window of electrochemical inertness.  The particular challenge of gas-liquid separations in microgravity, where buoyant effects cannot be exploited, will be addressed through a novel centripetal application of an established spiral-channel microfluidic concept.  The envisioned system described in this proposal consists of three distinct unit operations: (1) an absorber which "getters" gaseous CO2 from the atmosphere using a wet room temperature IL-based electrolyte, (2) a microfluidic electroreactor which efficiently converts the CO2 to CH4 with oxygen being generated as useful by-product, and (3) a spiral-channel gas-liquid separator to remove the CH4 and O2 from the IL stream which is recycled to the absorber.
The Architecture Framework for Fault Management Assessment And Design (AFFMAD) is a constraint-checking system for FM trade space exploration that provides rigorous performance guarantees for FM strategies for complex cyber-physical systems. AFFMAD will aid FM engineers in the early evaluation of FM strategies and improve the efficiency of implementing and testing those strategies. Using existing multi-mode cyber-physical reasoning systems, recent advances in Satisfiability Modulo Theory (SMT) solvers, hierarchical scheduling theory, and system-level modeling frameworks, AFFMAD will assist users in identifying FM conflicts and inconsistencies in FM approaches and mission requirements as they are developed.
Given that SysML is becoming a standard for model-based systems engineering and Integration (SE&amp;I), system health management (SHM)-related models will either be done in SysML, or be done outside of SysML but enabled by conversion, mapping, and traceability of information across SysML and SHM models. Given that current implementations of SysML are not particularly useful to perform analyses, and that SHM analyses are not identical to typical SE&amp;I-related analyses, there will need to be connectivity between SysML representations and SHM models that perform SHM-related analyses.

Qualtech Systems, Inc. (QSI), with Dr. Stephen Johnson as a consultant intends to explore and develop the integration of model-based systems engineering and Integration (SE&amp;I) using SysML with system health management (SHM) modeling and analysis using QSI's Testability Engineering and Maintenance System (TEAMS). An overarching objective of this proposal is to reduce the duplicative and disjoint effort by NASA's subject matter experts in the development of systems engineering and design models as well as systems health management/fault management models. The intent is to leverage the success space or intent based system design models and transform them for developing fault management models and ensuring changes in design have a natural flow-through to the FM domain, thereby keeping FM models in sync with the design through a semi-automated process. This is one step in the larger set of issues that will need to be addressed in the development of the model-based Discipline of Systems Engineering and its concurrent integration with SHM to achieve higher-quality designs while reducing the costs of SE&amp;I.
Microwave regenerative sorption media gas storage/delivery techniques are proposed to address both compressed gas management and hydrogen purification requirements in support of crewed deep space exploration missions.  By reducing or eliminating the need for a conventional gas compressor, both the crew habitat noise level and required storage pressure for important Air Revitalization (AR) gases, such as oxygen and carbon dioxide, are reduced by using this technology.  In addition, with slight modifications, the same concept can be used to serve as a regenerable hydrogen gas purifier.  In either application, the penetrative nature of microwave heating is utilized to efficiently drive gas desorption from physical sorbents.  For the compressorless gas storage application, the microwave desorption step supplies pressurized gas to downstream processes.  Similarly, for application as a hydrogen purifier, microwave heating drives off captured contaminants from the sorbent bed (which is held at relative vacuum) during regeneration.  Potential contaminants present in the hydrogen stream include water vapor, carbon monoxide and various hydrocarbons (including methane, acetylene, ethane, and ethylene).
A Microchannel Sabatier Reactor System (MSRS) consisting of cross connected arrays of isothermal or graded temperature reactors is proposed. The reactor array enables nearly complete single pass carbon dioxide reduction using the Sabatier reaction, allowing efficient recovery of oxygen from in situ carbon dioxide resources on Mars or other Near Earth Objects.  Arrays of microchannel reactors with decreasing temperatures and increasing residence times can be optimized to maximize reaction kinetics and overcome thermodynamic limits (85&#37; conversion at 400 C)of the Sabatier reaction resulting in 99&#37; conversion of carbon dioxide and hydrogen to water and methane.  Alternatively, monolithic graded temperature reactors can be developed that will optimize reaction kinetics with respect to the thermodynamic limitations of the Sabatier reaction in a compact and efficient design.  The Phase I efforts will focus on design and construction of the microchannel reactors.  The Phase II effort will build upon the feasibility demonstration resulting in the development of a prototype MSRS consisting of a microchannel reactor array and a graded temperature microreactor capable of 99&#37; single-pass, carbon dioxide conversion to methane and water capable of processing 1 kg hr-1.
Aurora Flight Sciences and partner, Draper Laboratory, propose to develop an on-orbit immuno-based label-free Suspension Cell Culture ANalysis tool, SCAN tool, which utilizes antibody-antigen surface binding as its core sensor technology.  Our proposed SCAN tool is designed to provide an on-orbit analysis of suspension samples to support studies of bone and muscle loss, multi-generational species studies and cell and plant tissue per NASA SBIR topic description H.10.02. 

The SCAN tool technology would function as follows: A disposable cartridge specific to a targeted biomarker is inserted into the SCAN tool.  The user introduces a cell suspension sample into the cartridge. Cells presenting target antigens bind specifically to corresponding antibodies fixed within the cartridge flow path.  The number of bound cells is detected optically by the SCAN tool and is reported to the user on a display screen within several minutes.  The cartridge is removed, disposed and replaced after each measurement.

We propose to heavily leverage our experience gained from the On-Orbit Immuno-Based Label-Free White Blood Cell Counting System with MEMS Technology (OILWBCS-MEMS) Phase I and Phase II SBIR contracts (completed August 2012) for this effort. The OILWBCS-MEMS benchtop evaluation setup will be used as a test platform, and the hand held SCAN tool design will use OILWBCS-MEMS as a point of departure.  The major difference between the two is the surface chemistry required to target the biomarkers of interest.  By building upon a successful project, we continue to make use of NASA's considerable prior investment.  Our prior effort also enables us to quickly mature this technology to high TRL (proposed TRL 6-7) by the end of Phase II.
To address NASA's need for advanced nondestructive evaluation (NDE) of complex built-up spacecraft structures, Physical Optics Corporation (POC) proposes to develop a new Multifunctional Compton Inspection Tool (MCIT) for operation onboard the International Space Station (ISS), based on POC's previously developed Compton imaging tomography (CIT) approach. CIT works by acquiring two-dimensional (2D) images of Compton-scattered X-ray radiation produced by multiple slice views of the object, with subsequent three-dimensional (3D) reconstruction of the inspected structure for high-resolution detection and localization of defects. The MCIT incorporates new features and modifications of the CIT, which permit it to operate in multiple modes with enhanced functionality, smaller form factor, and smaller weight. The proposed MCIT will allow noncontact, single-sided inspection of various spacecraft structures (such as micrometeoroid and orbital debris (MMOD) shields, pressure vessels, ISS modules, and thermal protection of visiting spacecraft) from either within the pressurized habitable compartments or open space. In Phase I POC will demonstrate the feasibility of using MCIT for NDE of spacecraft components by fabricating and testing a TRL-4 prototype, with the goal of achieving TRL-6 by the end of Phase II.
TUI proposes a novel process to produce 3d printer feedstock filament out of scrap ABS on the ISS.  Currently the plastic filament materials that most 3d printers use are produced with screw-based extruders that are fundamentally designed for high volume terrestrial production from uniformly pelletized resin feedstock.  These require relatively large continuous batch sizes with significant operator inputs and have generally poor control over the produced filament geometry.  Existing extrusion machines also tend to rely on separate facilities for fully drying the material beforehand, and do not inherently provide tight flow-rate control.   The proposed effort will develop a filament extruding machine that uses a process called Positrusion that is designed from the ground up for optimally producing small batches of positively controlled round filament directly out of arbitrarily shaped scraps of ABS plastic, while meeting requirements for operation on the ISS.  The machine will accept miscellaneous ABS parts, it will dry and degas the input material before melting and extruding it through a die, and the cross-sectional dimensions and feed-rate of the cooling extrudate will be tightly controlled in a continuous analog of closed-die molding.
This project will achieve a wrist-worn actigraphy device called STARwatch, designed specifically for space exploration environments. It will provide a minimally obtrusive, objective measure that evaluates astronaut sleep-wake activity and light exposure. This project will leverage our second generation actigraphy device that has already been validated in controlled laboratory experiments against gold-standard polysomnography. The compact wrist-worn device includes sensors to collect sleep metrics and will also serve as a wireless hub to collect real-time physiological data from other body-worn sensors (e.g., heart rate, EEG). It will use standardized wireless communication protocols (e.g., Bluetooth) to automatically uplink data to the ISS network (no astronaut time required). Data will automatically be integrated into medical operations support systems (e.g., BHP-Dashboard) to provide immediate feedback to astronauts and flight surgeons to aid in decision-making relative to astronaut medical, behavioral health and performance issues. During Phase I, we will develop an enhanced STARwatch, integrate data from other body worn sensors (e.g., heart rate sensor), demonstrate automatic data streaming using approaches compatible with the ISS network environment, and develop a plan for operational validation and spaceflight certification that will be implemented during Phase II (Phase I TRL of 4-5).
Some target signatures of interest in drought monitoring, flooding assessment, fire damage assessment, coastal changes, urban changes, etc. may need to be tracked periodically. In a typical change detection application, a hyperspectral image collected in an earlier visit may need to be compared with later images collected using different imagers with different viewing geometries, illumination, ground sampling distance (GSD), spectral sampling, signal-to-noise ratio (SNR), and atmospheric conditions. We propose a novel framework that can deal with all of the above challenges. We first propose to apply techniques such as flat-field to obtain the reflectance signature (fire damage signature, for example) from the target radiance signatures in a given hyperspectral image. The target reflectance signature is then saved in a target reflectance signature library for future use. After that, to detect targets (fire damage, for instance) in new images, we will expand a hyperspectral image processing system developed by the Johns Hopkins University/Applied Physics Lab (JHU/APL).
This proposal is responsive to NASA SBIR Subtopic S1.02: Microwave Technologies for Remote Sensing, 640GHz Polarimeter. VDI has recently demonstrated the integration of a WR10 Mixer-Amplifier Multiplier chain (MixAMC), including the LO and IF amplifier MMICs, into a single waveguide housing. The focus of the proposed research is the extension these innovative integration technologies to include additional components required for atmospheric radiometers, and to extend the resulting technology across the frequency band of interest to NASA. Such integration will fundamentally improve the size, weight, reliability and cost of terahertz receivers. Additionally, the integration of a newly available low noise MMIC amplifier at the front-end of the receiver will allow these improvements to be achieved with an overall reduction in the power requirements and an increase in receiver sensitivity.  At the end of the Phase 2 VDI will deliver to NASA a very compact and reliable receiver system suitable for polarimetric measurements at 640GHz. The ultimate result of this SBIR program will be the commercial availability of compact, reliable and cost effective receiver systems throughout the frequency range of interest for atmospheric remote sensing, including polarimetric measurement capabilities. Additionally, the new compact receivers will be compatible with CubeSats, which are expected to play a very important role in future atmospheric remote sensing missions.
Spacecraft cabin is noisy and uncomfortable. Sometimes, the noise level can exceed 80 dBA. There are 2 challenges to meet the above needs. One is to generate an anti-phase (180 deg out of phase) signal in real-time to reduce the loud cabin noise in a small area. Another one is to minimize the spillover of the anti-phase signal to other places. We propose a novel and high performance approach to suppressing background noise in noisy cabins. Our system utilizes a patent pending adaptive algorithm that can generate anti-phase signals in real-time to suppress background noise. Our system is portable and easy to set up. Most importantly, our system can suppress background noise in a small area and will not spill the anti-noise signal to other places.
Human exploration of Mars, as well as unmanned sample return missions can benefit greatly from use of propellants and life-support consumables produced from the resources available on Mars.  The first major step of any in-situ propellant production system is the acquisition of carbon dioxide from the Mars atmosphere and its compression for further chemical processing.   

TDA Research Inc. proposes to develop a compact, lightweight, advanced sorbent-based compressor to recover high-pressure, high purity CO2 from the Martian atmosphere. The system eliminates the need for a mechanical pump, increasing the reliability with relatively low power consumption. TDA's system uses a proprietary sorbent that selectively adsorb CO2 at 0.1 psia and regenerates by temperature swing, producing a continuous, high purity CO2 flow at pressure (&gt; 15 psia).  

The objective of this Phase I research is to develop a high capacity, regenerable CO2 adsorbent that maintains its CO2 capacity and mechanical integrity over extended adsorption/desorption cycles. We will optimize the sorbent formulation and conduct a minimum of 100 complete adsorption/regeneration cycles for our best sorbent formulation.  We will carry out a design of the adsorbent-based CO2 compressor and demonstrate the technical feasibility of the concept and quantify the logistics savings.
An on-board oxygen concentrator is required during long duration manned space missions to supply medical oxygen.  The commercial medical oxygen generators based on pressure swing adsorption (PSA) are large and highly power intensive.  TDA Research, Inc. (TDA) proposes to develop a small, lightweight, portable oxygen generator based on a vacuum swing adsorption (VSA) to produce concentrated medical oxygen.  The unit uses ambient vehicle cabin air as the feed and delivers high purity oxygen while meeting NASA's requirements for high flow capacity, closed-loop tissue oxygen control and operation in microgravity/partial gravity.  TDA's VSA system uses a modified version of the lithium exchanged low silica X zeolite (Li-LSX), a state-of-the-art air separation sorbent extensively used in commercial Portable Oxygen Concentrators (POCs) to enhance the N2 adsorption capacity.  

In Phase I, we will demonstrate the scientific, technical, and commercial feasibility of the oxygen concentrator module (OCM).  The concentrator will have an adjustable pressure output to produce 2-15 lpm of O2 at 50 percent to more than 90 percent purity from ambient cabin air.  The OCM will be capable of self-regulating the oxygenation of the patient using a closed loop feedback system that senses tissue oxygenation level. We will evaluate the sorbent performance in a breadboard bench-scale prototype under simulated microgravity/partial gravity exploration atmospheres and carry out a 10,000 cycle test (at a minimum) to determine its long-term performance and mechanical durability.  Based on the experimental results, we will carry design the demonstration unit, optimize its power draw over the range of flows and oxygen levels, and determine its weight, volume and heat rejection requirements. This design will also include an inlet filter designed to remove potential smoke or toxic gases.
Many of NASA's exploration scenarios include important roles for autonomous or partially autonomous robots.  It is desirable for them to utilize human tools when possible, rather than needing to build custom tools for each robot.  Control of robotic manipulators for tool usage generally requires a very precise Cartesian-space trajectory of the tool tip (e.g., moving a marker along the surface of a whiteboard or rotating a screwdriver about an axis).  Well-known techniques exist for manipulator control in Cartesian space, most of which necessitate solving a series of Inverse Kinematics (IK) problems.  Closed-form IK solvers work well for 7-degree-of-freedom (DOF) arms with rigid tool attachments, but cannot handle non-rigid tools that slip in the robot's hands.  Numerical IK approaches are more generic and can handle non-rigid links to tools, but can be slow to converge.  More importantly, if any joints fail or become limited in their range of motion, the robot arm essentially becomes 6-DOF or lower.  IK solvers often fail in these lower DOF spaces because the configuration space becomes non-continuous and full of "holes".  As a result, a 7-DOF robotic arm in space might be rendered largely useless if a single joint fails or even loses mobility until it can be serviced.  

TRACLabs proposes to investigate an alternative approach to traditional Cartesian control approaches, which rely on complex IK solvers that go from Cartesian space backwards to joint space.  We propose to leverage cheap memory and modern processing speeds to instead perform simple computations that go from joint space forwards to Cartesian space.  Such techniques should overcome common changes to a manipulation chain caused by tool slippage or the grasping of a new tool and to overcome uncommon changes to a chain caused by joint failures, reduced joint mobility, changes in joint geometry or range of motion, or added joints.
The state-of-the-art Li-ion battery technology is based on processing of lithium transition metal oxides, and graphite powder, and use of liquid organic electrolytes. It has shown limited room for further performance improvements in terms of energy density, cycle and calendar life, abuse tolerance and cost. This has heavily hindered the advancements of NASA's future space missions that need rechargeable batteries with higher energy density, longer life, and excellent abuse tolerance. In the commercial sector of electrical vehicles (EVs) and hybrid electric vehicles (HEVs), there are also urgent needs for rechargeable batteries with significantly higher performance characteristics that appear beyond the potential of current Li-ion system.

TH Chem, Inc. (THC) proposes to team with New Mexico Institute of Mining and Technology (NMT) to develop a new, all-solid-state Li-ion technology for NASA's future space missions that require rechargeable batteries capable of higher energy density (&gt;200 Wh/kg), longer cycle life (&gt;50,000 cycles), extended operation temperatures and radiation tolerance. The new battery system is based on development of a novel, all-solid-state, 3-dimmensional (D) battery design that exploits the full potentials of the electrode and electrolyte materials.

