Information Technology (IT) is a key element in the successful achievement of NASA's strategic goals. Modern IT tools and techniques have the capability to redefine many design and operational processes as well as enable grand exploration and science investigations. This proposal plans to address NASA's needs for innovative communication concepts for autonomous systems that require local information dissemination among mobile entities. We will explore a peer-to-peer paradigm for local dissemination of information among surface-based assets that are in geographic proximity. In this paradigm, a set of mobile objects (astronauts, rovers, robots, sensors, etc.) form a Mobile Ad-hoc NETwork (MANET), and they communicate with each other via short-range wireless technologies such as IEEE 802.11 and Bluetooth. We propose to develop a novel software toolkit that enables efficient local information dissemination applications in such an environment. The heart of this toolkit is a distributed peer-to-peer (P2P) algorithm that disseminates information intelligently based on the semantics of the information. This algorithm does not rely on any infrastructure, central server, or routing data structures, and therefore provides a higher survivability of the network than the traditional data dissemination techniques.
A clear need exists for the next generation of Ceramic Matrix Composites
(CMC) for Thermal Protection Systems (TPS), propulsion hardware, and
other high temperature applications.  No &amp;quot;off-the-shelf&amp;quot;
materials and/or processes capable of meeting NASA's goals are
available, yet   completely integrating a unique combination of
commercially available or nearly commercially available technologies can
meet NASA's goals.  The basic elements of the proposed approach focus on
refining 3-D fiber architectures, instituting semi-conductor industry
controls on the CVI process, forming a gradient interphase between the
matrix and fibers, and relying on molecular level modeling results to
predict thermal stability.  Both 3-D woven and 3-D braided preforms will
be designed and manufactured to control the resultant pocket size and
shapes to reduce voids during infiltration.  Pulsed CVI with an improved
out-gas control system will both form a gradient interphase that reduces
the CTE mismatch induced internal loads between fiber and matrix and
provide a more perfect microstructure while improving processing speed.
CMC test articles will be compared to previous work on molecular level
thermal modeling for Phase I.  Phase II will deliver optimized design
and manufacturing processes capable of making impact tolerant, long
fatigue life, high temperature CMC's.
Significant advances in several key technologies such as material
sciences, manufacturing, miniaturization, and active flow control
suggest that the time has come to address the issue of affordable
General Aviation (GA). These new technologies when combined with
advanced avionics and propulsion concepts will make GA affordable and
ecologically sustainable. With a greater ease of vehicle operation, GA
can become available to a much larger clientele and provide strong
impulses for the aerospace industry. When a large number of new
technologies are combined in a revolutionary way, validation of the
entire system at the design and development stage becomes highly
desirable. We propose building and flight testing a dynamically scaled
model of NASA's GA demonstrator that will feature many important
elements of the new GA concept.
This Phase I project is to investigate the feasibility for achieving EUV detectors for space applications by exploiting the ultrahigh bandgap semiconductor - AlN.  We plan to devise methods to improve the AlN epitaxial material quality and device structures for EUV detectors.  Specifically, we will study the properties of Si and Mg doped AlN epilayers and investigate n- and p-type doping issues in AlN and hence the feasibility for achieving high performance EUV detectors; improve the AlN material quality by exploiting novel template/substrates and growth schemes to reduce the dislocation and native defect density. Use knowledge gained from these investigations to provide new understanding of the III-nitride system and to improve EUV detector structural design. It is intended that EUV detector wafers will also be delivered to NASA scientists for the fabrication of detector arrays.  Improved performances of AlN based EUV detectors over conventional existing technologies are expected.
The investigation of the coating friction as a function of time is important to monitor the ball bearing heath. Despite the importance of the subject mater, there is a crucial lack of information in the literature about coating life and friction force in ball bearings as coating wear of progressively increases. Here we propose to develop a strategic space vehicle health monitoring system that will identify potential and/or imminent lubrication problems, analyze these parameters in real time, and provide direct input so that these problems are mitigated prior to failure. We will set up a lab experiment environment with a universal microtribometer and acoustic emission sensors measuring the signals associated with wear and the changes that tend to occur as a function of time. Friction force and acoustic signal will be measured with respect to the bearing condition. To capture the dynamic nature of friction evolution, we propose to extract the temporal transient features from the sensing data and develop Hidden Markov Models with four distinct states associated with four operation conditions of the ball bearing. Our system uniquely combine both physics-based and stochastic models for the online diagnosis.
The proposal outlines a research program for developing a novel soft-computing technology composed of an Artificial Immune System and Bayesian Belief Networks for monitoring, knowledge and information processing, and decision support infrastructure for testing of rocket engines of future spacecrafts. An engine failure during test operations may cause catastrophic results for the test article, supporting infrastructure, and potentially to supporting resources. The ability to effectively monitor health and status of a testbed and test article during a test firing and to take corrective measures for peak performance and improving reliable operations is of utmost importance. Using an existing SR-30 Jet Engine testbed utilizing artificial intelligence control techniques, novel algorithms are being developed by The University of Alabama that can function under faulty sensor conditions, can work effectively with thousands of sensors at high data rates, are self-checking, and are self-correcting can be of further support. The proposed effort builds on an existing joint MSFC/University of Alabama project where NASA's NSSTC is only funding graduate student research. This proposal will further enhance technology research for realization and synthesis of needed advanced algorithms in larger scale test platforms for propulsion health management, thereby furthering educational research addressing NASA's education missions.
Stirling Dynamics Inc and the University of Washington propose to develop a MATLAB toolbox for rapid aeroelastic (AE) and aeroservoelastic (ASE) modeling, analysis and optimization of flight vehicles.  In practically all current aeroelastic analysis/optimization codes, model generation takes a considerable amount of effort, as does the processing of results.  The proposed AE/ASE toolbox will provide user-friendly, mostly GUI-driven capabilities for rapid pre- and post-processing that will considerably decrease model generation effort and analysis/sensitivity cycle time compared to currently available tools.  ASE toolbox users will have access to customizable databases containing organizational knowledge and standards for flight vehicle material properties, construction details, actuator/sensor models, airfoil shapes, etc.  Model construction will be fully automated, eliminating time-consuming manual pre-processing.  A full-range of ASE analyses and design sensitivities will be available within the MATLAB/Simulink environment.  Utilities will be developed for importing and exporting computational model data (FEM, CFD, DLM, etc.) and results to and from the major commercial analysis codes.  Key innovations include: 1) rapid model development, analysis, and optimization; 2) integration with the widespread and highly accessible MATLAB/Simulink computational environment; and 3) connectivity from MATLAB to more general purpose codes such as NASTRAN for higher fidelity follow-on analyses and model refinement.
This proposal describes the development of passive surface acoustic wave (SAW) based hydrogen sensors for NASA application to distributed wireless hydrogen leak detection systems.  Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C.  The proposed hydrogen sensors will use a novel OFC SAW device structure, combined with Palladium nanocluster film elements to produce fast, reversible, highly sensitive hydrogen sensors capable of detecting a wide range of hydrogen concentrations at room temperature.  The proposed research will utilize results from Argonne National Labs on the formation of Pd nanocluster films on self-assembled siloxane monolayers on glass.  These optimized nanocluster films demonstrated hydrogen sensing from 25 ppm to over 2&#37; hydrogen, with response times of milliseconds, complete reversibility, and no baseline drift at room temperature.  The films experience large conductivity changes due to the hydrogen induced lattice expansion of the Pd nanoclusters and the quantum nature of conduction in nanocluster films.  The performance of the SAW device will change in response to a change in conductivity of this film.  Issues including SAM formation on piezoelectric substrates, nanocluster film deposition, and simulation of device performance will be evaluated.
This proposal describes the development of passive wireless surface acoustic wave (SAW) based liquid level sensors for NASA application to cryogenic liquid level sensing.  Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C.  The proposed liquid level sensors will use damping of the acoustic wave caused by mass loading of the liquid to produce fast, reversible liquid level sensors.  The proposed research will apply the results of ongoing work on OFC sensors and will evaluate their operation as liquid level sensors in selected liquids of interest at cryogenic temperatures.  Issues to be investigated include the stability of various SAW substrates when exposed to various (extreme and gradual) temperature changes, the effects on device integrity and performance of thermal cycling to cryogenic temperatures, and the effects of device exposure to various liquids and the reversibility thereof.  The result of the proposed research will be an understanding of potential failure mechanisms in SAW sensors used at cryogenic temperatures, knowledge of the required operating parameters to ensure device reliability under likely operating conditions, and demonstration of the use of OFC SAW sensors for liquid level detection.
A device to produce electron beams from magnetized plasma created with rf fields combined with electron extraction by electron sheaths is proposed. The source can provide electrons for neutralizing positive ion beams emerging from ion thrusters or as a generic electron source.  With hollow cathode sources currently employed to provide neutralizing electrons, operation is limited in time and/or current density by cathode deterioration. RF electron sources provide an alternative approach that does not consume electrode material.  The current from this Non-ambipolar Electron Source (NES) exceeds the current normally extracted from conventional rf plasma sources by a factor of (mi/me)1/2 where mi and me are the ion and electron mass.  Ions are lost to a negatively biased conducting cylinder with area Ai chosen to be Ai &amp;#8805; (mi/me)1/2 *Ae where Ae is the electron extraction area. Slots in the conducting cylinder allow the cylinder to serve as a Faraday shield to reduce capacitive coupling from the antenna to the plasma.  Proposed phase 1 design improvements should result in electron currents comparable to hollow cathode sources with lower neutral gas flow in the inductive discharge phase and higher currents with helicon operation.  Phase 2 will develop prototype sources suitable for spacecraft testing.
Currently, the state-of-the-art in space asset tracking and information management is bar-coding with relational database support. To support NASA's need for reliable and low-cost asset management, Payload Systems Inc. and MIT propose to develop Rule-based Analytic Asset Management for Space Exploration Systems (RAMSES) ? an intelligent space exploration environment in which information is shared and automatically harmonized among disparate data sources. This information is then combined with mathematical models and rule-based analysis to produce meaningful data for asset tracking and intelligent decisions. The combined data will communicate with analytic models that provide analyses, estimates, predictions and plans. This intelligent space exploration environment will be equipped with sensors, radio frequency identification (RFID) equipment and sophisticated information infrastructures to make full use of multiple data streams.
We will design and implement an interface between the Paramesh computational libraries, developed and used by groups at NASA GSFC, and the Cactus computational framework, developed primarily by scientists at Louisiana State University, the RI on this proposal.  Our innovation falls in the domain of adaptive mesh refinement (AMR), a technique to focus computational resources in regions of small scale dynamics.  Our approach is innovative as it brings together one of the leading AMR packages (Paramesh) with Cactus, a widely used modular, parallel problem solving environment that is supported on multiple computing architectures.  Our innovative proposal responds specifically the to the "Computing" subtopic in the solicitation in three areas:  It will (1) reduce costs for current Paramesh users at Goddard, by providing access to the wide variety of validated tools already available through Cactus and which would otherwise need to be redeveloped at NASA; (2) facilitate sharing of novel algorithms between Paramesh and Cactus users worldwide through the existing and proven interoperability features provided by Cactus; and (3) position Paramesh users to benefit from the many next-generation computer science innovations that are actively researched by the core Cactus development team (such as grid computing) and other Cactus contributors.
In integrating the following three significant components for its research/research and development (R/R&amp;D) effort, the power of this candidate Phase I project will be demonstrated through the Collaborative Virtual Environment Simulation Tool (CVEST):