In Phase I, THC will demonstrate the feasibility of the new battery technology by preparation of the proposed all-solid-state 3-D batteries via processing of electrode and electrolyte precursors, followed by electrochemical evaluation of the test cells.  The concept of the new electrochemical system will be demonstrated.  THC and its team have extensive experience in advanced rechargeable battery chemistries and technologies.
The advancement of hybrid-electric propulsion systems for rotorcraft enables vertical takeoff and landing (VTOL) vehicles to take advantage of aerodynamic efficiencies that can reduce fuel consumption and emissions compared to conventional rotorcraft vehicles.   Unlike conventional internal combustion engines or high speed turbine engines, the high power-to-weight ratio and energy efficiency of electric motors is conserved when the motor is scaled to a smaller size.  A distributed electric propulsion system for a VTOL aircraft can exploit aerodynamic benefits increasing the lift to drag ratio by 4 to 5 times (Fredericks et al, Intl Powered Lift Conf., Aug 2013) compared to that of convectional helicopters.  This can yield a 4x increase in range while maintaining the VTOL and hover capabilities of a conventional helicopter.  Using LaunchPoint Technologies' brushless electric motor optimization software, controller expertise, and battery technology, LaunchPoint proposes to design a hybrid propulsion system for a VTOL aircraft that has an extremely high power-to-weight ratio, to demonstrate the validity of a concept VTOL vehicle.  LaunchPoint Technologies will seek robust system solutions for this hybrid electric propulsion including specifications for motor (propeller) distribution, motor power, lift, drag, a heavy-fuel combustion engine, alternator, battery pack, vehicle range and hover duration.  LaunchPoint will then produce a detailed design of the Auxiliary Power Unit (combustion engine and alternator), motors, electrical systems, and power control systems for the aircraft.  LaunchPoint will also further develop their dual-Halbach array brushless motor technology by building and testing a carbon fiber composite rotor to increase the specific power density of this propulsion system.
The requirements for cost effective manufacturing and metrology of large optical surfaces is instrumental for the success of future NASA programs such as LISA, WFIRST and NGXO. Our plan in this Phase I effort would be to combine our UltraForm Finishing (UFF) (a sub-aperture compliant wheel and belt type polishing process for rapid material removal from the ground state to a finished optic), with our newly developed UltraSmooth Finishing (USF). USF is our sub- and mid- aperture conformal pad polishing process capable of larger area finishing and smoothing of mid-spatial frequency errors. The UFF rapidly removes residual grinding marks and sub-surface damage, while providing a robust solution for surface corrections on the required X-ray mandrels and cylindrical shells. Our USF process was initially developed for high speed finishing of hard ceramic plano components and is now producing impressive test results for smoothing of critical aspheric components. OptiPro's technologically advanced optical manufacturing capabilities, along with our strong university and industry partnerships, gives us a very strong team and a clear path towards developing and commercializing the platforms which solve the difficult challenges associated with the fabrication of these large complex mirrors and cylindrical shells.
The proposed Phase I plan will include fabrication, test and delivery of a 0.25 meter precision mirror. The part geometry will be measured with OptiPro's "UltraSurf" a non-contact free-form measurement system. We envision that the work done during Phase I will be extended during Phase II to hyperbolic or elliptical shaped mirror surfaces with dimensions ranging from 1 to 2 meters. This research will position us with the information needed to develop the machine platforms needed for the fabrication and test of these large NASA mirrors, which could also be a Phase II deliverable.
Historically, designing a nuclear thermal rocket engine and determining fuel performance has been a refractory and anfractuous process.  Typically, fuel forms would be developed and tested in separate tests of mechanical, radiation and thermal testing, and, in the NERVA program, the fuel elements were assembled in a rocket engine and tested.  The fuel did not perform to expectations, and the engine needed to be disassembled, the fuel examined and fixed needed to be determined; then the process would repeat itself.

In the Space Nuclear Thermal Propulsion Program, individual fuel elements were tested, but they could not be tested to full power density due to test reactor limitations.  Nevertheless, this was a far less expensive approach that full engine testing to determine whether the fuel elements in particular would withstand the rigors of the NRE (Nuclear Rocket Engine) mission. 
This proposal outline how LPS and its team members plan to integrate the latest in multi-physics model to simulate a fuel element based on a particular NRE design built up from designer parameters.  The multi-physics modules can determine fuel integrity and fission product retention as a function of temperature and operating times, determine micro-structure evolution including cracking and grain growth.  The fuel element parameters are derived from high level NRE requirements via the integration of the IROC (Integrated Rocket Optimization Code), linked with PHOENIX, a program linking multi-physics modules through MOOSE (Multi-physics Object-Oriented Simulation Environment)  Ultimately, detailed safety related information including results of impact analyses through extensive hydro-codes such as PRONTO/SPH and radiation transport codes such as MACCS2.  This enables safety to be integrated in from the very beginning of the design process resulting in a much more optimized safety based nuclear rocket engine.
TDA Research, Inc. (TDA) proposes to develop a post-fire air purification system that consists of a particulate removal assembly, a sorbent bed to remove the combustion by-products generated by low intensity fires (such as HCN, HCl, SO2 and NH3) and an ambient temperature oxidation catalyst to eliminate any carbon monoxide (CO) and volatile organic compounds (VOCs).  The unit will be designed to rapidly restore the cabin air to a safe condition.

In Phase I, we will first evaluate the performance of individual components in flow experiments to identify the optimum bed geometry.  We will then design a breadboard prototype unit and evaluate its performance in an environmental chamber under representative conditions.  We will carry out detailed design of the purification system, integrating the particulate removal assembly, sorbent bed and the ambient temperature oxidation catalyst.  We will determine the weight and volume of the unit as well as the energy required to circulate the contaminated cabin air through the purifier.
Aeroelasticity plays an important role in the design and development of highly flexible flight vehicles and blended wing body configurations. The operating margins on these flight systems are limited by non-linear unsteady phenomena such as stall, flutter, gusts, limit cycle oscillations, vortex roll-up which exhibit strong coupling between the aero-loads and structural deformations. The use of high-fidelity time domain methods such as CFD/FEM during the design phase has been limited by the cost of computing the unsteady physics. In this proposal researchers from CRAFT Tech and Georgia Tech offer a collaborative inter-disciplinary design optimization approach to aeroelasticity problems with high fidelity aerodynamics analysis and structural dynamics. This approach is primarily feasible because of the development of a novel unsteady analysis procedure that reconstructs the unsteady dynamics with high accuracy and nominal cost. The reconstruction procedure combines CFD and FEM with a modified Proper Orthogonal Decomposition method and an Artificial Neural Network to simulate the unsteady aeroelastic features associated with different shape designs with good reliability. Furthermore, the process of reconstructing the unsteady solution permits the incorporation of control strategies and time variant system responses making it appealing for the aeroservoelasticity class of problems.
The development of a new generation of large, high power deployable solar arrays has been identified as the most significant challenge facing the development of solar electric propulsion (SEP) systems.  In response, innovative solar array structural concepts have been proposed including flexible thin-film solar arrays which roll like a carpet for stowage.  These systems are simple and reliable while also exhibiting high performance.  Rollable solar arrays have not yet reached a high enough technology readiness level (TRL) to be utilized as the primary solar array in a high-stakes mission.  The TRL of the current rollable solar array systems is hindered by their reliance on a particular manifestation of deployable slit-tubes which utilizes an open and unsupported slit and high-performance fiber-reinforced polymer (FRP) composite materials.  The FRP slit tubes are high performance and ideally suited to the ROSA system, but do not have sufficient test-heritage or widely accepted engineering tools to enable reliable and efficient structural predictions such as buckling strength or design optimization studies.  A slit-tube optimization loop including comprehensive testing and analysis as well as the evaluation of novel design features and manufacturing methods is proposed to improve roll out solar array technologies being considered for SEP.  The proposed technology will result in a library of slit-tube test data with analytical correlation, will increase the deployed strength over the state of the art by 4X and increase the state of the art TRL.
Innovative, low cost high performance technologies are critical to the affordability of future space missions.  Carbon/carbon (C/C) composites have significant advantages over metallic solutions. However, C/C composites are generally known to have high costs and protracted lead times. Recent efforts by ATK Aerospace Group and Plasma Processes have focused on increasing capability of 2D C/C, while reducing cost and lead-time. Optimization studies by ATK have reduced manufacturing schedule by up to 60&#37; and improved mechanical performance. Plasma Processes has developed protective coatings for C/C deposited via additive manufacturing techniques that have performed well in flight tests. These recent advances can reduce the cost and inert mass of future hypersonic and launch vehicles.  However, additional efforts are needed to optimize economical oxidative protective solutions for C/C.  The objective of a proposed Phase I is to merge advancements in C/C composite manufacturing with additive manufacturing coating application techniques to yield economical hot structures for future hypersonic vehicles.
Hybrid electric distributed propulsion (HEDP) systems have proven worthy for further consideration by approaching NASA's goals for N+2 and N+3 energy consumption, noise, emission and field length. The thermal management associated with these systems has been recognized as a major challenge to be overcome. ESAero's recent 2012 Phase I SBIR (NNX13CC24P) identified the radiator as a driving component within the thermal management system (TMS). Its design has profound first order effects on the weight, performance, and aerodynamic drag of the TMS, and second order effects on the weight and performance of the overall propulsion system. During the proposed Phase I SBIR, ESAero will upgrade the existing physics-based radiator design, analysis, and weight estimation conceptual design tool by improving the flexibility and fidelity of thermodynamic analysis and predicting the effects of integrating the radiator core within a well-designed duct. ESAero will call upon existing techniques to design a robust tool that more accurately predicts the "as-built" behavior of the component. These modifications are expected to dramatically improve the predicted weight and performance of the radiator and negate nearly all of the radiator drag by employing the Meredith Effect, as seen on the P-51 Mustang.
Spacecraft for NASA, DoD and commercial missions need higher power, higher voltage, and much lower cost solar arrays to enable a variety of very high power missions. Power for these missions is envisioned to reach from 30kW-300kW in the near term and to 1MW in the future. Conventional solar arrays are simply not up to the challenge for many reasons. High efficiency, space-qualified solar cells are in themselves costly, &gt; $250/Watt, and there is considerable additional cost associated with the large number of piece-parts and labor needed to assemble the cells into the Photovoltaic Assembly. The current approach has many assembly steps, and has evolved with only minor changes from solar arrays fabricated in the 1970s, sacrificing cost because of risk adverse incremental development. If a very low cost solar cell could be implemented, while being complemented by economical automated solar array integration processes, and having environmental durability, then extensive cost savings could be realized, thus enabling energy intensive next generation missions. The proposed innovation is a very low cost durable PVA which has integrated construction designed for manufacturability, and active array management for voltage and current regulation. By utilizing mature thin film CIGS technology, along with Vanguard proprietary coverglass replacement technology (CGR), and automated integration and lamination processes, an extremely thin flexible lightweight and low cost solar array can be realized.
ATA Engineering, Inc. proposes an STTR program to develop innovative tools and methods that will significantly improve the accuracy of random vibration response predictions for aerospace structures under critical inhomogeneous aeroacoustic loads. This will allow more accurate predictions of structural responses to be made, potentially reducing vehicle weight and cost and improving the reliability of these structures. Empirical wind tunnel test data will be used as a basis to develop innovative methods to characterize the surface fluctuating pressures encountered by launch vehicles during ascent, and then to accurately predict the random vibration environment caused by these loads. The wind tunnel test will measure both the surface fluctuating pressure and the resulting vibration in a flexible panel. Phase I will be spent performing pre-test engineering to reduce Phase II risk, generating drawings for construction of test articles, and deriving the test matrix for the Phase II wind tunnel test. The objective of Phase I is to demonstrate that the proposed Phase II wind tunnel test will be able to provide the test data necessary to improve predictions of fluctuating pressures and random vibration during ascent. 

Phase II will be used to perform the wind tunnel tests for compression corners, expansion corners, and protuberances. The vibration and fluctuating pressure data from these tests will be used to develop more accurate models to predict the auto- and cross-spectra of surface fluctuating pressures during ascent, followed by the development of coupling models to predict the resulting spacecraft structural vibrations. A critical improvement over current methods will be the inclusion of a statistical basis which will enable prediction of both mean and maximum expected environments. The experimental data in Phase II will also be made available to other researchers performing unsteady computational fluid dynamics simulations as validation data.
Traditional hydraulic actuation and control surface layout both limit span wise control of lift distribution, and require large volume within wing cross-section, ultimately reducing efficiency. Mounting and support structures for traditional actuators, also necessitate drag-inducing protrusions in otherwise ideally smooth airfoils. Consequently, hydraulic systems are heavy and energy intensive as compared to electromechanical counterparts. Coupling distributed EMAs with novel controls optimizing lift distribution in real-time during flight allows lighter, thinner, and more flexible wing structure. Multidisciplinary Design Optimization used to couple control formulation for any point in flight with aeroelastic model of the wing. Parametric distribution of EMAs will guide actuator placement and aid design and sizing of flexible wing system that maximizes L/D. Aurora has used both distributed local flow sensors and on-board fiber-optic strain sensors, which along with novel control algorithms allow for on-board, near real-time control calculations to be completed, creating adaptive wing shapes, and optimize L/D within the flight envelope.
The objective of this NASA Phase I SBIR program is to leverage lightweight, durable materials developed by NanoSonic for use within extra vehicular activity (EVA) space boots to provide the following benefits: weight reduction, increased durability/longevity and thermal protection/comfort.  NanoSonic will collaborate with ILC Dover, the manufacturer of the EVA space boot, to develop next-generation designs employing the adaptive thermal control materials described herein.  Next-generation designs will increase the comfort and productivity while reducing fatigue and injury risks provided to crew members.  Further, these next-generation EVA boot materials shall also provide enhanced instep support and enable better boot sizing as indexing.

To address the comfort and thermal concerns within the EVA boot, NanoSonic will work with ILC Dover, the world's leader in EVA spacesuits, who was recently awarded the contract by NASA to develop the Z-2 advanced spacesuit.  In addition to providing enhancements for foot indexing and thermal comfort, NanoSonic will work with ILC to ensure that the solutions developed herein provide weight savings and increased durability such that the EVA prototype boots developed in the Phase II effort will afford crew members increased comfort and productivity while reducing fatigue and injury risk.  The proposed program would start at TRL 5 and end at TRL 8 after a Phase II effort.
One cannot build a system-level Prognosis and Health Management (PHM) solution by cobbling together a bunch of existing prognostic techniques; it will have a very high rate of false-positive indications. On the other hand, if a system-level health management solution could identify the individual degradations and indictors associated with those degradations, and thereby decouple the problem into smaller pieces, the existing prognostic techniques could still be used to predict time to failure, and could therefore drive an effective Condition Based Maintenance and Decision Support System (CBM+).

Qualtech Systems, Inc. (QSI) and Vanderbilt University team seeks to develop a system-level diagnostic and prognostic process and a "sense and respond capability" which first uses error codes and discrete sensor values to correctly diagnose the system health including degradations and failures of sensors and components, and then invoke appropriate prognostic routines for assessment of remaining life and capability. Thus, QSI's Testability Engineering And Maintenance System (TEAMS) real-time reasoner will enable the use of many existing prognostics techniques in the broader context by decomposing the complex system into local datasets of degradations and associated sensor data sets, thereby limiting the problem-space for the prognostic techniques to their limited design scope. Indeed, it is well established in the contexts of parameter estimation and model-based fault identification (i.e., fault isolation and severity estimation) that feature selection and diagnosis, respectively, followed by parameter estimation provides major improvements in estimation performance (measured in terms of computational time as well as the standard deviations of the estimated parameters) when compared to full parameter estimation which provides biased estimates for all the parameters.
The Automated Ply Inspection (API) system autonomously inspects layups created by high speed automated fiber placement (AFP) machines. API comprises a high accuracy line scanner to measure surface topology of as-made layups driven by a precision articulated arm Robot to perform rapid surface scanning of a Layup after tape placement and layup. Key to API is efficient and robust software to read very large volumes of line scan data and analyze, classify and detect key Layup features very rapidly and reliably. The software retains only key features, filtering the raw data by two orders of magnitude to facilitate real-time data processing at high scan rates. Software also compares the location of as-made features (gaps, overlaps, drops and adds)with the NC program ("virtual layup") to identify and record only those as-made features that are out of tolerance.     API addresses many of NASA's objectives for this topic:   ? Manufacturing for launch vehicles  ? Innovative automated process (AFP)  ? Applies to reliable, large scale PMC structure  ? Applies to Autoclave and OOA AFP methods    API provides a powerful capability to enhance reliability of structures manufactured by AFP by automating a tedious and difficult manual task. In fact, the speed of AFP machines today has advanced such that manual inspection now takes as much time, and often more, than automated layup requires. API can significantly increase total AFP productivity (C-rate) and reduce cost by reducing Inspection time.  Flightware has enlisted the participation of two other small businesses in this program to contribute their experience and expertise as subcontractors for specific tasks. Furthermore we have attracted the interest of larger industry leaders who supply AFP equipment and manufacture AFP Aerospace parts in this program, because they recognize its potential value.      This API program is a manufacturing innovation subject to Executive Order 13329 "Encouraging Innovation in Manufacturing."
Integrated circuits in NASA spacecraft and Robotic Exploration Technologies that enable exploration of the solar system planets, moons and small bodies must operate over large temperature extremes and mitigate radiation effects that can result in upset or destruction of devices. Development of a reliable, high-performance nonvolatile memory (NVM) is critical to successful NASA explorations and development of robotic exploration technologies designed to operate in the extreme temperature, pressure and radiation environments of planetary and lunar surfaces. PrivaTran has previously demonstrated an electronically-programmable resistor as a NVM element. Initial static data retention testing has shown tolerance to several radiation types and high thermal stress, thereby demonstrating the potential for use in radiation-hardened circuits for extreme environments. Device materials and fabrication processes are compatible with high-temperature semiconductor manufacturing platforms utilizing wide-bandgap semiconductor materials. The PrivaTran NVM device uses standard materials as the active switching medium and device electrodes can be formed either in the substrate material or within the interconnect layers of the integrated circuit (IC). As a result, NVM arrays can be integrated with wide-band-gap semiconductor materials in a three-dimensional (3D) architecture, resulting in a high-density memory with superior NVM performance and significant savings in size, weight, power and cost.
Unmanned aerial systems (UAS) and, in particular, intelligent, autonomous aircraft operating in the National Airspace (NAS) have the potential to significantly impact modern society.  They could perform difficult and dangerous tasks such as fire fighting, border patrol, and search and rescue, and dull tasks such as surveying crops. The elimination of a cockpit and the pilots makes UAS operation attractive from an economic standpoint. In addition, much of the technology used for autonomy could benefit manned flight as a pilot's aid to help in tasks such as landing on an oilrig in the high seas.  Open questions remain, however, about how unmanned autonomous aerial vehicles can be safely incorporated into the NAS. UAS's operating in the NAS must sense and avoid other vehicles, follow air traffic commands, avoid the terrain and land without operator intervention, react to contingencies, and be reliable and cost-effective.

The current approach for UAS integration relies on radio links and the operator's acuity to direct them. Lost links, however, are unavoidable. UAS's must have the capability to make their own decisions based on information available via databases and information discovered by onboard sensors. Near Earth Autonomy proposes to develop technologies and capabilities leading to fully autonomous systems that are able to discover and adapt to unpredicted changes in their environment, and yet still accomplish the mission, with minimal or no human involvement. The proposal focuses on developing autonomy in the form of sensors and computer software that will enable UAS's of the future to operate safely in the NAS. Additionally, the proposal addresses how the technical challenges can be met and how the technology developed can be shown to be both trustworthy and commercially viable for general aviation. This is aligned with NASA's current initiative for safe integration of UASs in the national airspace led by Langley Research Center.
Reactive Innovations, LLC, proposes a Phase I SBIR program to develop a compact and lightweight electrochemical reactor to separate and pressurize carbon dioxide  from the Martian atmosphere.  Our approach builds on recently developed technology in our laboratory and others in selective separation based on electrochemically modulated facilitated transport. This process electrochemically pumps the bound CO2 across a membrane separator effectively concentrating and pressurizing it in a separate process stream.
Efficient nuclear-thermal propulsion requires heating a low molecular weight gas, typically hydrogen, to high temperature and expelling it through a nozzle. The higher the temperature and pressure, the higher the thrust and specific impulse. For ground test facilities that will be heating the gas to temperatures up to 4400 F (2425 C), the number of materials that can be used is severely limited. The need for compatibility with hot hydrogen limits the field even further. In this project, Ultramet will design, fabricate, and test a system for heating high-pressure hydrogen up to 2400 C. The system will comprise a resistively heated open-cell refractory carbide foam heating element and an oxide-lined rhenium tube to contain the heater. By passing an electric current through the foam ligaments, they can be heated to arbitrarily high temperatures, and the carbides are stable in hot hydrogen. In previous work, Ultramet has demonstrated the ability to make robust electrical connections to foam heaters that will tolerate high temperature operation. Unlike most other refractory metals, rhenium is both ductile and non-reactive with hydrogen. It is also very strong and creep-resistant at high temperature. Consequently, rhenium is the material of choice for the pressure vessel and other hydrogen-washed surfaces such as the convergent/divergent nozzle. In the immediate vicinity of the heater, a thin layer of zirconia or hafnia (both of which are compatible with rhenium up to their melting point) will be used to electrically insulate the rhenium from the foam heater.
This SBIR Phase I proposes to establish the feasibility of using a space qualifiable Field Programmable Gate Array (FPGA) based digital controller to autonomously acquire and wavelength lock a tunable seed laser to a specified atomic or molecular reference.  Successful development of this technology, due to its compact, efficient, and reliable design, is an important step towards enabling deployment of future space-based high spectral resolution lidar (HSRL) systems for remote sensing systems, as well as improving the autonomous performance of deployed and developing ground and flight-based HSRL systems.
High power, compact, reliable and affordable power amplifiers operating in the W-band (94 GHz region) are critical to realizing transmitters for many NASA missions and other significant applications for remote sensing and environmental measurements.  QuinStar Technology proposes novel approach for a family of solid state power amplifiers (SSPA) that will exceed the performance and operational requirements for measurement instruments and monitoring equipment of the future. Proposed approach is based on optimal combination of unique techniques for highly efficient and yet robust power combining, circuit integration and innovative packaging methods.  This also leads to affordable products suitable for space, airborne as well as terrestrial applications.  Key features of the proposed implementation are: scalability of power output, compact, lightweight, flexible architecture and high reliability with very significant potential for performance improvement and price reduction as MMIC device technology matures further.  Initial objective of proposed effort is to achieve greater than 50 Watts of power output at 94 GHz at greater than 20&#37; duty cycle and with 40 dB or more gain.  Phase I work will focus on innovative robust designs for power combining, packaging and select device/material s.  Phase I effort will lead to a producible and scalable design baseline that will be used in Phase II for manufacturing deployable products.
Measurement of magnetic fields provides valuable information about charged particles and plasma interactions in the solar system, and about planetary dynamics and compositions. Magnetometers are thus important instruments to have aboard spacecraft on exploration missions. We propose a magnetometer system that is compact, low-cost, light-weight and low-power. The system is based on a miniature rubidium magnetometer and gives scalar and full vector operation with accuracy and sensitivity beyond state-of-the-art.
NASA has unique non-contact precision metrology requirements for dimensionally inspecting the global position and orientation of large and highly-polished multi-segmented mirrors (in an as-installed configuration), such as those used on the James Webb Space Telescope.  SURVICE Metrology has assembled a world-class team of metrologists and optical physicists to identify and develop innovative approaches to accurately inspect the positional accuracy of mirror segments using non-contact methods.  In addition to our in-house staff of experts in metrology and optics, our team includes industry-recognized academic experts in metrology.  What is needed is the ability to accurately measure the global position and orientation of mirror segments in an as-installed configuration using non-contact means from a safe distance to allow measurements to be made with minimal risk to the asset.  SURVICE proposes to research and evaluate technologies under the Phase I effort with respect to feasibility, cost, and risk and downselect to the best candidate technology for development in a Phase II effort.

SURVICE brings demonstrated metrology systems integration success that we will apply to the subject NASA challenge.  We have multiple Phase II and Phase III success stories, have delivered custom metrology solutions.
Both autopilot systems and human pilots, particularly human pilots operating in instrument meteorological conditions, rely heavily on sensor feedback to safely control aircraft.  The loss of reliable information for even a single state feedback signal can easily initiate a chain of events that leads to an accident.  Even when hardware redundancy is employed, common-mode failures are a significant hazard that can make hardware redundancy ineffective for achieving the desired system reliability. For example, multiple pitot tubes can experience a common-mode failure during an icing event, depriving the pilot of vital airspeed information. The proposed virtual redundancy approach can significantly improve flight safety by identifying failed sensors and estimating the correct output values as replacements for those failed sensors.  Estimates are based on a rigorous statistical formulation that makes optimal use of all available information including feedback from all remaining physical sensors, nonlinear models of vehicle dynamics, and models of actuator and sensor responses. The proposed research will also develop strategies for enabling pilots to make effective use of the virtual sensor outputs, including guidance algorithms that identify a trajectory that maximizes the likelihood of maintaining safety of flight and cueing techniques that allow the pilot to follow the resulting trajectory while minimizing the increase in workload.
Existing and proposed missions with ambitious science goals demand ever larger primary mirrors which, in turn, require the development of new light-weight, low-cost mirror technologies.  For Phase 2, Vanguard Space Technologies (VST) proposes to deliver a 2.5 meter, composite, on-axis, telescope by building upon the success of the Phase I effort.  The telescope will be suitable for use on the Super BLAST-pol mission. VST proposes building upon the success and leveraging the lessons learned from previous technology demonstration programs, leading to a successful CDR that includes a final design with budgeted errors, a detailed manufacturing plan, and a mature recurring cost model and estimate. A CDR package and one high efficiency telescope system will be provided during Phase II.  The envisioned telescope system will feature 2X lower areal mass and comparable areal cost for Unit Two+ than BLAST.  The Super BLAST-pol team at UPenn is committed to flight test this new technology on the maiden flight in 2016.
A device is proposed that can track the electrical charge dispersion that is created when hyper velocity impact (HVI) occurs between two entities with a closing velocity greater than 1 km per second. This same device can measure the time of arrival of the charge wave front at transducers placed throughout the vehicle. Using the known speed of light minus the reactive effects of the skin of the vehicle on the "charge", the system can calculate the exact point of impact. Further, the nature of the charge dispersal wave front contains critical information as to the damage incurred as a result of the HVI. This information along with AE waveforms will be tested and analyzed to determine signatures for various types of damage created by HVI events.
Flight Works is proposing to expand its work in micro-gear-pumps for propulsion applications in order to provide a highly capable propulsion and attitude control system (ACS) for asteroid proximity operations, landers and return capsules. In traditional systems, larger thrusters, specific to each mission, must be employed to counter the gravity field of the target. Also, throttling these larger thrusters for proximity operations and landing is not a trivial task. With the pump, the need for these larger, more expensive thrusters is eliminated. Instead the pump allows increasing (or decreasing) and controlling the thrust of the attitude control thrusters to the levels required for operating in the target's gravity field by modulating the pump RPM/power. Typically, only a few tens of watts are needed for pump operations. Flight Works is prepared to develop and demonstrate a low cost micro-pump capable of significantly increasing pressure and flow rate to the thrusters, to define a roadmap for larger increases if warranted, and to plan Phase II activities in order to reach a TRL 7 by the end of that phase. The technology builds on Aerojet Rocketdyne's work for NASA's on-going Green Propellant Infusion Mission (GPIM) and use the non-toxic hydroxyl ammonium-nitrate (HAN) -based propellant AF-M315E which provides 50&#37; greater density-ISP than hydrazine. The micropump leverages the Air Force Research Lab's (AFRL) investments in pump-fed technologies for small spacecraft propulsion applications, which have led to steady state and pulsed hot fire tests with hydrazine and demonstrations with other propellants.
Researchers have been working on flare prediction for many decades. However, the best prediction result achieved by Falconer et al. for major flares, CMEs, and solar proton events (SPEs) is a probability of detection of 39&#37;, meaning that only 39&#37; of the events are correctly predicted. Existing flare prediction algorithms are mainly based on a combination of data, statistical analysis, and pattern recognition algorithms. A serious deficiency of these algorithms is that they do not include the constraints and predictive power of the basic equations of magnetohydrodynamics (MHD) that describe the dynamics of the plasma atmosphere. We propose a new approach to flare prediction based on combining a detailed data based description of the solar atmosphere with the equations of magnetohydrodynamics (MHD). In this approach, a subset of the MHD equations take data as input, and then predict physical quantities that are not measured but may be important for predicting flares. Since the MHD equations must be obeyed by the plasma, when combined with data they also provide new constraints on pattern recognition algorithms that search for correlations between the occurrence of a flare and the values of observed and MHD model predicted quantities that describe the pre-flare plasma.
Leiden Measurement Technology (LMT) will design and develop a low volume analyte separation, concentration, and transfer system (ConTech), that couples a Subcritical Water (SCW) Extractor with Solid Phase Extraction (SPE) technology to extract analytes from complex host matrixes (e.g., soil, regolith, ice) and transfers them to a broad range of analytical instruments in situ. The use of SCW eliminates the need for organic solvents while allowing polarity-based separation of trace levels (ppb or below) of a broad range of inorganic and organic species. The technology will be developed to minimize mass, volume and power-usage and for compatibility with state-of-art in situ instruments currently under development by NASA including: microfluidic based systems, bioarrays, gas chromatography, high performance liquid chromatography, UV fluorescence spectroscopy, Raman spectroscopy, and mass spectroscopy.

The specific objectives of the Phase I R&amp;D effort are:

1) Assemble a compact prototype SCW-SPE system capable of extracting, separating, trapping, concentrating, and transferring/delivering soluble
inorganic ions, polar organics, and non-polar organics.

2) Determine the system requirements (solid phase extraction materials,
volume, geometry, temperature, flow) needed for processing Mars relevant
organics in complex matrices. 

3)Optimize analyte recoveries and perform an end-to-end proof-of-concept with laboratory prototype. 

4)Determine power, mass and volume requirements needed to meet analytical requirements.