1.	Software Application Development Toolkit 
2.	Physiological Hardware Interface
3.	Technology Integration Manager

The multi-faceted CVEST development environment operates as a plug-and-play interface to various software and hardware products specializing in virtual reality-based simulation development.  The final Phase I demonstration will feature the muscular mass/tissue deformation within a digital virtual human interface (DVH) to show performance data (physiological, biomechanical, etc).  

This STTR Phase I candidate project will concentrate on some new physiological hardware/haptic devices to produce tactile feedback to the user.  These range from gross or large object reporting to more fine-grain/granular tactile sensing to thermal sensing devices.  In addition, a COTS-based Global Position System (GPS) will be analyzed as wireless tracking source for the user.  

For NASA and commercial domains, this Phase I simulation facility, with its physiological/biomechanical functionality, could be implemented in software and integrated to enable realistic simulations of the forces exerted on and by users (astronauts, divers, etc.) as they work in various environments.
HyPerComp Engineering Inc. (HEI) and Utah State University (USU) propose to develop technology for lightweight composite materials for use in composite structures suitable for both cryogenic and damage tolerant environments. The proposed effort will incorporate previous work performed by HEI in the cryogenic performance of composite materials as well as previously developed improved impact technologies for micro-meteor/space debris survivability.  The application of filament wound composite pressure vessels in pressurized storage tanks at cryogenic temperatures has been undertaken at HEI and NASA MSFC with promising results.  Likewise, HEI has been conducting research and has patented, jointly with NASA MSFC, a robust impact resistant composite pressure vessel technology.  This technology shows great promise in its resistance to performance degradation from impacts, such as those that might be experienced in the space environment in the form of micrometeoroids and space debris.  Both of these technologies have been characterized for lightweight composite pressure vessels separately.  However, little if any understanding currently exists of their combined potential for both cryogenic and impact resistant composite structures applications, of those including, composite overwrap pressure vessels (COPV's).  The combination of the foregoing cryogenic technology with an impact resistant, robust composite pressure vessel technology would be studied.  Further, we believe, that combining these two technologies will provide a baseline technology from which to develop a dual-use composite structure.  This would be to ensure the integrity of the light weight composite structures, such as cryogenic fuel is stored in an orbiting depot, when exposed to the harsh environment a spacecraft will be expected to encounter during the life of its mission.
The goal of this SBIR Phase I research project is to develop batteryless, wireless magnetic sensors with orthogonal frequency coding (OFC).  These sensors will be based on surface acoustic wave (SAW) technology already in common use in microwave filters and signal processing elements for communications devices.  We will develop new magnetostrictive structures to be combined on-chip with SAW devices to create innovative magnetic field sensors that can be individually interrogated from a distance with a microwave reader.  Combining the magnetostrictive materials with OFC SAW transponders will provide new sensor capabilities that are compatible with the orthogonal frequency coding scheme recently demonstrated under NASA funding.   The novel magnetic field sensors will be individually coded, inexpensive to manufacture, and require no on-board power?making them ideal for distributed and embedded monitoring technologies, for both government and commercial use.
Encouraged by Phase I accomplishments, the proposed Phase II program will significantly mature and align the development of a Space Qualified Non-Destructive Evaluation &amp; Health Monitoring system with the needs of NASA. We are systematically working to improve the TRL to 5 at the end of Phase II and formulate commercialization and product development strategy beyond Phase II.

The proposed health monitoring system features three innovative technologies: excitation of preferential Lamb/Rayleigh wave modes; utilization of phased array concepts; and utilization of software algorithms rather than hardware for beam forming and signal analysis. The ability to detect cracks, corrosion, disbonds, and cracks under bolts for a stiffened panel was demonstrated in Phase I. The detection methods used were pitch-catch, pulse-echo, phased array, and electromechanical impedance.