5) Develop a design for a Phase II system.
Returning a geological sample from the surface of Mars will require an ascent propulsion system with a comparatively large velocity change (delta-V) capability due to the relatively deep Martian gravity well. Consequently, a significant propellant mass will be required. Bringing that mass from Earth, while technically possible, would be impractical and grossly inefficient. Manufacturing propellant from the Martian atmosphere would be far more practical. Highly efficient electrolyzers for splitting carbon dioxide into carbon monoxide (CO) and oxygen (O2) have been demonstrated. These can be run off solar power and used to generate high-pressure propellant without the need for pumps. With a theoretical vacuum specific impulse (Isp) of 324 sec (1000 psia chamber pressure, 40:1 nozzle expansion ratio), an O2/CO propulsion system would provide higher Isp than a solid rocket, and only a small fraction of the propulsion system wet mass would have to be brought from Earth. Previous testing with O2/CO propellant at NASA GRC has demonstrated that ignition of this mixture is very difficult. In that work, spark igniters were used, and every test resulted in a catastrophic detonation and damage to equipment. In this project, Ultramet will develop a high-performance ignition system for use with O2/CO propellant that is based on resistively heated silicon carbide open-cell foam. Previous testing has demonstrated that by passing an electric current through it, the foam can be heated to 1300 C in just 2 seconds. By flowing the non-hypergolic bipropellant mixture through the foam, ignition will take place in a pseudo-homogeneous manner as the gases enter the foam rather than only in the isolated vicinity of the arc in a spark igniter. This will prevent propellant accumulation in the chamber and subsequent detonation. Safe, reliable ignition of O2/CO is an enabling technology for the use of in-situ manufactured propellants on Mars.
Ultramet and ARA Ablatives Laboratory previously developed and demonstrated advanced foam-reinforced carbon/phenolic ablators that offer substantially increased high heat flux performance and reduced weight relative to conventional ablators. The structure consisted of an ablator-filled foam front surface backed by Ultramet's highly insulating aerogel-filled foam. Arcjet testing was performed at NASA ARC to heat flux levels exceeding 1000 W/cm2, with the results showing a significantly reduced ablation rate compared to conventional chopped fiber ablators, and ablation behavior comparable to FM5055 at just one-third the density. It is apparent that the foam helps retain the char layer by physical reinforcement and/or that the network of interconnected passages allows pyrolysis gases to escape with less disruption of the char layer. In 2008, NASA ARC contracted ARA to perform initial development of a new TPS design involving integration of fully cured mid-density ablator blocks within a structural honeycomb reinforcement. The block ablator-in-honeycomb heat shield is envisioned to provide high atmospheric entry reliability due to the structural attachment integrity provided by the honeycomb lattice in the ablative material layer. Any ablator failure such as cracking or char layer delamination is anticipated to occur within individual honeycomb cells rather than over large areas. The architecture is anticipated to have broad potential application for missions that involve large-vehicle entries into planetary atmospheres. Multiple block layers can be used within individual honeycomb cells, such as an outer high-density ablator layer with lightweight insulation underneath. This concept was analytically shown to have significant mass advantages over a traditional through-thickness ablator approach. Ultramet's ablator/aerogel-filled foams have very good potential for this application, and the Ultramet-ARA team will establish initial feasibility in this project.
Interest in civilian use of small Unmanned Aerial Vehicles (UAVs) with Vertical Takeoff and Landing (VTOL) capability has increased greatly in recent years, and is expected to grow significantly in the future.  Research to date has focused on propulsion, batteries, sensors and autonomous control laws, but little attention has been paid to acoustic characteristics.  The generation and propagation of noise associated with small VTOL UAVs are not well understood and prediction tools have not been developed or validated for this class of vehicles.  Since public acceptance of these vehicles is crucial to their future in civilian roles, it is imperative that NASA acquire the analysis tools and an adequate understanding of the acoustic characteristics associated with these aircraft.  The objective of the proposed effort is to create a base of experimental data to characterize the noise generated by this class of vehicle and then to use this data to evaluate and enhance existing rotary-wing design and analysis tools in this area.
Aircraft Loss-Of-Control (LOC) has been a longstanding contributor to fatal aviation accidents.  Inappropriate pilot action for healthy aircraft, control failures, and vehicle impairment are frequent contributors to LOC accidents. These accidents could be reduced if an on-board system was available to immediately guide the pilot to a safe flight condition (including cases of control failure or vehicle impairment). Barron Associates previously developed and demonstrated (in pilot-in-the-loop simulations) a system for finding appropriate control input sequences to recovery from upset conditions, and for cueing pilots to follow these sequences.
The proposed work would add several innovative capabilities to the existing architecture.  One of the most significant proposed enhancements is the addition of adaptation to address off-nominal vehicle responses.  Off-nominal vehicle responses can occur for a number of reasons including adverse onboard conditions (e.g., actuator failures, engine failures, or airframe damage) and external hazards, especially icing.  The addition of adaptation capabilities will allow the proposed system to provide appropriate upset recovery guidance in cases of off-nominal vehicle response. The proposed system is also specifically designed to be robust to variations in pilot dynamic behavior as well as provide enhanced robustness to pilot deviations from the recommended recovery strategies.
Dropsondes are one of the primary atmospheric measurement tools available to researchers.  Current dropsondes are deployed with a free fall parachute trajectory, allowing no flight path control and requiring the deployment aircraft to fly close to the target.  Adding an extended, guided range capability to the dropsonde will allow much greater mission flexibility by providing significant geographic and temporal coverage of areas of interest.  Barron Associates, Inc. will accomplish this through an innovative winged dropsonde that launches from a regular dropsonde launch tube, and deploys wing and tail control surfaces, and a propeller, starts the engine, and executes the mission under horizontal, powered flight.  The Phase I vehicle will focus on avionics and sensor integration, vehicle prototyping and flight testing of a long-endurance version of the vehicle. The vehicle will be equipped with a pressure, temperature and humidity sensor and a wind sensor which is extended out the front of the vehicle to allow accurate measurement. The vehicle will also be equipped with gas sensors, a custom autopilot board and a long-range telemetry system.  High-turbulence operation is highly desirable and a portion of the Phase I effort will go towards researching the vehicle configuration and software enhancements necessary to support operations in a highly turbulent environment.  The end result of the Phase I will be a flight tested, long-endurance, guided dropsonde vehicle, and a feasible Phase II plan for enhancing the vehicle to support high-turbulent operations, allowing use for hurricane, volcanic plume, and wildfire atmospheric science.
Sustainable Innovations' signature electrochemical cell architecture provides a solution to NASA's search for regenerative separation technology enabling maximum hydrogen recovery from a stream containing water vapor (saturated), carbon monoxide (CO), and hydrocarbons including methane, acetylene, ethane, and ethylene, among others. Separation of hydrogen from mixed gaseous streams presents a significant technical challenge for various NASA applications. In addition, the ability to efficiently perform hydrogen purification presents an attractive economic opportunity.  Sustainable Innovations is developing a technology that extracts hydrogen from a mixed stream by electro-oxidization of the hydrogen and subsequent electro-reduction of the resultant protons in a separate chamber.  The process, when combined with an electrochemical cell architecture that is engineered to tolerate high differential pressure, can be used to separate and compress hydrogen in a single step.  The process is proven to be efficient, quiet, and highly reliable.  It requires no reciprocating compressor, so it is largely maintenance free.
Legacy refractory materials that have origins dating to the original Saturn program are commonly used in current launch facilities. Although they failure to meet the target requirements, they are the only approved material.  Our research team proposed to develop an ultra high temperature refractory system that uses a non-cement binder, a high temperature macro aggregate, and reactive nano aggregates.  The developed binder system will exhibit substantial improvements in strength and have functional limit of 4000F.
In Phase I Busek matured the design of an existing 15-kW laboratory thruster.  Magnetic modeling was performed to generate a circuit incorporating magnetic shielding.  Erosion modeling predicts extremely long lifetime and high throughput.  A detailed mechanical design of the thruster resulted in an overall assembly with specific mass &lt;3kg/kW.  Modal, dynamic and thermal analyses were performed to calculate resonance frequencies, mode shapes, stress and fatigue values and temperature limits.  Experiments using the existing laboratory thruster evaluated a modified anode/gas distributor and a B-field distribution representative of the proposed magnetic shielded configuration.  Performance results suggest similar efficiency and performance as the baseline thruster.  Visual observation of the plume illustrated the characteristics of magnetic shielding were achieved.
  
In Phase II Busek will complete the detailed design of the thruster and a center mounted hollow cathode.  A prototype unit will be fabricated and performance tested included limited duration testing at Busek.  Depending on facility availability the thruster will independently tested at GRC.  Busek will hold a MRR and CDR then fabricate, assemble, and fully test a qualification model thruster/cathode to raise the maturity to TRL 6.  The thruster will be delivered to NASA for extended duration testing to complete the qualification.
NASA has identified Nuclear Thermal Propulsion (NTP) as a propulsion concept which could provide the fastest trip times to Mars and as the preferred concept for human space travel. The current NASA Strategic Space Technology Investment Plan states NTP is a high priority technology needed for future human exploration of Mars. In order to perform component testing in support of NTP engine development, an efficient means for delivering high-flowrate, high-temperature hydrogen is required. Non-nuclear generation of the desired hydrogen flowrates and temperatures for ground test of NTP components and subsystems is problematic.  ACENT Laboratories is proposing development Hydrogen Wave Heater (HWH) for this application. The HWH is an innovative embodiment of a wave rotor. Wave rotors can be used as a primary compressor/heater or as a topping compressor/heater to multiply the temperature and pressure of an existing compression or heating process. These highly-scalable continuous-flow devices are capable of flow rates upwards of 100 lb/s and temperatures over 5000 F.
There is no rad hard SDRAM currently available to support DDR2 and DDR3 applications. Space Micro proposes to build a radiation hardened by design (RHBD) SDRAM memory, using a modified version of our HF-Core Memory Controller to solve all the single event effects issues (SEU, SEFI and multiple bit errors).  The RHBD SDRAM will be manufactured on known radiation characterized eDRAM (embedded DRAM) ASIC processes: either TSMC or IBM for a Phase II demonstration.  The resulting RH-eDRAM (our name for this device), fabricated on a 130 nm process, provides 128 Mbit of radiation hardened (SEU, SEFI, SEL and TID) memory, while a 90 nm IBM process would result in 512 Mbit of DRAM.  The RH-eDRAM solves the space reliability problems with a well-understood set of solutions applied:
The goal of any spacecraft trajectory design process is to identify a path that transfers a vehicle from its point of origin to some specific destination in the presence of path and mission level constraints. From the mission designer perspective, this process is divided into two primary tasks: (a) the identification of candidate startup arcs, and (b) the subsequent refinement of those solutions, via targeting or optimization processes, to meet some pre-defined mission requirements. The work proposed here seeks to address the first aspect directly, while addressing the second indirectly, using NASA's General Mission Analysis Tool (GMAT) as the underlying demonstration platform. Phase I of this effort is focused on developing a prototype for an Interactive Visual Analytics Tool (IVAT) for GMAT. The goal of the IVAT module is to provide a modern, interactive, preliminary design tool that allows analysts to more efficiently explore and mine the space of candidate solutions prior to selecting a specific mission for the refinement phase. The development leverages GMAT's Advanced Path Planning (APP) and Dynamical Systems Analysis Toolbox (DSAT), developed by DECISIVE ANALYTICS Corporation (DAC). IVAT is envisioned as a preliminary design tool that can be readily integrated with gradient based optimal or sub-optimal refinement tools, such as but not limited to those provided by GMAT. However, for this effort we focus on GMAT as our selected technology demonstration platform.
Power systems are the core heartbeat of any advanced vehicle.  Reliability and flexibility of these systems are therefore of the highest priority.  This Phase 1 project proposes a highly efficient and modular isolated bidirectional DC converter for battery energy applications.  GridBridge is utilizing advanced DC converter topologies for modernization of the today's electrical distribution power grid and will translate work into high priority NASA power system applications, demonstrating transferability, robustness, and scalability.  This bidirectional DC converter offers an extremely high power density and will utilize a novel hybrid resonance and PWM technique to achieve.  It will also offer NASA the flexibility for many power system topologies, including: distributing large single cells throughout the vehicle, use of smaller cells in a centralized location, or a combination banked smaller cells distributed throughout the system.  This is accomplished through independent charging and discharging control of state-of-charge and state-of-health for each battery module, inherent active maximum current limit and short-circuit protection, and ease of module balancing.
Shape Change Technologies is developing a radical new technique for the fabrication of Shape Memory alloys, such as TiNi and its ternary alloys of Hf, Zr, and Cu. The technique utilizes these components as chloride feedstock, which are then decomposed onto a substrate.  As the technique involves atom by atom mixing, the microstructure should be both pure and single phase, improving the fatigue life over diffusion-based fabrication methods. 
    This technique also allows for user selected transformation temperatures over a wide temperature range, user selected external forms and internal geometry allowing for fast acting, high power actuators. By making thin foams and sheets, vibration isolation   sheets can be used for integration into composite materials.     The technique is a radical departure from conventional ingot processing, and will enable applications in high and low temperature actuator and switches in engines, and for thermal energy recovery systems in commercial applications.
This effort proposes to design, build, and demonstrate a new instrument for icing research and flight safety capable of discriminating liquid water from ice while simultaneously measuring the diameter, velocity, and temperature of droplets or the velocity and size for ice crystals. From these individual particle characteristics the total liquid water content (LWC) and the total water content (TWC) of the flow may be found. This non-intrusive, laser-based, point measurement diagnostic will operate in an off-axis, backscatter configuration at a range of working distances appropriate to characterize laboratory-scale experiments, icing tunnel flows, free jet test facilities, or flight conditions at altitude.
The proposed instrument will apply phase-Doppler interferometry, polarization ratio phase discrimination, droplet rainbow thermometry, and cross-polarization imaging to each particle measured. This will provide joint measures of liquid/solid phase, velocity, diameter or particle size, and droplet temperature. Furthermore, there is redundancy built into the measurements. For instance, the droplet diameter can be measured both by phase-Doppler interferometry and by rainbow thermometry and all four measurement techniques can discriminate solid ice from liquid droplets. While no single instrument can measure all possible cloud droplets, the proposed instrument can be configured to measure droplets from as small as 3 um to larger than 3 mm in diameter.
Systima Technologies, Inc. is developing a non-catalytic ignition technology for advanced green ionic salt monopropellants such as HAN-based monopropellant AF-M315E.  Green (non-hazardous, low toxicity) monopropellants such as AF-M315E offer significant advantages in performance and reduced handling infrastructure for vehicles and payloads compared to traditional hydrazine systems.  Systima's innovative ignition technology does not require a catalyst bed, thus avoiding the need to pre-heat the thruster chamber, is light weight, and operates with very low power.  This approach is well suited for applications that require a lower system weight, less power consumption and increased thruster lifetime, and is also well suited for auxiliary power units (APU's).  The Phase I program will establish parameters for non-catalytic ignition of AF-M315E.  In Phase II we will conduct extended life hot-fire testing, evaluate system performance, and identify paths to flight demonstration in collaboration with Aerojet Rocketdyne.
The NASA Phase I program would develop and demonstrate semiconductor nanomembrane (NM) based flight sensors and arrays on flexible substrates, using SOI (Silicon on Insulator) silicon NM technique in combination with our pioneering HybridsilTM copolymer nanocomposite materials. Specifically, ultrathin nanostructured sensor skins with integrated interconnect elements and electronic devices that can be applied to new or existing wind tunnel models for skin friction analysis would be developed. NanoSonic has demonstrated the feasibility of NM transducer materials in such sensor skins for the measurement of flow-induced skin friction and pressure. Early experimental results have compared very favorably with data from other sensor gages.Major improvements from the previous Metal RubberTM based sensor include faster response time and less temperature dependence due to the high carrier mobility with the inorganic NMs. During this NASA STTR program, a semiconductor NM based distributed sensor array will be developed (Phase I) and deployed to measure in-flight (Phase II) the surface properties on an airplane wing surface. The properties that will be measured will include shear stress and pressure. With the high frequency response of the NM sensors (100 kHz), it is possible that laminar to turbulence transition can be detected. In phase I, an existing Mach 0.7 wind tunnel will be used to check out the performance of the sensors.
This SBIR Phase I effort will demonstrate the feasibility of developing a fully packaged, efficient, short pulse, high repetition rate frequency doubled micro-chip laser for use in  NASA-JPL's Time Resolved Raman Spectrometer (TRRS) to analyze elemental and mineral compositions in remote planetary environments.  Time Resolved Raman Spectroscopy can identify mineral content in natural geological context with enhanced discrimination from impurity-based interfering fluorescence making it a leading candidate for in situ exploration of planetary bodies.  The combination of a high repetition rate, short pulse width laser with commercially available single photon avalanche detector (SPAD) arrays will enable the development of a robust, compact, electrically efficient TRRS instrument that is well suited for space-based use.
To meet the NASA's need for innovative technologies that decrease turn-around time for inspections and assessments for safe operations of aircraft and spacecraft,  X-wave Innovations, Inc. (XII), teaming up with Prof. Fuh-Gwo Yuan at North Carolina State University (NCSU), proposes to develop an innovative guided-wave based Time-Reversal Tomography (TRT) technology and Bayesian Framework based Damage Segmentation (BFDS) technology for finite-size damage detection and characterization in complex structures.  This framework provides a means for evaluation of the Model-Assisted Probability of Detection (MAPOD) and Confidence Level (CL) for damage characterization in the context of Structural Health Monitoring (SHM).
Thermal control systems are sized for the maximum heat load in the warmest continuous environment.  This design process results in a larger radiator surface area than is needed for portions of a mission where the heat load is lower or the environment is colder.  Now that NASA is refocusing its human missions to the much colder areas of exploration beyond Low Earth Orbit (LEO), the need for a variable heat rejection thermal control system increases.  This SBIR project by ACT will develop a Variable Heat Rejection multi Loop Heat Pipe (VHR/mLHP) Radiator where the variable heat rejection feature will be provided by independently controlling the heat load for each LHP by heating and cooling the compensation chamber The proposed approach will use a series of individually controlled loop heat pipes (LHPs) receiving heat from a single phase pumped loop to perform the function of variable heat rejection while still closely controlling the loop setpoint temperature.  This technology development effort has three main objectives that build on mature LHP technology: optimization of the liquid/LHP heat exchanger, investigation of the use of heaters or thermoelectrics for temperature control and shutdown of the individual LHPs, and characterization of the system performance when multiple LHPs are assembled in series. The purpose of this program is to develop a holistic approach for a variable heat rejection system design consisting of multiple heat exchangers and multiple individually controlled LHPs which can achieve high turn down ratios for variable heat rejection while increasing the system reliability and reducing the system power and mass.  The proposed concept is flexible, as various configurations could be obtained to meet different mission parameters.  The main advantage of this technology development effort is that it leverages already proven technologies to integrate a novel system that can achieve robust variable heat rejection.
SSCI proposes to develop and test the Sensor integritY Management and Prognostics Technology with On-line fault Mitigation (SYMPTOM) system. The SYMPTOM assures system integrity by fusing available information from a variety of similar and dissimilar sensors and other sources with advanced signal processing and dynamic equations of motion to arrive at high-confidence estimates of the current sensor health, rapidly and accurately detect and isolate the fault, and mitigate its effect before the information from the sensor has been sent to the flight controller and the cockpit display. The SYMPTOM system uses all available information relevant for flight-critical sensor Fault Detection, Identification and Accommodation (FDIA), fuses it to build virtual and software sensors, and applies advanced statistical tests, nonlinear estimation and prediction,  and parameter estimation schemes to accurately detect, isolate and accommodate the faults in both individual sensors and sensor suites. The SYMPTOM leverages our previous work on single-thread sensor FDIA. In Phase II of the project, Boeing Phantom Works (Dr. Kevin Wise) will provide technical and commercialization support.
Wrong decisions during the missions can lead to an unsafe condition or immediate failure, while correct decisions can help continue the missions even from faulty conditions. In view of the lessons learned from mishaps, i.e., failed space missions, it is imminent that reliability analysis and risk assessment are kept in sync with space system design as it evolves from the concept through preliminary design, detailed design, production, and operations. From the successful proof-of-concept demonstration for the proposal solution in Phase I, Qualtech Systems, Inc. (QSI) in collaboration with Dr. John Sheppard from Montana State University (MSU) proposes to architect the solution for continuous real-time health monitoring and diagnosis, automatically generating current risk assessment for Loss of Mission, Loss of Crew, Loss of Vehicle during vehicle operations while taking into account the current health of the vehicle and operational modes and phases in Phase II. The QSI-MSU team plans to emphasize advancement in the six following areas: (a) enhancement of the existing EPS model/modeling a new target system, (b) dynamic generation of fault-tree by TEAMS-RDS&amp;#174;, (c) expansion of risk modeling and learning, (d) expansion of risk assessment capabilities, (e) Automatic information exchange between TEAMS-RDS&amp;#174; reasoner and CTBN reasoner for both design-time and run-time, and (f) enhancement and incorporation of the risk visualization tool capability into web-based TEAMS-RDS&amp;#174; dashboard. The solution architecture will provide the ability for the crew to assess and select the "right" mitigation option for component failures and subsequently update the health diagnosis and risk assessment given the executed mitigation plan.
Future NASA exploration missions require high specific power (&gt;500 W/kg) solar arrays.  To increase cell efficiency while reducing weight and maintaining structural integrity, we propose an approach to cell design that involves the use of quantum dots and epitaxial lift-off.  In the near term, this approach will allow us to improve on what are currently the best space solar cells available in terms of efficiency and material properties for space utilization.  In the proposed Phase I project, MicroLink and its collaborator, Rochester Institute of Technology, will incorporate InAs quantum dots (QDs) in the InGaAs subcell of an InGaP/GaAs/InGaAs triple-junction solar cell to increase radiation tolerance and efficiency, thereby improving end-of-life performance of the solar cell by &gt;5&#37;.  By incorporating quantum dots into the InGaAs third cell, we will also extend the wavelength absorption range of InGaAs cell to beyond 1,250 nm, thereby increasing the current produced in the bottom subcell.  The quantum dot-enhanced subcell will be the last grown solar cell in an inverted metamorphic (IMM) format on GaAs and will be compatible with MicroLink's epitaxial lift-off (ELO) process.  Innovative light management techniques such as reflective metal back contact will be employed to increase absorption in the solar cell by promoting photon recycling.
Systima in collaboration with University of Washington is developing a high performance injection system for advanced green monopropellant AF-M315E micropropulsion systems (0.1 &amp;#150; 1.0 N) for small- and micro-satellites and cubesats (100 kg-500 kg and &lt;100 kg).  The monopropellant has low-toxicity making it easy to store, integrate into modular designs and launch without added costs associated with handling toxic propellants such as hydrazine.  The injector is a critical component that is designed to enhance combustion and optimize microthruster performance.  In the Phase I program, Systima and UW completed proof-of-concept tests that demonstrated the injector technical concept and system advantages.  In the Phase II program we will develop a prototype injector design, conduct injector performance testing and workhorse microthruster hot-fire tests with AF-M315E.  This effort will result in a monopropellant injection system for modular microthruster system designs that meets the needs of current and future small- and micro-satellites for NASA missions, commercial and military customers.
NASA and Boeing Phantom Works have been working on the  Elastically Shaped Future Vehicle Concept (ESFVC) and have shown that aircraft with elastically shaped wings  have great potential to save fuel by minimizing drag. Main feature of the ESFVC is that it uses Variable Camber Continuous Trailing Edge Flap (VCC-TEF) flight control surfaces to bend &amp; twist the wing to a "drooped wing" configuration that was shown capable of achieving drag reduction. However, elastic wings are characterized by reduced stiffness, which may result in lower flutter margins. Hence flutter suppression is an important aspect of the ESFVC. In order to address this technical challenge, SSCI and Boeing Phantom Works propose to design, implement and test an innovative  Drag Identification &amp; Reduction Technology (DIRECT) approach to drag reduction and flutter suppression in flexible-wing aircraft. The approach is based on leveraging prior work by SSCI and includes on-line identification of flutter modes using real-time subspace identification techniques, flutter suppression control law development, and the selection of the optimal control allocation that minimizes drag based on the CFD/FEA analysis. The approach will be tested on aircraft dynamics simulation, developed by Boeing, that includes a large number of relevant flexible modes. Boeing Phantom Works (Mr. James Urnes, Sr) will provide technical and commercialization support under the project.
In this Phase II STTR project, RNET and its subcontractors are proposing to fully develop an empirical performance optimization tool called OrFPGA that efficiently explores the "user tunable" parameter space of an FPGA design and assists in deducing the near optimal design in terms of timing score, device utilization, and power consumption. The tunable parameter space will include IPCore parameters, HDL and HLS code constructs, and parameter settings for the vendor's design tools. Special automation tools will be developed to facilitate annotation of HDL/HLS code and design tool scripts. The computational magnitude of empirical performance tuning of FPGA designs will be addressed by novel machine learning based search algorithms requiring minimal empirical evaluations, computational steering, leveraging intermediate performance analysis results, and parallelization techniques. The tool will support specification of prioritized performance metrics, easy-to-use interfaces for defining the parameter space, and intuitive visualization of performance models. The user will be able to automatically deduce the best environment settings the chip and also accurately identify the optimal power consumption through optional real-time power monitoring. The benefits of the tool to NASA will be demonstrated in terms of performance metrics and cost benefits (user productivity) using real NASA designs that are used in space missions.
PSI proposes to develop a rechargeable lithium metal cell with energy density &gt;400Wh/kg.  This represents a &gt;70&#37; increase as compared to similarly constructed cells using commercial off the shelf components.  Further, the use of lithium metal eliminates the need to produce the anode material and electrode, simplifying cell construction and thus reducing cost.  The Phase I work will build upon PSI's previous efforts focused on forming a high power cell design.  These efforts have demonstrated the ability to construct pouch sized cells that charge and discharge without the formation of dendrites.  During Phase I, PSI will build high energy pouch cells and demonstrate the cycling efficiency of its lithium metal cell design.  A specialized electrolyte will be developed that maximizes the cycle life and offers comparable performance to conventional electrolytes designed for graphite cells.  A composite separator tailored to efficiently operate with the electrolyte will be used to provide a reduced diffusion distance between the anode and cathode.  Phase I testing will demonstrate each component can be scaled to allow stable cycling of Ah pouch cells.  Phase II will focus on building multi amp hour cells that achieve the targeted energy density, 400Wh/kg.
To-date, the realization of small-scale, high-performance liquid bipropellant rocket engines has largely been limited by the inability to operate at high chamber pressures in a regeneratively-cooled environment using on-board pumps for propellant pressurization. 

Ventions seeks to fulfill this critical need by using a novel fabrication scheme that builds on previously-demonstrated technologies (under DARPA and NASA sponsored efforts) to design, fabricate and hot-fire test a pump-fed, 3,000lbf LOX/RP propulsion system.
SSCI, in collaboration with University of Texas, Austin (UTA), proposes to develop, integrate, implement and test a novel framework for the design and performance evaluation of Guidance, Naviagation &amp; Control algorithms for spacecraft Autonomous Rendezvous and Docking (AR\&amp;D). The framework is referred to as the GUARD (GUidance, Navigation and Control for AR\&amp;D), and will include a suite of advanced navigation, optimal trajectory generation, Failure Detection and Identification (FDI), and constrained adaptive fault-tolerant guidance and control algorithms that can be tailored to a specific AR&amp;D mission and tested with respect to a given set of requirements and specifications. Specific Phase I tasks include: (i) Develop GN&amp;C-oriented and high-fidelity dynamic models for AR&amp;D; (ii) Develop Optimal AR&amp;D Algorithms under non-convex constraints; (iii) Develop Constrained Control Algorithms; (iv) Integrate the G&amp;C Algorithms with Vision-based Navigation Algorithm; and (v)  Carry out initial simulation testing &amp; performance evaluation. Phase II will be focused on further maturation of the approach, rigorous Verification and Validation of the overall GUARD system, and its implementation on an experimental test bed at UTA. Dr. Behcet Acikmese of UTA will be our subcontractor under the project.
Virtually all optical information gathering instruments benefit from greater aperture. For space-based instruments whose geometries are constrained by the launch vehicle, increasing the aperture requires deployment of some aspect of the optical train and then the precise and dynamically stable latching of the deployed components into defined positions. Existing latching technology is too inaccurate, unstable, and expensive for use in many NASA missions.
Physical Sciences Inc. (PSI) will develop a simple, scalable latching technology by applying precision engineering approaches from previous developments that carefully manages the friction and strain energy stored internal to the latching mechanism. The result will be a small, low-cost latching system with sub-micron positional repeatability and dynamic stability.
During the Phase I efforts, the PSI team will design, build, and test a latch for a cubesat-scale application. In future phases, PSI will fully qualify the device and demonstrate its performance when integrated into a complete deployable optical system
This Phase I SBIR will establish the feasibility of developing compact, robust, integrated components suitable for atomic interferometry.  AdvR's design is enabled by capitalizing on robust, well-commercialized, low-noise telecom components with high reliability and declining costs which will help to drive the widespread deployment of this system.  The key innovation is the combination of current telecom-based fiber laser and modulator technology with periodically-poled waveguide technology to produce tunable laser light at rubidium D1 and D2 wavelengths (and expandable to other alkalis) using second harmonic generation (SHG).  With this technology, multiple channels can be independently tuned to produce the fields needed for addressing atomic states in atom interferometers and clocks.  In addition, this technology could be useful in the development cold-atom inertial sensors and gyroscopes.
An automated in-space recycling system for 3D printer feedstock will provide game-changing resupply benefits including but not limited to launch mass reduction, mission reliability increases, and decreased reliance on resupply from Earth.  To bring these benefits to ISS in the near term, Made In Space proposes the further development of their unique recycling system, called R3DO, for transforming ABS plastic parts on ISS into 3D printer filament feedstock.

R3DO leverages Made In Space's knowledge of the extrusion process in microgravity, which enables 3D printing in space. R3DO's patent-pending technologies designed to meet NASA ISS requirements, and include multiple unique innovations such as filament use in microgravity, the low-power heating system, microgravity stabilization, material control, breaker plate migration, material-filter interactions, cooling characteristics, and safety mechanisms. 

Made In Space has developed and tested four prototype iterations of R3DO in the lab, to verify that the recycler is capable of recycling 3D printed material into feedstock and that that feedstock can be used with Made In Space printers.  Further, Made In Space has flown one of these prototypes on several microgravity flights to verify that it is capable of recycling ABS plastic and extruding feedstock in microgravity. Feedstock extruded in microgravity was then used to successfully print parts using Made In Space 3D printers.

For Phase 1 development, Made In Space will conduct a feasibility study and create a bench-top proof of concept of the full ISS system, based on the aforementioned prototypes, with a planned Technology Readiness Level ("TRL") of 5. Phase 2 will produce an Engineering Test Unit and accumulate data at TRL 6, and Phase 3 will feature the manufacturing of a Flight Unit, integration with the ISS and commercial applications, demonstrating TRL 9.
Peregrine will bring together recent laboratory developments and mature the technology so that complete mirror and telescope assemblies can be reliably and robustly produced. This proposed innovation will lower the cost of space mirrors from their current state of the art of $6.4 m/m2 to less than $1.6 m/m2 while maintaining low weight, high stiffness and high performance for x-ray, neutron and UV/optical mirrors.
This SBIR will adapt and demonstrate a low cost flexible method of manufacturing channel wall liquid rocket nozzles and combustors, while providing developers a means to manufacture more complex designs for improved engine performance.
Current channel wall engine concepts are limited by capabilities of available manufacturing methods.  This SBIR will provide a cold, non-chemical, low load alternative while supporting more complex liner designs.  It will enable features such as cooling channels with complex patterns, bifurcations, flow trips, varying width and depth, thin hot walls, negative wall taper, more accurately placed channel walls and more complex liner contours.
Ormond will work together with contacts at NASA and Aerojet Rocketdyne during Phase I to provide demonstration coupons of current engine concepts and to identify additional design options that can be incorporated through use of the proposed technology.  Cost and technical feasibility will be demonstrated.
A Phase II program will result in a TRL-6 level means of machining channel combustor and nozzle liners.  Scalability to SSME class of engines will be addressed.  
Government and commercial applications that may benefit from the proposed technology development include channel wall liquid rocket engines, ground based turbine generators, advanced turbine blades, scramjets, space optics, and down-hole oil well tooling.
The defense and the commercial sectors in US have been undergoing severe energy issues, with the prices and demand of fuel increasing over the years. Thus investigations into advanced fuel efficient designs have become inevitable. With increase in air traffic, environmental concerns of noise and emissions have also been brought to the forefront. This has resulted in NASA's ambitious N+3 vision, as exemplified in the Subsonic Fixed Wing projects's four corners of the design trade space. Also, the burgeoning interest in UAS platforms promises significant departures from traditional aircraft designs. To enable introduction of new aircraft into the inventory, the conceptual design of advanced concepts is critical. However, the aircraft design community realizes a need for introducing physics based analysis early in the design space. In particular weight estimates based on statistical relations are inadequate for new concepts, and there is a need for improved weight estimation. For this purpose, Intelligent Automation proposes VaC-CADO, a variable complexity conceptual aircraft design tool for the design of advanced airplanes by combining multi-fidelity optimization and MDO with FEM-based weight estimation. This is a novel technique leveraging on state-of-the-art in aircraft design and enhancing it using our extensive experience in this field.
Development of the CESI focal plane and optics technology will lead to miniaturized hyperspectral and SWIR-band spectral imaging instrumentation compatible with CubeSat and other nanosat platforms.  The project will implement the technology by developing a CubeSat-compatible SEMM instrument for global mapping of atmospheric methane concentrations. 
Specific Phase I technical objectives include:
- Perform a trade study comparing the performance potential of alternate concepts for a miniaturized spectrometer with respect to the methane mapping mission. 
- Demonstrate that the image of a scene collected through an interferometer is a product of the scene radiance pattern with the interferogram.
- Build a laboratory prototype and demonstrate enhanced detection of a multi-line molecular absorption band.
- Test novel detector devises suitable for high-gain, low-noise SWIR imaging in a nanosat setting.
- Develop the instrument architecture for SEMM and validate the concept analytically by a radiometric model.
- Design the high sensitivity, low-noise SWIR focal plane for SEMM.
The CESI project is undertaken by Wavefront LLC with the Space Dynamics Lab (SDL) collaborating as the research institution.  The key personnel are the Project Manager and the Principle Investigator (from Wavefront) and the scientists (from SDL).  The duration of Phase I is 12 months.