To efficiently and cost-effectively achieve Phase II objectives, NextGen has teamed with Lockheed Martin Space Systems - Michoud Operations to test the proposed system in realistic environment. A cryogenic, composite LOX tank, built by Lockheed Martin for the X-34, is currently in a test fixture at NASA Marshall and will be used for evaluating our system. Additional tests will be performed to validate the durability and survivability of the system for space certification.
Luna Innovations has teamed with the University of Alabama, Huntsville, to develop a miniature flush-mounted fiber-optic pressure sensor that will allow accurate, high-frequency high-pressure measurement of LOx and LH2.  The Innovation of this proposed development is that the miniature flush-mounted fiber-optic pressure sensor is not intrusive, is intrinsically safe, and is a novel adaptation of proven technology.  To insure compatibility with the LOx environment, the sensor has been constructed from metal-oxides, ceramics and other materials that are intrinsically safe.  The sensor will help engineers optimize performance of liquid fueled rocket engines for the next generation of reusable lift vehicles, and flight versions of the sensors will enable real-time monitoring and control of the engines, improving safety and enabling commercialization of space.  During the Phase I, prototype sensors were demonstrated in Liquid Oxygen (LOx) at temperatures of -196&lt;SUP&gt;o&lt;/SUP&gt;C.  The sensor was able to measure pressures over 1000 psi and transients exceeding 4500 psi/sec rates of change without failure.  During the Phase II, optimized thermally compensated sensors will be constructed and extensive tests conducted to advance the technology to pre-production status.  This system meets NASA's goals by providing LOx and LH2 pressure data while: 1) minimizing intrusion, 2) improving reliability, 3) having fast response time, and 4) being intrinsically safe.
Industry is driven by the cost of man-power and time to market, and is still awaiting a versatile and reliable multi-disciplinary analysis code. The proposed JFLO software suite addresses many aspects that are still not totally resolved in current state-of- the-art  CFD. It will enable optimal designs as well as the multi-disciplinary application of CFD for digital flight. The key elements of JFLO are : ease of use; broad analysis capability for 3D steady and unsteady applications for the entire range of speeds for low Mach to supersonic, high-resolution mesh-blind solution algorithms and CAD-blind surface reconstruction, mesh-and user-independent results via CAD-respecting mesh adaptation, fast solutions via advanced convergence acceleration techniques, and above all reliability and high accuracy. It weaves together technologies that have been recognized in their individual right: optimal control design, coupled CFD and CSD and automatic mesh optimization. Here they are brought together in a single package for the first time.
Future NASA space exploration missions will use nanometer-scale electronic technologies which call for a shift in how radiation effects in such devices and materials are viewed. The energy deposition by ionizing particles (so called single event effects) can no longer be treated as an average deposition (linear energy transfer, LET). Nano-scale electronic device responses are strongly related to the microstructure of the radiation event. This requires a much more detailed physics-based modeling approach. It is also important to convert such results into engineering models used in device and circuit designs. Hence, the proposed innovation: detailed high-energy-physics-based simulations of radiation events efficiently coupled with advanced device response computations. The innovative Technology Transfer: interface specification and implementation to allow smooth, automated integration between Vanderbilt University high-energy particle advanced computations and CFDRC Device Simulator, and to enable statistically meaningful runs on a massively parallel supercomputing cluster. Significance for NASA:  the impact of such radiation events has implications for nano-scale devices operating in space exploration environments. The new approach to understanding the single-event response of semiconductor materials, devices, and circuits is necessary for reliable engineering models used for early design assessment, radiation hardening, and to reduce the amount of radiation testing cost and time.
The current state-of-the-art in DEM modeling has two major limitations
which must be overcome to ensure that the technique can be useful to
NASA engineers and the commercial sector: the computational intensive
nature of the software, and the lack of an established methodology to
determine the particle properties to best accurately model a given
physical system.   The proposed work will address both of these
limitations. We will look at two approaches to overcome the particle
count limitations of DEM: investigate the scaling up of particle size;
and combine FEA and DEM to look at problems of densely packed solids. We
will explore regimes where DEM and FEA are applicable and establish a
coupling methodology that can be further developed during phase II.  To
address the lack of an established methodology to determine the particle
properties to best accurately model a given physical system, we will
investigate several small scale experiments that can be used to
characterize DEM models. The proposed work will advance the
state-of-the-art in DEM.  At the end of phase I we will show the
feasibility of developing modeling approaches to overcome the main
limitations of DEM.
There are several objectives of this Phase I proposal.  One major objective is to investigate SAW sensor embodiments for pressure and acceleration.  Two approaches will be studied, one using the SAW substrate as both the sensor and the communication link, and a second approach using the SAW device as a communication link for an external sensor.  The approach will use wireless, passive SAW coded devices, building on previous orthogonal frequency coding, and also investigating different approaches, such as phononic structure coding and combinations of coding techniques.  A second major objective is to investigate and propose a complete device-transceiver sensor system, such that a complete sensor system will be realized.  This is crucial to the success of the fielding and commercializing the SAW sensor technology, since it enables the interrogation of the tags and will ultimately lead to a commercial, manufacturable sensor product.  A third major objective is to study important ancillary technology issues: the antenna, the packaging, and the coding used for the sensor identification.  The results of this Phase I proposal will yield a vision towards the building of a complete SAW sensor system for pressure and acceleration measurements.
An integrated computational environment for multidisciplinary, physics-based simulation and analyses of airbreathing hypersonic flight vehicles will be developed. These vehicles are among the most promising alternatives for the next generation of Highly Reliable Reusable Launch Systems (HRRLS). The proposed work will enable development of models with varying fidelity, incorporating the coupled dynamic elements resulting from the tightly integrated airframe-engine configuration. These will include aero-propulsion and aero-elastic interactions as well as thermal loading. The effect of unsteady aerodynamics and nonlinear phenomena such as shock-shock interaction on vehicle performance will be evaluated. Simple and intuitive models for control design as well as high fidelity models for validation and simulation will be developed. The investigators' extensive experience with multidisciplinary software such as STARS and FLUENT will be an asset in this regard. Rather than creating completely new suit of software the approach proposed here is to develop new software when necessary but also produce codes which will enhance the present capabilities of existing software to handle coupled aero-propulsion as well as aeroelastic effects. The methods and products developed in this effort will significantly enhance the present capabilities for modeling, simulation, and control design, for airbreathing hypersonic flight vehicles.
In this proposal, we describe a program to demonstrate the technical
feasibility of a high-performance, cost-effective and robust microwave
receiver for the detection of laser-generated ultrasound for NDE. Our
innovative receiver is based on the integration of a microwave
interferometer coupled with a pulsed laser to generate the ultrasound.
By using a microwave interferometer design we will be able to overcome
the limitation generally associated with classical optical receiver: 1)
Inability to work in harsh environment where thermal and mechanical
perturbations are present; 2) Reduction in sensitivity caused by the
speckle nature of the light reflected from rough surfaces; 3) High
system cost due the price of the different lasers, optics and
engineering to develop an optical system working in a harsh environment
and 4) high maintenance cost (Lasers and optics need to be checked,
maintained and re-aligned frequently).
The overall objective of this STTR effort is to evaluate and demonstrate the potential for well-designed, strategically-located synthetic jet actuators to provide improved aircraft safety by: (1) delaying wing stall and improving aircraft controllability at high angles of attack and (2) providing low-cost actuation redun-dancy to improve controllability in the event of a mechanical control surface failure.  Delaying flow separa-tion (i.e., wing stall) and providing "back-up" control power could allow an aircraft to recover from adverse conditions (due to a control surface failure, pilot/autopilot error, etc.) that would otherwise result in a loss of control.
Flow control studies have shown that synthetic jet actuators are efficient devices for controlling separated internal and external flows.  However, an obstacle to the widespread application of synthetic jet actuators for practical flight control is that modulated input signals to achieve closed-loop flow control objectives have been shown to be complex.  Barron Associates, the University of Virginia, and the University of Wyoming propose to develop a software toolbox for the creation of adaptive control systems for actuators having complex, nonlinear dynamics.  The Phase II effort will culminate in a wind tunnel test that quanti-fies the safety improvement potential offered by adaptively-controlled synthetic jet actuators.
In the future, exploration missions will benefit greatly from advanced metrology capabilities, particularly structural health monitoring systems that provide real time in-situ diagnostics and evaluation of structural integrity. Safety- and mission-critical components and systems will be instrumented with embedded sensors to provide a real-time indication of health, helping to ensure that America's space exploration remains safe and cost efficient. One of the most promising technologies for accomplishing this is fiber-optic sensors. Due to their light-weight and multiplexing potential, fiber-optic sensors are highly desirable for employment in this fashion. However, most commercial fiber-optic sensor interrogators are bench sized units and are too large and heavy to be easily integrated for space-based applications.