During Phase II, SDL will prototype the complete CESI instrument incorporating Wavefront's novel high-sensitivity focal plane and readout over 24-month duration.
In this project Orbital Technologies Corporation (ORBITEC) will utilize its unique vortex propulsion technology to develop a high-capacity heating system to heat hydrogen to extremely high temperature levels.  The heated hydrogen is to be used for test purposes for nuclear rocket propulsion simulations and total exhaust recovery applications.  Our vortex rocket propulsion system is able to reliably and repeatedly operate at very high levels of reliability and operating temperature.  This has been demonstrated through a large number of tests conducted over more than a decade using many different propellant combinations and engine sizes.   The ORBITEC Vortex is an ideal thermal energy source for the needed hydrogen heating application.  In phase 1, two hydrogen heating system concepts  (based on the vortex approach) will be analyzed.  Basic breadboard systems will be constructed and tested.and evaluated.  The feasibility of extended duration hot hydrogen production will be demonstrated.  In phase 2/3, a larger operational system will be developed, tested, delivered, and installed at the NASA Stennis Space Center.
As HEDP systems have proven worthy of further consideration by approaching NASA's goals for N+2 and N+3 energy consumption, noise, emission and field length, conceptual design tools to expedite the design cycle are desired. During this Phase I effort ESAero will progress the development of the hybrid-electric distributed propulsion (HEDP) TOGW tool developed in the previous Phase I SBIR (NNX13CC24P) by producing a physics-based wing structure analysis and weight estimation module. The layout of the structural members will be estimated using heuristic trends and top-level design assumptions, and the members will be sized according to classical beam theory. The interaction between HEDP configuration and aircraft weight is important to understand, as one primary advantage of the configuration is the ability to place smaller propulsors at virtually any location on the aircraft, leveraging pre-existing airframe supports. By delving into the structural analysis of HEDP designs, progress can be made toward determining how sensitive aircraft structural weight is to propulsion configuration. This new module will replace the modified, empirically based equations used in the current TOGW framework. By incorporating this capability, the novel architectures and configurations of HEDP systems, as well as other advanced aircraft concepts, could be analyzed and sized with greater fidelity. Furthermore, this effort may start to unravel concerns over other structural members paving the way for further investigation in a Phase II. Other potential Phase II tasks may include integrating this structural analysis and weight estimation into other conceptual design tools, such as OpenVSP.
Future human spacecraft will venture far beyond the relatively benign environment of low Earth orbit. They will transit through the deep space, but they may encounter warm transient environments such as low lunar orbit. Some spacecraft elements may be launched untended and would operate at relatively low power levels as they transit to their final destination. The combination of extreme environments and high turndown capability will be a major challenge for spacecraft thermal control systems.  Thermal switches are among the thermal control devices that are required and can dissipate a wide range of heat loads in widely varying environments while using fewer of the limited spacecraft mass, volume and power resources.  This SBIR project proposed by ACT will develop a low mass and high conduction ratio two-phase thermal switch as a thermal control system component for human spacecraft. The proposed device could work in thermal switch regime or in variable conductance regime while the set point can be changed remotely.  A trade study will be conducted to define the three features of the low mass two-phase thermal switch and demonstrate the feasability of the concept.  A preliminary full scale prototype will be designed, fabricated and tested at the end of the Phase I program.
This project aims to improve conventional lightning strike protection in composite aircraft and proposes a novel method to monitor structures for damage upon lightning strike.   Metallic fasteners joining composite parts must be properly grounded to reduce lightning damage and fire risk. Composite panels in the most critical areas e.g., near fuel tanks, incorporate lightning strike protection (LSP), an outer ply of conductive foil to handle large currents in the event of a lightning strike. Direct Write conductor traces deposited along fastener lines will connect fasteners together, via coated countersinks.   The proposed improvement will be demonstrated through Direct Effect Lightning Testing.  In addition, the Company's Direct Write process will be used to print SansEC sensors onto composite materials, demonstrating an effective method of sensor integration.  Open circuit resonator patterns will be used to detect cracking through shifts in resonant frequency.
NASA's long range goals of reducing the fuel consumption by 30&#37; and increasing fuel efficiency by 35&#37; can be partially accomplished through increasing engine operation temperatures.  As a result, the disk section is desired to operate in increasingly higher temperatures, which will subject it to additional degradation mechanisms of oxidation and hot corrosion.  One approach to enhance the temperature capability of these systems is through the incorporation of environmental protective coatings which can provide resistance from oxidation and hot corrosion.  Research is proposed here to optimize the use of advanced coating manufacturing techniques designed to enable the affordable application of environmental protective coatings having enhanced resistance to hot corrosion and oxidation to allow operation at the desired high temperature engine environments.  Advanced testing conditions will be used to simulate real world conditions and demonstrate the performance of the deposited coatings in these conditions.  This approach is envisioned to aid the development of advanced coatings required to protect the surface of turbine disk components at higher temperatures desired for fuel and thrust operationally improvement without inducing significant fatigue debit.  Advanced coating systems will be applied in this work onto coupons, and subcomponents to demonstrate coating capability and allow simulated engine environment testing in follow on programs. Success in meeting the objectives will significantly aid the temperature capability of turbine disk components, allowing significant fuel efficiency and thrust increases for turbine engines.
Future Venus or Comet mission architectures may feature robotic sampling systems comprised of a Sampling Tool and Deployment Mechanism.  Since 2005, Honeybee has been developing extreme-temperature motors, position sensors, brakes, and gearboxes, resulting in multiple successful demonstrations of component-level technologies under Venus-like environmental conditions.

An important next step toward a viable Venus or Comet surface mission architecture is to combine these components and raise the TRL of the total sampling system including the Deployment Mechanism.  The proposed work will leverage component development to date by integrating extreme temperature actuators with functional elements to demonstrate a complete multi-DOF Deployment Mechanism suitable for candidate surface missions.
During this Phase I effort ESAero will draw upon its knowledge of hybrid-electric propulsion system design and analysis for fixed wing aircraft to investigate the potential benefits of incorporating such systems into rotorcraft designs. Past rotorcraft studies have been conducted in conjunction with Electricore, Inc. and an industry prime, to develop hybrid propulsion system trade studies and develop databases for hybrid propulsion system worthy components. This knowledge will be leveraged to investigate potential areas of improvement including energy consumption, weight, overall efficiency, and safety. Implementing hybrid-electric systems could potentially remove redundant systems, reduce turbine size and allow for electrically powered emergency decent. In addition, decoupled energy management has shown potential benefits for fixed wing aircraft, allowing propulsors to be placed virtually anywhere around the aircraft. The potential benefit specific to rotorcraft may mean a broadening of configuration possibilities.
Systima in collaboration with the University of Washington will develop a high performance, advanced green monopropellant microthruster (0.1 &amp;#150; 1.0 N) for small- and micro-satellites.  The microthruster utilizes a high energy density HAN-based monopropellant AF-M315E, and a novel injection system to maximize thruster performance.  The propellant is non-toxic making it easy to store, integrate into modular designs and launch without added costs associated with handling toxic propellants such as hydrazine.  Phase I will focus on development of the microthruster propellant injection system to deliver propellant to a miniaturized catalyst bed to provide fast response while maintaining the life of the catalyst bed.  In Phase II these systems will be integrated into the full microthruster design.  This effort will result in a micropropulsion system with a modular design that meets the needs of current and future small- and micro-satellites for NASA missions.
The Conjugate Etalon Spectral Imaging (CESI) concept enables the development of miniature instruments with high spectral resolution, suitable for LEO missions aboard CubeSat or nanosat buses, including constellation missions providing global coverage and characterization of dynamic phenomena.  Small size, low power, and a simplified instrument architecture support missions for earth observation, atmospheric science, and planetary science.
Unlike prior art hyperspectral and ultraspectral instruments that are much too large and complex for deployment on a nanosat, the CESI concept can be implemented in a small form factor using inexpensive components and requiring only a small optical aperture.  CESI superimposes the interferogram from a conjugate Fabry-Perot etalon on the image of a scanned scene captured on a novel high-sensitivity low-noise SWIR focal plane.  Using image processing, high resolution spectral characterization is performed independently for each point in the scene.  The innovative focal plane and spectroscopic concepts have many promising scientific and commercial applications.
The Scanned Etalon Methane Mapper (SEMM) is a CubeSat instrument that incorporates the CESI concept to perform global daytime mapping of atmospheric methane column density.  Performance capabilities: ground resolution 100 m; concentration sensitivity 18 ppb; and global revisit ~ 60 days.
We propose building upon the modular extensible architecture and existing capabilities of Open|SpeedShop to provide seamless, integrated, heterogeneous processor performance analysis. The NVIDIA GPU and Intel Many Integrated Core (MIC) processors are increasingly important at high performance computing (HPC) laboratories within NASA for use on NASA's high-end computing (HEC) projects because of their ability to accelerate scientific application performance.  In order to understand what impact these accelerators are having on performance, tools must succinctly present heterogeneous processor performance information.

One of the key goals of this work is to develop innovative methods for presenting the performance information extracted from applications running on both traditional CPU and GPU/MIC processors. And, specifically, to provide command line interface (CLI) and graphical user interface (GUI) displays of the heterogeneous processor performance information that facilitates the user's understanding of how their application utilizes the accelerator.

For this project, Phase I GPU-related research will include measuring the usefulness of a GPU kernel, including device utilization, data transfer rates, device efficiency metric, internal device tiling factors, device memory hierarchy usage, as well as additional factors outlined in the referenced material. When measuring the performance of an application that contains concurrent processing on both the CPU and GPU processors, attributing time spent to the proper processor can be difficult - a difficulty exacerbated by the potential presence and usage of multiple accelerators concurrently. Accurately measuring the interactions of multiple accelerator devices is necessary in order to accurately report the application's performance to the user, but is difficult with the current set of accelerator interfaces. Developing techniques for mitigating these limitations will be another area of our GPU research.
The key innovation of this effort is the development of an Uninhabited Aerial System (UAS) Traffic Manager Evaluator (UTME) specifically targeted at evaluating potential air traffic systems for handling low-altitude UAS flights.  It has been estimated that over 90&#37; of future UAS flights will be low altitude (less than 6,000 feet above ground level).  At such low altitudes, the conventional air traffic management systems are ineffective, primarily because both communication and surveillance coverage is limited at those low altitudes, and communication latencies among the controller, remote pilot, and UAS vehicle will be higher than controllers are accustomed to today.  Therefore the current approach of treating low-altitude piloted  flights distant from a major airport with Visual Flight Rules (delegating separation to the pilot in visual meteorological condition) may lead to unacceptably low levels of safety (high probability of accidents). In part because of these concerns, NASA is considering developing a low-altitude air traffic control system specifically for UAS flights&amp;#151;what is called here a system for UAS Traffic Management, or UTM.   But how should such a UAS Traffic Management (UTM) system be structured?  What are the fundamental requirements?  How can different proposals for handling such traffic be evaluated?  A UTM evaluator, which is the system proposed herein, will help answer these questions.
MYMIC will analyze, design, develop and evaluate the Virtual Control Room &amp;#150; Compressor Station (VCoR-CS) training system. VCoR-CS will provide procedural training to NASA operators within a 3D virtual environment that realistically models the Compressor Station Control Room. It will include an accessible information repository to store expert knowledge and Standard Operating Procedures for display via a simple, training interface. VCoR-CS will leverage a "crawl-walk-run" learning approach with practice and assessments levels in order to allow users to slowly increase the cognitive load and difficulty of their training. A log-in capability will enable user performance to be tracked and training to be accessed on-demand. MYMIC will evaluate the effectiveness of VCoR-CS training prototype and adherence to its learning objectives. Project efforts and results will be incorporated into a Final Report. MYMIC will also conceptualize the expansion of VCoR-CS to include emergency preparedness and scenario-based training modules for future, follow-on efforts.
The integration of Unmanned Aircraft Systems (UAS) into the National Airspace System (NAS) requires a robust, reliable communication link between the Unmanned Aerial Vehicle (UAV) and its operators. Constant communication is a necessity. New and innovative approaches are needed to provide high-bandwidth Control and Non-Payload Communications (CNPC).