To address this shortcoming, Luna Innovations proposes to develop a compact, light-weight, multi-parameter distributed fiber-optic instrumentation system based on the OFDR technique. The interrogator will incorporate photonic integrated circuit technology, a highly integrated swept-wavelength laser, and state-of-the-art integrated processing technology to dramatically reduce the size, weight, and cost and to dramatically increase the performance and robustness relative to existing technology. This interrogator will interface with fiber-optic strain, temperature, and shape sensor arrays, enabling simultaneous interrogation of a multitude of sensors, dramatically reducing the per sensor cost of instrumentation.
This STTR project aims to develop a process-hardened, simple and low cost multi-analyte sensor for detecting components of rocket engine plumes. The sensor will be constructed with materials for operating continuously at 550 OK. It will also withstand temperatures as high as 2100 OK for at least five seconds.  NASA roadmaps point towards new hydrocarbon fueled engines. A non-intrusive instrument suitable for monitoring plume signature with high degree of reliability will facilitate this future development. Tasks are designed to establish the device feasibility by detecting carbon dioxide and kerosene in air over 0-1&#37; (v/v) range in the presence of 100&#37; moisture. The sensor array chip is capable of holding indicators for tens of analytes. A major aerospace company has expressed strong interest in the proposed technology for integrating in their test facilities.  InnoSense LLC (ISL) will develop, characterize and field-test the prototype in Phase II. For assuring success of this project, ISL has assembled a technical team with a cumulative 90 person-years of experience in developing commercially viable sensor systems.
The bone loss associated with extended space missions in astronaut
represents a serious health threat, both over the flight period and upon
returning to gravitational fields. Continuously monitoring bone
qualities during prolonged space missions will lead to a better
understanding of the progressive adaptation of bone loss in astronauts
subject to both microgravity and aging, and the ensuing musculoskeletal
complications such as osteoporosis. In this proposal, Boston Applied
Technologies Incorporated (BATi), collaborated with University of
Florida, proposes a portable and noninvasive ultrasound measurement
apparatus for rapid assessment of human bone densities. With our unique
approach and algorithm, the proposed device will have greater
measurement accuracy and sensitivity than those of other noninvasive
techniques. In addition, the self-calibration feature of the instrument
will assure the diagnostic methodology to be accurate, fast, and simple.
For NASA exploration missions to the Moon and Mars, medical grade water generation is a necessity. Adsorption filter technology has shown some promise, but requires transport of disposable/replacement filter cartridges, which adds to the overall mass/volume of the system for medical grade water generation. Distillation and reverse osmosis are other techniques that are used to generate medical grade water. However, power requirements, processing rates, and microgravity affects render these techniques undesirable for NASA missions. Therefore, we propose to develop a compact, low-power nanofiltration system for the generation of medical grade water. The key nanofiltration component will be a soda can-sized package housing a stack of silicon nanoporous membranes to process onboard potable water. The system would generate ~2 liters/hour of purified water with &lt;1 psi differential driving pressure. In Phase 1, we would complete fabrication of silicon nanoporous membranes, test them for nanofiltration of endotoxins, and develop an optimized design for the next generation of miniaturized nanoporous membranes. In Phase 2, we would fabricate the optimized design, manufacture a portable medical grade water generator based on the optimized design, and test the system for endotoxin filtration.
Science and Technology Applications, LLC's (STA) vision for a versatile space propulsion system is a highly throttleable, high performance, and cost effective Liquid Oxygen/Hydrogen engine utilizing innovative design and manufacturing processes to simultaneously meet NASA's Space Exploration requirements. To that end, an innovative injector element concept is proposed consisting of axial flow coaxial injectors with pintle center post. This element concept is expected to provide deep throttle capability while maintaining performance over the entire range. Cold flow tests will be performed to characterize mixing and atomization distribution.
We propose here to develop tunable diode laser spectroscopy as a diagnostic for the Space Shuttle main engines during test stand operations. These engines represent the state-of-the-art in rocket engine propulsion systems, and as such, they stretch available technology to the limit. The engines must be test-fired through several cycles prior to incorporation into the shuttle for flight operations. Diagnostic tests for the engines are extremely limited due to the harsh nature of the environment. We propose to develop diode laser instrumentation in order to measure temperature, velocity, surface erosion, and possibly efficiency in real time with an update rate of up to 1 kHz. The system technology will be based on wavelength multiplexed tunable diode laser spectroscopy which Zolo and Stanford have jointly developed to diagnose many types of aeropropulsion systems including SCRAMJETs, augmentors, and pulsed detonation engines. This project represents the first time that the wavelength-multiplexed technology will be tested on full-scale rocket engines.
To address the need for non-intrusive sensors for rocket plume properties, we propose a laser-based velocity diagnostic that does not require seeding, works in high or low temperature flows, and can be used over a broad range of velocities. Hydroxyl tagging velocimetry (HTV) "writes" a line of OH molecules into the flow and interrogates them after a short delay to determine the velocity. Since the markers are molecules, the method measures the gas velocity directly, avoiding errors due to particle drag associated with seeded techniques. The only requirement is that H2O molecules must be present in the flow, which is easily met by most rocket plume applications. Because OH molecules survive at high temperatures for appreciable lifetimes, it is anticipated that the HTV technique will work in even the highest temperature rocket plumes. The proposed diagnostic will provide measurements not obtainable by current methods, and will enable experimental data that can be used for validating computer models for rocket engine performance predictions.
Radiative heat fluxes are important in the design of launch vehicles for Project Constellation.  In this Phase II STTR, CFDRC and its partner Mississippi State University will develop an innovative, comprehensive, high fidelity radiation module in the LOCI CFD framework that will enable NASA to design/analyze heat transfer challenges that include radiation.  In Phase I, CFDRC/MSU successfully demonstrated the feasibility of developing a radiation module in LOCI-Chem.  A preliminary module was developed that included a gray gas model, as well as simplified nongray gas and particulate radiation capabilities.  Following successful implementation and validation, LOCI-Chem with the radiation module was successfully applied to a Solid Rocket Motor (SRM) plume on a launch pad as a demonstration case.  The proposed Phase II effort continues the development by: 1) implementing more accurate, robust nongray gas and particle radiation models, 2) increasing tool-fidelity by developing innovative methodologies to minimize modeling uncertainties, 3) formally verifying the module using the Method of Manufactured Solutions (MMS), and 4) validating the module and applying it to cases of direct relevance to NASA.  NASA, ATK, and Pratt &amp; Whitney Rocketdyne will be beta testers of the software in Phase II, and provide user feedback. At the end of Phase II, a final version of the software with full documentation will be delivered to NASA.
The intent of the proposed effort is to investigate the detailed composite material performance characteristics after being subjected to cryogenic temperatures and impact damage.  HyPerComp Engineering, Inc. (HEI) and Utah State University (USU) further propose to correlate these characteristics to composite overwrapped pressure vessels (COPVs) and demonstrate the correlation through actual COPV testing.  This will result in a safer, more reliable design for high performance COPVs in a cryogenic environment.

HEI and USU also propose to study the cryogenic bond necessary between composites and aluminum for thin walled aluminum lined COPVs to prevent the buckling of the aluminum during depressurization.  This intent will be demonstrated by actual pressure vessel testing.
In completing the Phase I SBIR, Agave BioSystems and the Universities Space Research Association, have successfully demonstrated proof of concept for the use of novel carbon nanotube (CNT)-based structures as next generation smart adsorbents for the adsorption and destruction of potentially toxic air contaminants.  Since CNTs have an extremely high surface area, can be readily modified with metals or functional groups, and can function without the mass transfer limitations of traditional activated carbon, they are an ideal material for integration into spacecraft air handling systems.  In the Phase II program, we will build upon the unique structural and chemical nature of carbon nanotubes to construct a prototype system utilizing these smart adsorbents.
The Integrated Data Assimilation Architecture (IDAA) addresses the fundamental problem of command, control, and communications systems interoperability.  Interoperability of Explorations systems is necessary to improve reliability, reduce complexity, increase software and hardware reusability, and enable multi-developer / multi-agency support. The IDAA architecture consists of a software component, the BioNet middleware, and a hardware component, a Mobile Data Acquisition and Communications processing System (MDACS).  Development and advancement of the BioNet middleware was the primary focus of the Phase I STTR effort.  Continued BioNet middleware development will occur as a proposed Phase II activity along with the development of the MDACS generic hardware platform.  From a functional perspective, the BioNet middleware provides a standards-based command and control capability, while the MDACS provides a generic space-rated hardware platform for general-purpose computations and communications.
Sierra Engineering Inc. and Purdue University propose to develop a non-intrusive plume instrument capable of detecting and diagnosing combustion instability.  This Stability Diagnostic System (SDS) will be designed, assembled, and tested during this effort.  The SDS will include a high-speed video camera and multiple photodiode detectors for observing the plume.  It will also include a software package, which will aid in analyzing the plume data and in determining the acoustic modes of the instability.  To ensure that the system works properly, Sierra and Purdue will leverage an oxygen/kerosene combustor, developed under AFRL funding, to operate with unstable combustion.  Technology previously developed at Purdue will be used to modify the engine's injector so that the combustion instability occurs.  The dirty (soot laden) plume produced by this combustor better simulates the conditions present in full-scale hydrocarbon fueled engines.  Finally, the methodology for predicting combustion response from plume observations, developed under the Phase I effort,  will be matured.  The SDS system and accompanying software will be delivered to NASA for future application on NASA test facilities.  Successful completion of this project will provide a non-intrusive tool for detecting and diagnosing combustion instability that is superior to current, intrusive methods.
Balcones Technologies, proposes to adapt actively controlled suspension technology developed for high performance off-road vehicles to address NASA's requirement for Active Vibration Control for Ground Support Equipment (GSE).  This innovative approach to meeting NASA needs exploits approximately $23M of highly successful R&amp;D since 1993 at the University of Texas Center for Electromechanics (CEM) on active suspension systems for off-road military vehicles.  STTR subtopic T6.02 indicates that previous experience on NASA's Mobile Launch Platform (MLP) shows that passive vibration isolation systems are inadequate and that actively controlled vibration isolation systems to supplement or replace existing passive systems will most likely be required.  Initial modeling of this system by CEM indicates that our team's proposed actively controlled Vibration Isolation System (VIS) provides more than an order of magnitude improvement in vibration isolation compared to conventional approaches (see proposal Part 4 for details).  Our actively controlled VIS offers unique benefits compared to conventional passive systems because it mimics compliant attachment to inertial reference systems rather than attachment to local reference systems on the vibrating MLP; eliminates resonant peaks associated with passive systems (i.e., our system has flat response at low frequencies); and provides 10 to 16 times better vibration isolation over most of the frequency range of interest than conventional systems.  Based on our vehicular active suspension results and preliminary modeling described in proposal Part 4, our proven design approach will yield robust solutions that are not sensitive to variations in GSE electronics racks or MLP excitations during shuttle launch.  This approach fully meets all requirements defined or implied in STTR 2007-1 Subtopic T6.02.
T3RSS is the system engineer's tool that allows a systematic approach to ensuring that even if one or more failures occur in a single component or subsystem, then the subsystem will continue to function and most, if not all, mission objectives can still be achieved. T3RSS does this by using a Configuration Manager for a Dynamically Reconfigurable System (CMDRS). This piece of logic employs a Mission Survivability Assurance Algorithm (MSAA) for the subsystem.  Should radiation, manufacturing or even launch damage render a particular region of the FPGA temporarily or permanently unusable while on orbit, then the MSAA can shift the critical logic to a new region, or even to a new FPGA altogether. The shifting logic uses a network of components to maintain the ability of each logic block to communicate with the required memory and hardware. Ensuring that needed logic is always available ensures that the satellite can maintain 100&#37; mission survivability even during failures.
Our proposed future Phase II activities are aimed at developing a scientifically based "tool box" for flight research using scaled models. These tools will be of great use for GA companies in the design, development, and FAA approval of future general aviation (GA) aircraft, in particular also when novel technologies such as active flow control, circulation control, etc. are being considered. We will demonstrate that time, cost, and risk associated with the development and flight testing of future GA aircraft and GA relevant technologies, can be greatly reduced by performing part of the flight research program using dynamically scaled models. As part of the proposed activities we will design, construct, and perform flight research with a 1/3 dynamically scaled model of the Cirrus SR22.
Payload Systems Inc. (PSI) and the Massachusetts Institute of Technology (MIT) were selected to jointly develop the Rule-based Analytic Asset Management for Space Exploration System (RAMSES) in this NASA STTR project. This system implements a modular layered architecture that enables automated multi-level asset tracking and management for both space and ground applications based on state-of-the-art RFID technology. The main advantages of this system over current bar-code based asset tracking are: (i) significant time savings through automation, (ii) real-time remote status monitoring through the internet, and (iii) rule-based analytics for proactive asset management.

In Phase 2 we propose to redesign the Smart Container by taking advantage of Generation 2 RFID tag technology, lightweight RFID readers and batteries as well as integrating container technologies in a more tight and robust manner. We plan to build a total of three (3) smart containers to demonstrate scalability of the system and interaction among containers. The RAILS software will be upgraded to provide enterprise-level capabilities such as user authentication, inventory and item time history analysis, and an expanded analytic rule set. Testing will be conducted both in the laboratory and in the field to demonstrate seamless three level tracking (container level, room level, outdoors). Finally, we will perform a detailed RAMSES cost/benefit analysis and market survey in preparation for Phase 3.
During the phase I program Northwestern and APS, Inc., have manufactured several different materials systems that are lighter than Beryllium and stiffer than Aluminum.  These high specific strength materials are also easily fabricated into larger shapes or even net shape processed. The mechanical (tensile and modulus) and thermal physical (CTE, thermal conductivity) property data for several systems never before manufactured, will be presented as well as fabricated coupons, mirrors, structures and other parts will be available for review.  Several different diameter parts ranging for 3" to 11" have been demonstrated.  These various extremely lightweight systems are easily machined, threaded/joined and have highly variable properties, including variations of thermal conductivity, and radiation hardening/protection capabilities. Phase II will continue with this success for mirrors an dlightweight structure.
ENTECH, Auburn, NASA, and others have recently developed a new space photovoltaic array called the Stretched Lens Array (SLA), offering unprecedented performance (&gt;80 kW/cu.m. stowed power, &gt;300 W/sq.m. areal power, and &gt;300 W/kg specific power) and cost-effectiveness (&gt;75&#37; savings in $/W compared to planar arrays).  SLA achieves these outstanding attributes by employing flexible Fresnel lenses for optical concentration (e.g., 8X), thereby minimizing solar cell area, mass, and cost.  SLA's small cell size (85&#37; less cell area than planar high-efficiency arrays) also allows super-insulation and super-shielding of the solar cells to enable high-voltage operation and radiation hardness in the space environment.  Recent studies show that SLA offers a 3-4X advantage over competing arrays in specific power for many NASA Exploration missions, and that SLA is ideally matched to Solar Electric Propulsion (SEP) applications, which can save NASA &gt;$10 billion for lunar exploration cargo transportation.  In Phase II, ENTECH and Auburn will perform critical ground tests, including an advanced solar concentrator (1 kW, 600 V, color-mixing lenses, multi-junction cells) direct-driving a Hall-effect electric thruster, and SLA/thruster plume interaction tests.  After Phase II, SLA for SEP technology will be ready for flight testing in preparation for many NASA, DOD, and commercial missions.
In integrating the following three significant components for its research/research and development (R/R&amp;D) effort, the power of this candidate Phase II project will be demonstrated and developed the following
1. Software Application Development Toolkit for Simulation and Training 
2. Physiological Hardware/Software Interface for Dynamic Balance Trainer.
3. A Data Glove and control system captures the motion of the Robonaut hand and finger
The multi-faceted CVEST development environment operates as a plug-and-play interface to various software and hardware products specializing in virtual reality-based simulation development. The final Phase II demonstration will feature to show the CVEST toolkit for the CEV Seat design concept

This STTR Phase II candidate project will concentrate on some new physiological hardware/software devices to produce a Dynamic Balance Trainer System to improve Post-flight Locomotor Performance.