To enable the CNPC system and increase the utility of UAS in the NAS, NuWaves Engineering has teamed up with Auriga Microwave (http://www.aurigamicrowave.com/) of Chelmsford, MA to propose the UAS Power amplifier for Extended range of Non-payload communication Devices (UPEND) project. UPEND combines a very high-efficiency radio frequency (RF) power amplifier (PA) with innovative linearization techniques in a miniature package capable of being integrated into UAS platforms as small as the venerable Boeing/Insitu ScanEagle. NuWaves' UPEND leverages advanced Monolithic Microwave Integrated Circuit (MMIC) technology, as well as efficiency and thermal design, to minimize size, weight, and power (SWaP) of a PA module, while maintaining the linear output required by complex modern communications waveforms, such as 802.16.
The innovative methodologies proposed in this STTR Phase 1 project will enhance Loci-STREAM which is a high performance, high fidelity simulation tool already being used at NASA for a variety of CFD applications. This project will address critical needs in order to enable fast and accurate simulations of liquid space propulsion systems (using propellants such as LOX, LCH4, RP-1, LH2, etc.). The proposed enhancements to Loci-STREAM in this project are:
(1)	Level-Set methodology (which will be of high fidelity and highly scalable for massively parallel computing) for tracking liquid propellant interface for primary atomization, and 
(2)	Adaptive tabulation for flamelet models for turbulent combustion designed for distributed parallel computing architectures.
The following methodologies are already available in Loci-STREAM:
(a)	Lagrangian particle tracking for motion of droplets,
(b)	Droplet evaporation model, and
(c)	Flamelet models in Hybrid RANS-LES framework for unsteady turbulent combustion. 
Integration of the methodologies proposed in this project into Loci-STREAM will result in a state-of-the-art multiphase combustion modeling tool which will enable fast and accurate design and analysis of liquid rocket engine flow environments, combustion stability analysis, etc. which constitute critical components of space propulsion engines that are part of NASA's Space Launch System (SLS).
High-value bearings are a critical part of the safety, reliability, cost and performance of modern aircraft. A typical passenger jet will have 100 to 175 high-valve bearings costing from $2,500 to $50,000 each for a total aircraft cost of $300,000 to $600,000.  All gas turbine engine bearings are inspected at overhaul and typically 30-40&#37; of there are rejected. For each engine overhaul, bearing replacement costs on average $100,000.  Any process that increases bearing performance and reliability will have a commensurate effect on aircraft safety, reliability, performance and operating cost. Ormond is proposing to use a novel surface enhancement process, cavitation peening, to impart deep, high magnitude residual stresses without roughening the bearing such  as to significantly enhance bearing life, reliability and performance.  Cavitation peening uses ultra-high pressure water jets to generate intense clouds of cavitation bubbles that collapse on the work piece generating shock waves that cold work the material. No particles are used, the process produces no waste, adds no weight to the part and is very inexpensive. The new technology is currently being evaluated by Boeing, Sikorsky, Bell and Rolls-Royce for aerospace applications and is proving particularly effective for gears. A 20&#37; improvement in bearing life is targeted. This project would generate the residual stress and fatigue data for bearings to convince stakeholders of the value of the technology for this application.
NASA's Road Maps for both Launch and In Space Propulsion call for the development of non-toxic, monopropellant reaction control systems to replace current state-of-art hydrazine.  The Orion Multi-Purpose Crew Vehicle capsule with twelve 160 pound force (lbf) hydrazine monopropellant thrusters and the Orion Service Module with eight 100lbf NTO/MMH auxiliary propulsion thrusters are obvious insertion candidates.   Additionally, the Commercial Crew and Cargo spacecraft have also demonstrated the need for 100lbf class attitude control thrusters with quantities comparable to Orion.  Hydrazine replacements, including HAN- and ADN-monopropellants, combust at higher temperatures making them incompatible with current Inconel 625 thrusters used in 100lbf engines. In addition, Orion MPCV models indicate when current thrusters are fired during re-entry, the extra thermal loads of re-entry may exceed the operating envelope of Inconel.  In support of NASA's goal to replace hydrazine and the need for higher performance 100lbf class engines, Plasma Processes proposes to design, fabricate and test a 100lbf thruster with emphasis on non-toxic propellant, increased performance, ease of manufacturing and cost reduction.
This Phase I SBIR project seeks to develop a 500 Wh/kg Lithium primary battery for intended application as the primary power source on landers and probes for future missions to Titan/Enceladus and near Earth asteroids. The proposed battery technology aims to offer a viable alternative to Li/SO2 primary batteries which were used in the most recent mission to Titan. A thorough analysis of power requirements for the Huygens-Cassini mission (2005 landing) will be undertaken from the point of view of identifying engineering areas where the benefits of introduction of a more potent battery could be realized. Developers will focus on the engineering and performance testing of two distinctly different cell designs in a 32650 cylindrical cell housing. An integral part of the new battery will be a system of smart electrical heaters which, at a fraction of available battery power, will turn resistive heaters on and off as required to compensate for heat losses through the battery box wall (the assumption of the model being studied is that the battery should not require the use of external radioactive heating sources to maintain operation). This project will see the introduction of several new materials which will be manufactured by the contractor for purposes of boosting the energy efficiency of the proposed battery system.
Plasma Controls will manufacture and test a set of ion optics for electric propulsion ion thrusters using additive manufacturing technology, also known as 3D printing. Additive manufacturing can potentially produce optics with novel or complex geometry that have better performance compared to those made traditionally, while also giving cost and mass savings.
A key component to solving many engineering challenges of UAS integration into the National Airspace System is the ability to state the numbers of forecasted UAS by airframe and mission/operation type being performed within discrete airspaces. UAS growth is a function of locational based businesses and public use needs, in addition to increases in UAS uses and future aircraft types. Being able to forecast this growth requires time consuming and highly detailed configuration and model development, consensus between different organizations, and flexible tools tunable to changing perspectives. Availability of a common cloud based application integrating varying growth curves and linking geospatial aspects of UAS operations will greatly enhance and stabilize system level analysis of issues such as: radio spectrum usage, safety case analysis, economic forecasts, etc. Individuals and organizations would benefit in using a community centric tool with the ability to shared data and projections while still allowing individual researchers to set up paradigms for their own, unique forecasts.  The overall project objective is to design, develop, and study the feasibility and potential benefits of a UAS Demand Generator for Discrete Airspace Density (UAxpan) system which allows for common solutions in complex forecasts of growth and uses of numerous unmanned systems and mission/operational types. This will be accomplished by developing and testing a prototype system and performing the key functionality objectives using real industry, UAS, geographic, and NAS data.
An eye-safe, multispectral cross-track scan subsystem with a large receiver aperture and a narrow FOV is proposed for the NASA Cloud Physics Lidar (CPL) to increase the horizontal scan area coverage. The  /-14 degree cross-track scan capability will cover  /- 5 km from nadir at a 20 km altitude. The cross-track scanner uses a bidirectional scan pattern, which collects 10,000 data points per cross track scan at a 5 kHz transmitter rep rate. Solar background is reduced with narrow bandpass filters and a narrow transmitter linewidth with center wavelength control. The scanner accounts for the return pulse lag angle due to pulse time of flight. The existing CPL vertical resolution is maintained at 30 m. Photon counting SPAD detectors and PMT's are used with photon counting modules and multichannel scalers, which support eye-safe operation. The compact receiver telescope design is achieved with a configuration that uses a fixed primary mirror and a scanning secondary mirror, which directs the return signal through a Coude path to the the detector optics bench. The multispectral lidar uses polarization discrimination on two of the three receiver channels, and the optics design supports a 100 urad receiver Instantaneous Field Of View to minimize the solar background noise.
In this phase II SBIR we will design, build, test, and deliver new scanning based micro-ladar sensors with unprecedented small size, weight, and power (SWaP), thereby enabling scanning LADAR deployment on previously inaccessible platforms such as satellites.  The system will range out to &gt; 1 km, have high frame rates, high resolution (up to 500 x 500), high range accuracy (&lt;5 cm), weigh less than a kg, be constructed from space deployable technologies with no-moving parts.  The enabling technology for this Micro-LADAR system is a combination of two new electro-optic laser scanning technologies: high speed refractive continuous scanners with a 60&amp;#176;x15&amp;#176; field of view (FOV) and diffractive-waveplate discrete or step-wise scanners to boost the total FOV (ultimately up to unthinkable angles such as 120&amp;#176;x120&amp;#176;). The results will be a very low-power, long-life (no moving parts), radiation hard, micro-LADAR.
Wrong decisions during the missions can lead to an unsafe condition or immediate failure, while correct decisions can help continue the missions even from faulty conditions. In view of the lessons learned from mishaps, i.e., failed space missions, it is imminent that reliability analysis and risk assessment are kept in sync with space system design as it evolves from the concept through preliminary design, detailed design, production, and operations. Qualtech Systems, Inc. (QSI) in collaboration with Dr. John Sheppard from Montana State University (MSU) proposes a real-time health and risk assessment solution. The proposed efforts through this project in developing real-time computer-based environment for diagnosis, risk assessment, and visualization of system status will provide: (1) an environment for thorough and collaborative analysis and evaluation of a system design before the system is built and commissioned, (2) real-time diagnosis to identify Good, Bad, Unknown, Suspect, Degraded and Suspected Degraded of subsystems/components, (3) state of redundancies in real-time in case of single/multiple faults, (4) degradation status/criticality/time-to-failure, (5) risk identification of software and loss of mission/vehicle/life, (6) recommendation of a safer state to go to, and (7) visualization of risk (rank-ordered missions, probability of mission success, schedule and cost), mission criticality, and diagnostic coverage. The proposed solution should be of significant relevance to NASA's space missions because it provides capabilities in characterizing as system in its failure space as well as uncovering and managing risks as the system design evolves.
Capitalizing on a strong expertise in III-Nitride epitaxy, GaN-Si power device designs, and wide-bandgap power electronics, researchers at GeneSiC Semiconductor propose a SBIR program focused on the development of 15 kW/300C-rated power converters using AlGaN/GaN-Si MOS-HFETs and Schottky rectifiers. The proposed AlGaN/GaN-Si power converters to be developed in this program will usher in a new generation of high-efficiency, low-cost, and radiation-hard power conversion units on-board future NASA spacecraft. Phase I of this proposed work focussed on the optimization of the design and fabrication of the AlGaN/GaN-Si MOS-HFET and NSJ SBR devices. Phase II will be focused on the design and integration of Si/GaN gate-drive circuitry with the power SBRs and transistors to create high-power integrated circuits. Another major objective during Phase II will be the construction of Rad-Hard packaging for the power ICs. At the end of Phase II of this program, a fully-functional 15 kW/300C rated power converter IC equipped with AlGaN/GaN-on-Si  MOS-HFETs, Natural SuperJunction (NSJ) SBRs as free-wheeling diodes and on-chip SiC or III-Nitride gate drive circuitry will be demonstrated at a switching frequency of &amp;#8805; 1 MHz and at a temperature of  &amp;#8805; 300C. As compared to the existing state-of-the-art power electronics technology, the proposed AlGaN/GaN-on-Si power converters will offer (A) Lower on-state losses, 300C operation and 1 MHz switching capability (B) A Lateral device architecture, which is highly desirable for construction for monolithic power integrated circuits (C) Possibility of hybrid interconnection of III-Nitride Power Devices with on-chip Rad-Hard AlGaN/GaN Gate Drive Circuitry (D) Desirable Normally-OFF Power Switches
We propose to combine two revolutionary cathode technologies into a single device for use in electric space propulsion.  This will overcome problems that both technologies have when operated alone.  
The cathode is currently the component which most limits performance and life in ion and Hall Effect thrusters.  Improved cathodes are essential for NASA's next generation electric space propulsion initiative.  The innovation will benefit both satellite and deep space missions.  We have successfully demonstrated both stand-alone reservoir and scandate cathodes in hollow cathode geometries.  Reservoir cathodes are known to provide unprecedented life and stability.  Scandate cathodes dramatically lower operating temperature.  By combining the two technologies, we incorporate extremely long life (greater than 10 years) and extremely low temperature (less than 850 degrees C) into a single device.  The result will be a revolutionary enhancement in electric propulsion.  
Reservoir cathodes employ a chamber behind the emitter which contains a barium emissive material.  This greatly increases the amount of barium available to the cathode.  Scandate cathodes provide a scandium-containing cathode surface which lowers the work function.
CRG's no-oven, no-autoclave (NONA) composite processing technology enables the fabrication of high-performance composite parts without the limitations imposed by autoclaves and ovens. The NONA infusion and cure of autoclave prepreg materials allows the manufacture of large primary composite structures without the expensive and energy-intensive capital equipment currently required for fabrication. The NONA process enables the remote fabrication of complex, integrated structures, dramatically shifting the composites manufacturing paradigm. Qualified autoclave or OoA prepreg tapes can be applied simultaneously with dry unidirectional (UD) tapes in an automated process. The presence of dry fibers throughout the layup before infusion allows improved breathing, removal of volatiles from prepreg, and improved compaction with only atmospheric pressure, mimicking the double vacuum debulk (DVD) process without the added equipment. NONA resin is then introduced to the evacuated layup at ambient temperature to wet out all available contact surfaces and cure itself and the prepreg in place. The NONA epoxy resin uses its own chemical energy to propel itself through a complete cure with no external heat required. With a high degree of crosslinking, the baseline NONA resin provides good strength, chemical resistance, and thermal performance up to 350 degrees F. Pairing NONA resin with a compatible prepreg, such as IM7/Cycom 977-3 or Hexcel IM7/8552-1, a cure of both systems can be achieved at room temperature. Because the cure occurs at room temperature, the NONA resin locks in its shape near room temperature, thus allowing the use of low-cost tooling materials, typically avoided because the of high coefficient of thermal expansion (CTE).
The proposed solution exploits recent advances in computer vision to conceive of a single-camera + gyro + accelerometer vision-based navigation solution such that the processing will be lightweight (requiring only a single optical flow sample per frame).  Known landmarks (natural or artificial) will have absolute positions known to planetary exploration worker robots.  The worker robot can identify it's absolute position by observing known landmark features and deriving range from the raw attitude sensor data and the video stream.  By observing one or more landmark features during camera motion, the position uncertainty of the range and bearing from the vehicle can be estimated.  Each range / bearing measurement to known landmarks acts as a constraint for the camera position in the landmark navigation space (which may be arbitrarily defined and not oriented the same as the global navigation frame).  Combining the worker's rough knowledge of it's own position can further reduce the position error estimates.

The single-camera passive ranging technology leverages Navy SBIR funded work for early simulation tasks.
The key innovation of this effort is the development of a Metroplex-based arrival, departure, and surface optimization system which we call MetroSim.  Linking with both the NASA-developed Traffic Management Advisor (TMA) tool, the NASA-developed System Oriented Runway Management (SORM) tool, the FAA-proposed Terminal Flight Data Management (TFDM) system, or alternatively with live or recorded flight data, MetroSim allows airport planners, traffic flow management experts, airline dispatchers, air traffic controllers, and pilots to reduce the uncertainty in operations planning, recover quickly from disruptive events, maintain high throughput even in adverse weather conditions, and handle the uncertainties associated with irregular operations. 
Not only are we proposing innovations that improve Metroplex flight management, but we are also proposing innovations in the way aviation software is structured.  In order to manage the high volume of flights in the New York airspace effectively, and simultaneously improve the arrival stream, departure stream, and surface operations, the MetroSim architecture contains a collection of different tools, some of which are analytic computations, some of which are physics-based computations, and some of which are mathematical optimization calculations, interoperating in a distributed computational environment.  Finally, the architecture allows Metrosim to be adapted to any Metroplex.
Pioneer Astronautics proposes an advanced photocatalytic oxidation reactor for enhancing the reliability and performance of Water Recovery Post Processing systems aboard crewed spacecraft.  This novel technology, called the Advanced Wastewater Photooxidation System (AWPS) is designed to oxidize and remove recalcitrant aqueous organic constituents in the water recovery post processing system under ambient temperature and pressure conditions.   The basis of the innovation is the combination of high brightness and long lifetime UV LED light sources with efficient geometric illumination of a highly active photocatalyst immobilized on a high surface area support.  This combined approach leads to numerous performance benefits including high conversion efficiency, low temperature and pressure operation, compact footprint, high reliability and low crew maintenance, and decreased equivalent system mass (ESM).   The Phase I effort will clearly demonstrate the feasibility of these concepts by mineralization of polar water soluble organics and organosilanol constituents under long duration testing.  Data from the Phase I will lead to a prototype scale-up of the device in Phase II.   Development strategies for the Phase II device include component design verification testing and determining optimum reaction conditions.   Long duration performance tests will validate the reactor design, and establish the technology applications in space and commercial markets.
We have developed a common architecture for laser transmitters that address requirements for water vapor as well as ground and airborne ozone lidar systems.  Our innovative approach to these requirements has the advantages of reducing size, weight and power (SWaP) as well as hardware cost for all of the applications envisioned.  Under this Phase I SBIR program Fibertek proposes to demonstrate operation of laser systems at wavelengths required for both water vapor and ozone DIAL systems and power scaling to desired levels.  In the Phase II follow-on, Fibertek will build and deliver laser transmitters and frequency converters designed to meet NASA requirements for both water vapor and ozone lidar systems.  The use common technology for the two DIAL applications provides NASA a lower cost and risk path to development of next-generation DIAL systems sought under this select SBIR opportunity.
With the capacity and performance of FPGAs suitable for space borne applications continuously increasing, the design of FPGAs is becoming increasingly complex involving trading off or simultaneous optimization of space, speed, and power. RNET and ANL are proposing to develop software infrastructure that facilitates automatic performance tuning of FPGAs in terms of speed, power, and size. We introduce an extensible empirical tuning tool system OrFPGA, which is aimed at improving both performance and productivity by enabling FPGA designers to create simple scripts that trigger various FPGA performance optimizations for a specific design. OrFPGA will generate various tuned versions of the same design with different designer parameters and evaluates the versions to select the best performing one for production use. The proposed work will leverage an existing performance tuning tool named Orio developed by ANL for empirical tuning of compute-intensive kernels for a given architecture.
The ultimate goal of the SOAR program is to develop robust hardware and algorithms for low light, passive terrain sensing.  The SOAR system will provide NASA with a solution for real-time obstacle avoidance for large and small unmanned air platforms.
During Phase-I, we will collect images with all of the leading low-light camera technologies.  The image data will be used to derive, test, and enhance a passive terrain sensing algorithm based-on state-of-the-art, visual odometry and dense stereo algorithms.  At the end of Phase-I, we will recommend the optimal hardware, algorithm, and computing platform for full prototype development during Phase-II.  The factors used to make the recommendation include cost, range accuracy, size, power consumption, algorithm execution time, etc.
Zero net positive suction head (NPSH)-capable hydrogen pump inducers are a critical component needed to lower the cost and increase the effectiveness of Nuclear Thermal Propulsion (NTP) engines.  Zero NPSH pumps need to be able to pump up to 55&#37; vapor fraction by volume without significant head fall-off.  Current technology inducers can pump liquid hydrogen up to a limit of about 25&#37; vapor fraction by volume because of choking of the vapor in either the inlet pipe or the inducer blade passage.  It is proposed that the Concepts NREC (CN) inlet cover treatment cavitation and stability control device (SCD) will be able to increase the hydrogen vapor volume pumping fraction to the required 55&#37;.  The device allows the inducer to operate stably at high blade angles and low flow coefficients which increases the blade passage and the inlet pipe area to delay choking of the pumped fluid.
To be useful for computational combustor design and analysis using tools like the National Combustion Code (NCC), low-dimensional chemical kinetic mechanisms for modeling of real fuel combustion chemistry must be sufficiently compact so that they can be utilized in multi-dimensional, multi-physics, reacting computational fluid dynamics (CFD) simulations. Despite advances in CFD-appropriate kinetic mechanism reduction for kerosene-range fuels, significant combustion property variation among current and prospective certified fuels remains a challenge for meaningful CFD-advised design of high pressure, low-emissions combustors. The proposed project will leverage Princeton's ongoing work in aviation fuel surrogate formulation and modeling as well as kinetic mechanism development for emissions and high pressure combustion to produce and demonstrate a meta-model framework for automated generation of fuel-flexible compact chemical kinetic mechanisms appropriate for 3-D combustion CFD codes. Phase I will demonstrate the novel meta-model approach by providing compact kinetic mechanisms for both a "typical" Jet A/JP-8 (POSF-4658), as well as a synthetic paraffinic kerosene (SPK) derived from natural gas (POSF 4734). Phase II of this proposed work would generalize the Phase I results to span the combustion property parameter space relevant to both conventional and next-generation alternative aviation fuels.  The commercial product foreseen from this SBIR program is a stand-alone, novice-friendly real fuel kinetic mechanism generator software package that can interface with commercially-available computational fluid dynamics (CFD) codes.  Potential customers may include the companies supplying ANSYS, CFD-ACE+, or COMSOL, as well as industrial users with proprietary in-house codes.  Tools to yield compact real fuel kinetic models has similar broad appeal for computational simulations in  automotive, aerospace (both defense and civilian), and marine propulsion industries.
For this award, Tyvak proposes to develop a complete suite of avionics for a Nano-Launch Vehicle (NLV) based on the architecture determinations performed during Phase I. This system will address the unique avionics challenges of a dedicated small launch vehicle and will utilize heritage and lessons learned from Tyvak's CubeSat avionics systems, modifying and optimizing its existing products for use with this new class of launch vehicles. The major technical objectives are: 
- Provide broad compatibility with all known NLV systems in development 
- Determine and provide appropriate performance and reliability metrics while maintaining the low-cost/low-mass approach made possible by commercial electronic systems 
-	Implement the latest network protocols with support for wireless systems in the NLV environment 
- Develop a GPS metric tracking system and perform requirement verification to meet  range safety recommendations
- Demonstrate the reliability of low-cost/low-mass/low-power/redundant automatic flight termination system (AFTS) by combining the latest generation of commercial miniature GPS systems with high performance computer systems currently used by Tyvak
- Validate functionality and performance for the entire NLV avionics suite through a series of incremental tests, from vibration and thermal vacuum, through a stratospheric balloon flight, an inert test article flight, to final demonstration on a NLV proxy.
NASA's long range goals of reducing fuel consumption by 30&#37; and increasing fuel efficiency by 35&#37; can be partially accomplished through increasing the operation temperatures of gas turbine engines.  The advent of advanced alloys, coatings, cooling technologies and ceramic components has created the potential for significant increases in the hot section of these engines; however, these advances will also lead to elevated temperatures in other regions of the engine. For example, the turbine disk section would also need to operate at increasingly higher temperatures that would subject it to oxidation and hot corrosion degradation mechanisms not currently experienced. One approach to enhance the temperature capability of these systems is through the incorporation of environmental protective coatings.  Research is proposed here to employ advanced coating manufacturing techniques designed to enable the affordable application of environmental protective coatings having enhanced resistance to hot corrosion and oxidation. Advanced testing approaches will be used that simulate real-world conditions and demonstrate the performance advantages of the deposited coatings. The coating systems will be applied in this work onto coupons and components to demonstrate coating capability and allow simulated engine environment testing in follow-on programs.
Numerical cavitation modeling capability is critical in the design of liquid rocket engine turbopumps, feed lines, injector manifolds and engine test facilities. Cavitation in turbopumps leads to reduced performance, mechanical vibrations, and component erosion. The Computational Fluid Dynamics (CFD) solver Loci-STREAM&amp;#150;developed by Streamline Numerics&amp;#150;is one of the primary production tools currently used at NASA to simulate turbopumps.  With a long term goal of enabling accurate computational modeling of cavitating turbopumps subjected to an array of potential operating conditions, this project is aimed at enhancing the cavitation modeling capability in Loci-STREAM to enable time-accurate simulations involving complex engineering geometries present in turbopumps of relevance to NASA involving cryogenic fluids (LOX, LH2, LCH4, RP-1, RP-2). This will contribute to enhanced performance, reliability and reduced developmental costs of liquid rocket pumps. The project will involve a tightly coupled experimental/computational effort.  The experimental simulations will be conducted at the University of Florida in a dedicated experimental facility capable of investigating various cavitation modes covering the entire range of non-cryogenic to cryogenic fluids; the proposed studies will be supported by extensive instrumentation.  The cavitation models in Loci-STREAM will be substantively validated via dedicated experimental data directed by the computational and model requirements.
SSCI and MIT propose to design, implement and test a comprehensive Integrated Mission Planning \&amp; Autonomous Control Technology (IMPACT) for Autonomous ISR missions employing collaborating Unmanned Aerial Vehicles (UAV). The main feature of the IMPACT system for Autonomous ISR is that it is based on robust real-time learning about dynamic and stochastic environments, and on a capability to autonomously react to contingencies while satisfying the mission objectives and the overall flight safety. The project will leverage a number of technologies recently developed by SSCI and  MIT, and integrate various system modules within a flexible and user-friendly framework. In order to achieve the project objectives, the following tasks will be carried out: (i) Problem Statement &amp; Test Scenario Selection jointly with NASA; (ii) Develop, Implement &amp; Test Vehicle-level Subsystems; (iii) Develop, Implement &amp; Test Mission-level Subsystems; and (iii) Carry out  Integration &amp; Initial Testing of the overall IMPACT System for an Autonomous ISR mission. Phase II of the project will be focused on the enhancements and full implementation of the IMPACT system, prototype system development, and demonstration of its features through hardware-in-the-loop simulations and flight tests at MIT.
Thermal Transfer is a critical part of power electronics application in both terrestrial and space environments.  Due to longer lifetime expectancies and harsh operational conditions, space vehicles require unique materials to deal with the increasing electrical and thermal loads placed upon the structure.  Increasing use of power electronics including high current carrying semiconductor devices such as IGBTs, MOSFETs, power transistors, and modules drive the need for specialty thermal management materials both in the packaging of the discrete devices as well as for the packaging of modules consisting of several or arrays of these devices. 