Lastly STTR Phase II candidate project will develop and demo a prototype concept device to capture the positional and rotational of the Robonaut hand
Our proposal and the Phase I work completed under it addressed these NASA-identified needs by providing software infrastructure that provides physical scientists a "plug-and-play" architecture in which they can insert their "physics kernels" and exploit very large existing code bases for the computer science aspects of the problem.  In particular, our STTR product provides cutting-edge adaptive mesh refinement (AMR) capabilities, and our Phase I results demonstrate the ability of our software architecture to run existing physics code with the newly incorporated AMR driver.  Our innovative solution to the problem delivered significant value to NASA at a relatively small cost by combining existing open source tools.  In Phase I, we built an interface, which we call Parca,  between the Paramesh computational libraries, developed at NASA GSFC to support AMR computations in the area computational hydrodynamics, and the Cactus computational toolkit, which is an infrastructure package developed by Louisiana State University that provides a "plug-and-play" framework for cross-institution and cross-disciplinary scientific codes.  Both of these software packages have large user bases in the areas of computational fluid dynamics and numerical general relativity, and both had existing users at NASA GSFC.  Prior to our Phase I work, there was no way these user communities to collaborate directly, leading each user group to redevelop software already available in the other user community.
Under NASA Phase I funding, we have developed a system for the ball bearing fault detection and identification. Our system can effectively identify multiple fault modes related to the evolution of friction within the contact in the coated ball bearings. To detect bearing faulty modes, we have developed a new bispectrum and entropy analysis method to capture the faulty transient signals embedded in the measurements. To classify the fault modes, we further developed a set of stochastic models using hidden Markov model (HMM) and Gaussian mixtures. Test results using lab experiment data have shown that our system can identify coated ball bearing fault modes in near real-time. In Phase II, we will further develop and test our system developed in Phase I for spacecraft mechanical parts health monitoring and mitigating actions. A thorough understanding of the failure mechanisms of the moving parts will emerge by the end of the Phase II effort, as well as the methodology to prevent catastrophic failure while in orbit. Algorithms developed in Phase I/II will be implemented in C/C++. Effort will be focused on the accuracy, autonomous, speed and efficiency of the system. The Boeing Company has teamed with us for Phase II effort.
This proposal describes the continued development of passive wireless surface acoustic wave (SAW) based liquid level sensors for NASA application to cryogenic liquid level sensing.  Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C.  The liquid level sensors use damping of the acoustic wave caused by mass loading of the liquid to produce fast, reversible liquid level sensors.  The Phase I research successfully demonstrated operation of these devices as liquid level sensors in selected liquids of interest at cryogenic temperatures.  Stability of selected commercially available SAW devices was confirmed, both when exposed to various (extreme and gradual) temperature changes, and upon repeated exposure to liquid nitrogen.  The reversibility of the device response was confirmed. Phase I demonstrated the technical feasibility of using these sensors for cryogenic liquid level monitoring of low to moderate pressure liquids (under 500 psi).  Phase II will result in prototype product development.
This proposal describes the continued development of passive orthogonal frequency coded (OFC) surface acoustic wave (SAW) based hydrogen sensors for NASA application to distributed wireless hydrogen leak detection systems.  These novel sensors use an OFC SAW device structure, combined with Palladium (Pd) nanocluster film elements and hydrophobic self assembled monolayer (SAM) coatings to produce fast, reversible, highly sensitive hydrogen sensors capable of detecting a wide range of hydrogen concentrations at room temperature.  The technical feasibility of these sensors was clearly demonstrated in Phase I.  The Pd films experience conductivity changes due to the hydrogen induced stretching of the Pd nanoclusters and the quantum nature of conduction in nanocluster films.  The performance of the SAW device will change in response to a change in conductivity of this film.  Rapid (under 1 second) room temperature detection of hydrogen was observed, with complete reversibility of response.  Compatibility of film conductivity with acoustic wave propagation and detection of changes in film conductivity using variations on SAW device delay were confirmed.  Manufacturing compatible processes for SAM deposition and patterning were developed.  The successful elimination of the potential technical risks accomplished in this Phase I effort provides a sound basis for further development of these sensors.
With embedded software becoming ever more complex, assuming that it behaves perfectly is not realistic. The adaptation of fault protection concepts to embedded software is attractive, particularly in the context of the fault containment and health management capabilities provided by ARINC 653. In Phase II we shall develop tools to define simple, verifiable models that characterize the software with respect to its interface behavior, resource usage, and data reasonableness. We shall provide a software framework to instrument and monitor the software as it executes in both test and operational environments. When a deviation from the model is detected, a simple remediation action, including a hard or soft component reset is invoked. These tools will be integrated into ARINC 653 to support fault detection and recovery in an operational context, and the Eclipse software development environment for application in a  test and verification context such as DSIL and engineering analysis context such as  CEAL. Further we shall produce a methodology to assist in certification of instantiations of our software fault protection framework.
Accurate CFD modeling of fuel/oxidizer injection and combustion is needed to design and analyze liquid rocket engines.  Currently, however, there is no mature modeling capability for liquid fuel/oxidizer injectors in LOCI-Chem, used by NASA and its contractors to analyze rocket engines. In this STTR, an innovative, high fidelity injection module will be developed that features the Level Set (LS) interface tracking method coupled with Adaptive Mesh Refinement (AMR).  In addition to tracking liquid atomization for subcritical flows, the module will have the capability to model transcritical and supercritical regimes, as well as transient and steady operating conditions in a cryogenic engine combustion chamber.  CFDRC will team with Mississippi State University to develop the proposed unified module in LOCI-Chem.  To show feasibility, the Phase I effort will implement the LS method to track liquid-gas interfaces, and resolve the primary atomization of liquid jets in a subcritical environment.  Validation will be performed using the shear coaxial LN2/GN2 jet data of AFRL (Edwards AFB).  In Phase II, the LS module will be coupled with the Lagrangian spray model in LOCI-Chem in order to completely track the spray. AMR capability will be developed and integrated with the LS module to improve LS's liquid mass conservation accuracy.  Models for secondary atomization and drop vaporization will be implemented in Phase II, in addition to thermodynamic models to capture transcritical and supercritical combustion.  Final demonstration of the software will include validation against practical liquid propellant injector cases selected in consultation with NASA personnel.
This research focuses on fully developing energy density sensors that will yield a significant benefit both for measurements of interest to NASA, as well as for general acoustic measurements. Previous research has developed prototype energy density sensors. The Phase I research focused on developing effective calibration techniques for these probes, testing and validating the probes to identify the most effective design, developing a sofware interface to facilitate user-friendly data acquisition, and developing software to measure acoustic directivity and sound power using the energy sensors. Phase II research objectives extend the use of these sensors to measure source directivity and sound power. Energy propagation will be determined from these measurements. A major Phase II focus will be the development of a high-temperature, high pressure design for the energy density sensor, as well as investigating nonlinear effects on these energy-based measurements.
NASA applications of the technology include characterizing radiation from rocket plumes to better understand the mechanisms involved and to match numerical codes. Non-Nasa applications are many, including such tasks as in-situ measurements of sound, power and radiation characteristics of sources.
The need for aerodynamics-based efficiency enhancements for air vehicles is presented. The results of the Phase I investigation of concepts for morphing aircraft are discussed. Morphing enables the aircraft to optimize its configuration for various flight regimes. This translates to benefits in range, endurance, manueuvering and speed characteristics of the air vehicle. Using simulations, live testing, and benchtop hardware development, the feasibility of the concepts was established in Phase I. In Phase II, key additions to the design, such as trailing edge flaps, and an intelligent, sense-and-adapt method to achieve continuous aerodynamic optimization flight testing will be integrated. Wind tunnel testing and flight testing will be performed to refine and finalize the designs.
HyPerComp Engineering, Inc. (HEI) proposes to continue the characterization of the cryogenic evaluation of irradiated composite materials for use in composite overwrap pressure vessels COPVs.  The intent of the proposed effort is to study the constituent raw composite material properties that result from radiation exposure and tested at cryogenic temperatures. 

HEI and Mississippi  State University (MSU) have recently completed a Phase I STTR (contract #NNM05AA61C) through NASA/MSFC.  The intent of this effort is to further the development of that key building block technology for lightweight composite structures suitable for cryogenic fuel storage or human in-space habitats.  This effort will incorporate and expand previous work by the participants in the cryogenic performance of composite materials exposed to radiation environments.
The primary focus of Integrated Vehicle Health Management (IVHM) has been on faults due to hardware failures. Yet software is growing in complexity, controls critical functionality under a wide range of conditions and does so with greater autonomy. Furthermore, software errors have negatively impacted major missions.

Runtime recovery from software faults is gaining momentum in research community with major efforts such as the IBM autonomic computing effort and the Stanford/Berkeley Recovery-Oriented Computing project. We propose application of these methods to flight software in the context of JPL's Mission Data System (MDS), an integrated systems and software architecture for next-generation space missions.

Specifically, we consider:

?	Detection and repair of radiation induced Single Event Upsets (SEU) that can either change data values or code.
?	Recovery from bugs manifested as the use of computational resources outside of a specified mode-dependent resource profile.
?	Software organization and infrastructure to help diagnose and limit the impact of errors. We shall study how to restructure MDS as a distributed system with redundant hierarchical components.
?	A recovery strategy based on component-level rebooting. 

This STTR is a cooperative project between the small business Kestrel Technology and NASA's Jet Propulsion Laboratory (JPL).
An Integrated Sensing and Control of Aeroelastic Deformation (ISCAD) Toolbox is proposed. Specif-ically, this toolbox will provide a methodology, both hardware and software, that serves to compensate for uncommanded de?ections of ?ight systems. This toolbox is meant to augment existing procedures for design of both aircraft and autopilots by providing additional capabilities that address aspects unique to for aeroelastic control. The sensors are provided by the ?ow and loads measuring systems pioneered by Tao Systems while the control synthesis builds upon expertise at the University of Florida in ?exible -wing aeroelasticity.  The approach integrates state--of--the -art sensing capability with advanced control synthesis systems.  In this way, a collaborative partnership is formed that is ideally suited to develop the ISCAD Toolbox.
AdTech Photonics, in collaboration with the Center for Advanced Studies in Photonics Research (CASPR) at UMBC, is pleased to submit this Phase II proposal entitled ?High-Performance, Radiation-Hard, 2-D, Near-Infrared, Avalanche Photodiode Arrays? in response to NASA STTR 2004 program solicitation topics: T4.01 Earth Science Sensors and Instruments and T4.02 Space Science Sensors and Instruments. Our goal is to develop high performance avalanche photodiodes (APDs) and arrays with high sensitivity in the 1.06 &amp;#61549;m and the near-infrared 1-1.6 &amp;#61549;m wavelength ranges, which will be used in various NASA applications including interplanetary free space communications, remote sensing, 3-D lidar atmospheric, terrain, and vegetation studies from airborne, UAV, balloon, and space-borne platforms. All these applications will benefit from the improved sensitivity, photon counting rate, and radiation hardness, which will result from this research project.
Proposal Title:
	Aerospace Systems Monitor
PHASE 1 Technical Abstract:
This Phase II STTR project will continue development and commercialization of the Aerospace System Monitor (ASM). This technology transforms the power distribution network in a spacecraft or aircraft into a multiple-use service, providing not only power distribution but also a diagnostic monitoring capability and system health monitoring based on observations of the way in which loads draw power from the distribution service. Careful measurements are made power transients and this data is used to assess system functioning and identify potential faults and failures. In the Phase II project,  development will continue on the ASM software and on power line sensors to obtain data in ground testing and in flight.  ASM will be applied to reaction wheels and momentum wheels.  A test bed will be built and we will demonstrate the ability to verify correct operation and identify faults and flaws in prototype and operational reaction wheels.   Phase III will continue this work and apply it further to reaction wheels and to other systems and components in ground testing and in flight.
We intend to perform a ?Demonstration? Certification of a COTS automotive engine, including and focusing on what is likely to be one of the most challenging aspects of the FAA Engine Certification, the FAA approval of a COTS automotive Engine Control Unit (ECU). 
The COTS automotive based ECU is the most technically challenging system due, not only to the design and manufacturing processes employed in the mass production of the ECU, but because of the ?criticality? of the ECU in the functions it performs on the COTS engine, and the ?criticality? of the ECU when it is integrated within the aircraft system, for the safety of flight.

In addition the COTS automotive ECU contains complex electronic hardware and software, and employs mass production processes, with advanced manufacturing technologies and packaging techniques, which are not currently employed in the production of commercial aviation flight critical digital electronic systems today.