The overall objective of this program (Phase II) is to adapt CarbAlTM-based advanced thermal management substrates from terrestrial to space applications.  ANI will target improved CarbAl&amp;#153;-based heatsinks and thermally conductive circuit boards for power electronic applications.  CarbAl&amp;#153; is a carbon-based thermal composite with a thermal performance exceeding that of many metals.  The low CTE provides excellent matching to state-of-the-art power transistor dies and the low density and robustness make it suitable for space vehicle applications.   The proposed Phase I program is a continuation of the materials development completed internally at ANI.  If successful, the technology developed through this project will provide and accurate, robust, reliable and cost effective.
As the power density of advanced engines increases, the need for new materials that are capable of higher operating temperatures, such as ceramic matrix composites (CMCs), is critical for turbine hot-section static and rotating components. Such advanced materials have demonstrated the promise to significantly increase the engine operating temperature relative to conventional super alloy metallic blades. They also show the potential to enable longer life, reduced emissions, growth margin, reduced weight and increased performance relative to super alloy blade materials.

MR&amp;D is proposing to perform a combined analytical, fabrication and experimental program to achieve the program objectives of developing innovative approaches to improving foreign object damage (FOD) resistance of CMC materials, specifically with Hyper-Therm High Temperature Ceramics's material system as this will be used by Rolls Royce for turbine engine hot-section components. MR&amp;D will develop finite element math models of the CMC material specimens and the high velocity metal projectiles to simulate impact testing.  The models will first be verified by reproducing experimental data measured on impacted baseline CMC specimens. Thereafter, candidate methods for potential improvement of the FOD resistance will be analytically investigated through mathematical simulations of impact tests.
Solar cells are the critical power source for the majority of space missions.  The advancement from single junction silicon cells to current, state-of-the-art, triple junction, germanium cells enabled greater mission power per weight, stowed volume and deployed area.  Near-term, advanced solar cell technologies will range from 4 to 6 junctions, and include a variety of band gaps.
Solar cell testing is critical to space missions.  Every solar cell is tested at the cell level under continuous light and at the panel, wing and sometimes spacecraft level multiple times under LAPSS.  Current test methods calibrate the light source by measuring the current output of each junction and adjusting the source accordingly.  Today's sources are a combination of lamps and filters.  As cells with more the 3 junctions come into test, more flexible sources of narrower bands will be needed and current methods will have extreme difficulty, complexity and expense trying to keep up with the variety of near-term advanced solar cell designs.
We propose a solid state illumination source with enough discrete source wavelengths to be flexible enough to be calibrated to any number of junctions, up to 6, for continuous cell testing.  In addition, this source would be cost effective enough to allow many sources connected together to perform large area testing, pulsed or continuous, for panel and wing level testing.  Calibration would follow similar methods to the current practice, but would be simplified through a software interface.
Robots need to know their location to map of their surroundings but without global positioning data they need a map to identify their surroundings and estimate their location. Simultaneous localization and mapping (SLAM) solves these dual problems at once. SLAM does not depend on any kind of infrastructure and is thus a promising localization technology for NASA planetary missions and for many terrestrial applications as well.

However, state-of-the-art SLAM depends on easily-recognizable landmarks in the robot's environment, which are lacking in barren planetary surfaces. Our work will develop a technology we call MeshSLAM, which constructs robust landmarks from associations of weak features extracted from terrain. Our test results will also show that MeshSLAM applies to all environments in which NASA's rovers could someday operate: dunes, rocky plains, overhangs, cliff faces, and underground structures such as lava tubes.

Another limitation of SLAM for planetary missions is its significant data-association problems. As a robot travels it must infer its motion from the sensor data it collects, which invariably suffers from drift due to random error. To correct drift, SLAM recognize when the robot has returned to a previously-visited place, which requires searching over a great deal of previously-sensed data. Computation on such a large amount of memory may be infeasible on space-relevant hardware. MeshSLAM eases these requirements. It employs topology-based map segmentation, which limits the scope of a search. Furthermore, a faster, multi-resolution search is performed over the topological graph of observations.

Mesh Robotics LLC and Carnegie Mellon University have formed a partnership to commercially develop MeshSLAM. MeshSLAM technology will be available via open source, to ease its adoption by NASA. In Phase 1 of our project we will show the feasibility of MeshSLAM for NASA and commercial applications through a series of focused technical demonstrations.
Chronos Technology (DIv of FMI, Inc.) proposes to design, fabricate, and deliver a performance proven, and commercially available set of extreme high operating temperature PWM controller and circuit blocks (EXTEC1). These rad-hard (TID, SEU, ELDERS) components are intended to be used in a variety of spacecraft power and propulsion systems (PPU) along with smart power sub-assemblies for a wide range of both manned and unmanned space missions and payloads. The resulting devices would meet and exceed the required performance under extreme environment, high temperature while being offered commercially in very light, small and rugged package sizes and footprints. The described performance would be superior to any present-day alternatives that may only be available at much lower operating temperatures with no provisions for radiation hardness. The proposed range of circuit blocks that will be fabricated in Silicon Carbide (SiC) technology includes monolithic Pulse Width Modulator (PWM) controller as well as basic circuit blocks such as logic gate(s), counter(s), multivibrator, ramp generator, voltage reference, oscillator, buffer(s) and driver circuits. Logically and synergistically, many of the aforementioned circuit blocks would be used in the integrated PWM design.The significant points of innovation that we propose to bring to realization are:
1-Design and fabrication of a SiC MSI (medium-scale integration) Mixed-Signal ASIC. The proposed PWM controller ASIC is a mixed-signal system.
2-Design and fabrication of a precision, high-temperature capable, voltage reference on SiC at the integrated circuit level (used in the PWM and other applications). 
3-Design and fabrication of precision, extreme high-temperature capable, timing circuits on SiC at the integrated circuit level (used in the PWM and other applications).
4-Common approach to the yield packaged extreme environment component encapsulation among the various devices designed and fabricated in the project
The liberation of particles induced by rocket plume flow from spacecraft landing on unprepared regolith of the Moon, Mars, and other destinations poses high mission risks for robotic and human exploration activities. This process occurs in a combination of "extreme environments" that combine low gravity, little or no atmosphere, with rocket exhaust gas flow that is supersonic and partially rarefied, and unusual geological and mechanical properties of highly irregular soil regolith. CFDRC and the University of Florida have previously developed unique plume driven erosion simulation software for such environments by combining novel granular physics simulation modules developed by UF with the Unified Flow Solver (UFS) plume flow simulation software developed by CFDRC. Granular flow constitutive models, formulated through first-principle 3-D Discrete Element Method particle kinetics simulations, were implemented for efficient Eulerian gas-granular flow CFD modeling in the UFS simulation framework. Resultant simulations realistically capture the granular flow characteristics of particle erosion and cratering scenarios. The goal of this project is to dramatically advance the fidelity of these simulations towards simulating actual extra-terrestrial soil compositions with broad shape and size variations. This will be achieved through applying recent, novel particle kinetics modeling concepts to formulate granular flow physics models for both, realistic irregular particle shapes and realistically dispersed particle size distributions. The proposed technology development will result in unprecedented computer modeling capability for predicting liberation and flow of realistic granular material compositions in extreme extra-terrestrial environments.
The focus of this Select Phase II program is to build and deliver laser components both for airborne water vapor and ozone DIAL systems.  Specifically, Fibertek proposes to deliver to NASA the following prototype systems:

   1) A complete water vapor DIAL transmitter with single-line output tunable over the 936 nm water vapor line,
   2)  A wavelength converter for ozone DIAL compatible with the GOLD (Global Ozone Lidar Demonstrator) pump laser, with an output on two lines between 300 and 320 nm.  

Fibertek has developed a common architecture for wavelength converters for both water vapor and ozone DIAL applications.  Use of common technology allows us to economically manufacture components for both applications that are compatible with provide  improved performance from instruments planned or previously developed by NASA Langley Research Center (LaRC).  The laser systems delivered will provide NASA with the critical components needed for a new generation of airborne lidar sensors for measurement of stratospheric and upper tropospheric species central to improved weather forecasting and understanding of global climatology.  The laser systems developed also provide a stepping-stone to space-based sensors &amp;#150; utilizing components and architectures that are scalable and traceable to space based operations.
Robots need to know their location to map of their surroundings but without global positioning data they need a map to identify their surroundings and estimate their location. Simultaneous localization and mapping (SLAM) solves these dual problems at once. SLAM does not depend on any kind of infrastructure and is thus a promising localization technology for NASA planetary missions and for many terrestrial applications as well. However, state-of-the-art SLAM depends on easily-recognizable landmarks in the robot's environment, which are lacking in barren planetary surfaces. Our work will develop a technology we call MeshSLAM, which constructs robust landmarks from associations of weak features extracted from terrain. Our test results will also show that MeshSLAM applies to all environments in which NASA's rovers could someday operate: dunes, rocky plains, overhangs, cliff faces, and underground structures such as lava tubes. Another limitation of SLAM for planetary missions is its significant data-association problems. As a robot travels it must infer its motion from the sensor data it collects, which invariably suffers from drift due to random error. To correct drift, SLAM recognize when the robot has returned to a previously-visited place, which requires searching over a great deal of previously-sensed data. Computation on such a large amount of memory may be infeasible on space-relevant hardware. MeshSLAM eases these requirements. It employs topology-based map segmentation, which limits the scope of a search. Furthermore, a faster, multi-resolution search is performed over the topological graph of observations. Mesh Robotics LLC and Carnegie Mellon University have formed a partnership to commercially develop MeshSLAM. MeshSLAM technology will be available via open source, to ease its adoption by NASA. In Phase 1 of our project we will show the feasibility of MeshSLAM for NASA and commercial applications through a series of focused technical demonstrations.
Advanced Scientific Concepts, Inc. (ASC) is a small business that has developed 3D Flash LIDAR systems for space and terrestrial applications.  3D Flash LIDAR is ideal for determining real-time spacecraft trajectory, speed and orientation to the planet's surface, as well as evaluating potential landing sites.   ASC's Flash LIDAR has been used for autonomous berthing with the International Space Station (ISS) and is currently under development for the OSIRIS-REx asteroid rendezvous mission.  Flash LIDAR is also being evaluated by JPL and NASA for Entry Decent and Landing (EDL) for ALHAT and Mars. Through the investigations at JPL and NASA Langley a number of improvements to the technology have been identified as beneficial to landing application.   Improved range resolution, spatial resolution, increased sensitivity and greater dynamic range would increase the functionality for successful landing operations. ASC has developed the core technology for Flash LIDAR with its 3D-FPA and is developing higher resolution arrays to address these concerns.  ASC currently has on hand high sensitivity 32x32 arrays (shuttle run for the 320x320) that have not been tested with detectors.  Initial evaluation suggests that they have increased sensitivity by 50x, spatial resolution by 2.5x, and range resolution by 3x.
The objective of this proposal is to develop three unique energy harvesting technologies utilizing our existing research strengths that will be of interest and utility to NASA applications and environmental conditions. By developing multiple technologies, NASA will be able to harvest energy from multiple waste energy sources, namely environmental vibrations, thermal energy, and solar flux. These devices will initially be developed separately, but all the while with an eye on the final integration into a single package at the end of Phase II. Since the research on these technologies has been ongoing, it is reasonable to develop an initial prototype of these technologies at the end of Phase I, with integration occurring in Phase II.
Space presents a challenging environment for computing. Extended development times and radiation tolerance requirements leave hardware performance a decade or more behind the terrestrial state-of-the-art at the time of deployment. Additionally, once deployed, hardware changes are impractical, encouraging a trend towards increased software programmability. At the same time, topside pressure from application advancements is forcing space-based platforms to improve throughput and latency while reducing power consumption. A popular approach to addressing the tension between these requirements is the heterogeneous processing architecture. By providing multiple hardware tools that optimally support a subset of the anticipated workload, a heterogeneous architecture can offer performance and power solutions to the application developer. However, programming these systems is extremely challenging due to variations in toolsets and data sharing interfaces. As a result, data sharing and dynamic workload scheduling across heterogeneous architectures are often suboptimal and hindered by poor scalability. In this research and development effort, we study the feasibility of unifying a heterogeneous processing platform a unique programming model This platform is called the Assimilation Dynamic Network (ADN). The ADN employs a mesh network and virtual tiles on FPGAs and scalable multicore processors to create a cleaner and innovative programming model.
Boston Applied Technologies, Inc (BATi), together with Kent State University (KSU), proposes to develop a high sensitivity infrared (IR) imaging sensor without cooling, which covers a broad band from near infrared (NIR) to mid-infrared (mid-IR). It is based on a specific transparent functional material developed at BATi that has excellent pyroelectric effect, over strong absorption at NIR, mid-IR and long-wave infrared (LWIR) wavebands, perfect transmittance in visible wavelength.  With this material, the intensity variation of an incident NIR, Mid-IR or/and LWIR radiation from a warm object can be transferred into intensity variation of a visible beam by a smart use of liquid crystal, which can be detected by a commercial CCD or CMOS camera. Of the most important, the collaboration with Dr. Quan Li's group at The Glenn H. Brown Liquid Crystal Institute at KSU, which is renowned for their pioneer research and development on liquid crystal, will further leverage and ensure the success of the proposed program.  Compared to existing thermal imaging techniques, this invention will generate an uncooled IR imaging sensor with unprecedented low costs, high resolution, high sensitivity, low mass, and  low power consumption, which is very important to NASA's planetary exploration projects and other applications.
Launch vehicles experience extreme acoustic loads during liftoff driven by the interaction of rocket plumes and plume-generated acoustic waves with ground structures. Currently employed predictive capabilities to model the complex turbulent plume physics are too dissipative to accurately resolve the propagation of acoustic waves throughout the launch environment. Higher fidelity liftoff acoustic analysis tools to design mitigation measures such as deluge water and launch pad geometry are critically needed to optimize launch pads for SLS and commercial launch vehicles. This STTR project will deliver breakthrough technologies to drastically improve predictive capabilities for launch vehicle lift-off acoustic environments. Hybrid RANS/LES modeling presently established in NASA production flow solvers will be used for simulation of the acoustic generation physics, and a high-order accurate unstructured discontinuous Galerkin (DG) solver developed in the same production framework will be employed to accurately propagate acoustic waves across large distances. An innovative hybrid CFD-CAA method will be developed in which the launch-induced acoustic field predicted from hybrid RANS/LES will be transmitted to a DG solver and propagated using high-order accurate schemes ideal for acoustic propagation modeling. This new paradigm enables: (1) Improved fidelity over linear methods for modeling nonlinear launch-induced acoustics; (2) Greatly reduced numerical dissipation and dispersion; and (3) Improved acoustics modeling for attenuation, reflection, and diffraction from complex geometry. The merits of the proposed approach will be investigated and demonstrated in Phase I for benchmark CAA applications and plume impingement problems. In Phase II, the methodology will be refined and validated against realistic targeted applications.