We are confident that the approach taken for the ?Demonstration? Certification of the COTS engine, and the COTS ECU, can then be ?leveraged? into achieving FAA approval of not only all other aspects of the propulsion system, but also into the aircraft flight control systems, including the flight deck electronics, displays, communication and navigation systems.
This work proposes to capitalize on our Phase I success in a novel visible-near infrared Stokes polarization imaging technology based on high performance fast tunable phase retarder and novel algorithms for analyzing and diagnosing biological phantoms and cells. Phase I results have demonstrated the feasibility of this technique in in-vivo analyzing biological phantoms and cells. In this Phase II proposal, Boston Applied Technologies Incorporated, will team up with the Catholic University of America and Georgetown University to further develop this technique and apply it to biological cell analysis. Prototypes Stokes imaging system with real time video will be designed and developed. Computer-aided diagnosis software will be further developed for the imaging system with improved classification accuracy and speed. The Stokes polarization imaging system and its computer-aided diagnosis software will be tested on fresh tissue samples from laboratory animals. The tissues will include normal tissues from multiple organs as well as cancerous tissue from laboratory animals. The Stokes images will be compared to reflectance confocal microscopy images and standard light microscopy images to reveal the polarization fingerprints of biological tissues/cells.
Space exploration is a unique challenge with many difficulties in its implementation. With a goal of the return of man to the moon and travel to Mars, the stage has been set for the expansion of human knowledge beyond comprehension. Traveling to the moon and Mars, however, will require new and innovative technologies. Key to this will be system health management (SHM). For any given system of the myriad that will be required for space missions, a way of safely and efficiently managing the system health will be required. These goals are the motivation behind the proposed Phase II effort.
This work represents the exploitation of a unique method of crystal growth ? constrained epitaxy (CE) ? in the manufacture of low-noise, multi-color UV sensors. The sensors developed here are based on the GaN/AlGaN materials system and are sensitive in the wavelength range from 250-400nm. Target responsivities are &gt; 0.1 A/W throughout the spectral interest range. The first arrays produced under phase 1 were sensitive both to 285 and 315 nm simultaneously. Multicolor sensitivity improves background noise rejection and provides much more detailed analysis of atmospheric aerosol scattering. Noise is dominated by diode reverse leakage and is less than 10-9A/cm2. The CE manufacturing process is enabled by the recognition that surfaces on which radiation sensitive materials are grown cannot be exposed to plasma etch effluents. To overcome this limitation, a dielectric lift-off-lithography process was developed. In this process, the growth surfaces only come in contact with organic solvents and photosensitive plastics during manufacture. Initial results were obtained on a 10 x 10 diode array. In subsequent work, we intend to produce 100 x 100 arrays. In addition, it the range of attainable spectral sensitivities will be mapped out by studying the range of achievable AlGaN stoichiometries that are practically attainable.
The proposed STTR is the combination of a small business with unique materials experience, and Northwestern Unviersity, with expertise in Mirror applications, processing and characterization.  The combination of these two entities with various prime contractors providing assistance makes for a successful STTR program.   The applications for these materials have significant impact on NASA and other commercial entities.  The unique materials being demonstrated under this program also have significant commercial applications.  A successful Phase I will result in the identification of various parts and programs that can be supported by these materials.  Phase II will focus on characterization and qualification of these materials.
The Integrated Data Assimilation Architecture (IDAA) is a middleware architecture that facilitates the incorporation of heterogeneous sensing and control devices into a unifying system with standardized application interfaces.  The architecture is standards-based (IEEE wireless standards) and is an open architecture that can be easily extended.  This system is innovative from several perspectives: (1) the design explicitly supports multiple disparate devices ? to date, wireless middlewares have focused on single device types or single network types; (2) independent development is explicitly supported by means of a published application programmer interface (API) along with system client libraries that provide standard services; and (3) a Development Kit ("DevKit") that includes working examples and source code templates is provided to assist developers in the integration of a new monitoring device and/or the composition of a new application that is a consumer of the data produced by the system.  The proposed system will support the T3.01 Aerospace Communications topic by delivering a hybrid architecture that by design can incorporate multiple heterogeneous wireless devices and networks. Additionally, the IDAA system provides for multi-developer system extensibility, alleviating the problem of a monopolistic single-vendor implementation, where only the original developer of the middleware can efficiently extend the system functionality.
Sierra Engineering and Purdue University propose to leverage combustion stability testing, already funded and planned for the second and third quarters of next year at Purdue, by developing a non-intrusive plume instrument capable of detecting combustion instability and testing it during combustor firings.  Purdue has previously created the combustor and demonstrated unstable combustion operation.  Sierra will apply its experience with plume signature prediction and plume signature tailoring to model the combustor response and estimate the high frequency variations in the combustion process that feeds the instabilities.  Both Sierra and Purdue have expertise in combustion instability and the mechanisms that cause it.  This expertise will be used to develop a methodology, based on plume observations, to estimate combustion burning response and, hence, predict combustion stability margin.  During a Phase II STTR, more testing and higher fidelity instrumentation will mature the methodology for future application to NASA test facilities.  Successful completion of this project will provide a non-intrusive tool for detecting and diagnosing combustion instability that is superior to current intrusive methods.
Spacesuit systems for planetary EVAs must maximize human productivity and provide the astronaut with the capability to perform useful work tasks.  Mide plans to work with MIT to develop mechanisms to augment astronaut productivity during advanced EVA missions.  We propose to demonstrate the feasibility of using shape memory polymers (SMPs) to provide pressurizing life support in the Bio-Suit, an advanced EVA system based on mechanical counterpressure (MCP) that is being designed to provide a "second skin" biomechanically and cybernetically augmented human performance capacity for planetary exploration.  SMPs are "smart" polymers whose pliability makes them comfortable to wear against the skin.  However, their material properties and shape can also be controlled using external stimuli such as temperature, electricity or stress, making them particularly appropriate for use in a "second skin" spacesuit that adapts to the astronaut's shape changes during EVA movements.  Our initiative would be the first-ever demonstration of the use of smart materials in an MCP spacesuit; as such, this innovation could potentially accelerate the development of space-rated MCP suits because it would provide both a means of increasing the pressure production and control whilst maintaining user comfort and usability ? competing requirements which have hindered development of previous MCP spacesuits.
NASA/ Marshall Space Flight Center (MSFC) needs sensors that can be operated on rocket engine plume environments to improve NASA/SSC rocket engine performance.  In particular, NASA/MSFC would like to develop sensors to monitor the performance of rocket engines. The measurement of soot volume fraction and soot particle size can be employed to develop a sensor for on-line, real-time measurements to characterize the performance of hydrocarbon rocket engines and study the effects of the rocket engine exhaust on the environment. The goal of this proposed effort is to develop a laser-induced incandescence (LII) sensor, which is able to provide near real time measurement of soot concentration in the engine plume. During Phase I, a LII system based on telescopic collection optics for remote applications will be designed. The experimental parameters will be evaluated to achieve optimum response time and sensitivity. The study from Phase I will provide the necessary information to improve the phase II prototype design to achieve millisecond response time and better sensitivity. In Phase II, a prototype fieldable LII system will be developed and tested at MSFC and will be delivered to NASA/MSFC for further testing.
Microcalorimetry is an enabling technology for many NASA space science missions because it permits detection of single photons at high rates with unprecedented energy resolution and efficiency. This remarkable technology relies upon superconducting devices that must be cooled below 100 mK. We propose to construct a doubly-integrated circuit in which critical features of microcalorimeter pixels on micromachined thermal isolation structures are cooled by microscale refrigerators that exhaust heat into the substrate at 300 mK. In Phase 1 we will demonstrate a new process for fabricating suspended thermal isolation membranes that is planar and fully photolithographic. A parallel Phase 1 activity will be to design a self-contained "omni-orientable" sorption refrigerator as a 300 mK heat sink that can be started and operated in any orientation in order to facilitate retrofitting microcalorimeters to existing materials analysis systems.
Redefine Technologies, along with researchers at the University of Colorado, will use three redundancy methods to decrease the susceptibility of a spacecraft, on a mission survivability level, to electronic failures anywhere throughout the spacecraft. By using  Field Programmable Gate Array (FPGA) chips, we will analyze the spacecraft-wide benefits of:
 *triplicating the logic and RAM on-board each subsystem using a Xilinx proprietary Triple Modular Redundancy (TMR) tool;
 *triplicating the persistent memory storage (i.e. ROM, science data, and flight code) on-board each subsystem using various methods specific for the space environment; and,
 *triplicating the backup architecture itself, while reducing weight and volume requirements, so subsystem code can run on alternate processors if any component is rendered inoperable due to an electronic failure (radiation, manufacturing, human-error, etc).

These three methods of triplication should significantly increase the reliability of non-radiation hardened designs, which should allow commercial off-the-shelf (COTS) processing components to be used as flight critical hardware. The analysis that is performed will predict the total benefit of this approach to any future spacecraft.
Proposed work envisions development of high-rejection filters and smart reconfigurable antennas using MEMS switches. Adaptive feature of the proposed antenna provides higher S/N ratio and extends range for surface-to-surface communications. Tunable high-rejection filters lend themselves easily to software defined radios.
Advanced liquid rocket propulsion systems must achieve longer burn times without performance degradation to allow the lowest cost per kilogram access to space. Ablative thrust chambers have an extensive heritage and are the low cost approach to fabricating rocket thrust chambers. However, composite ablative chambers suffer from erosion that typically limits
performance of the engine in terms of burn time and efficiency/performance of the combustion. In the last decade, there has
been significant interest in utilizing fiber-reinforced ceramic composites such as carbon fiber-reinforced silicon carbide (C/SiC) composites. Such composites have demonstrated a low erosion rate in bi-propellant liquid rocket thrust chambers at temperatures approaching 4000F. However insertion of these materials have been limited by complexities associated with required system redesign to accommodate a radiatively-cooled chamber, attachment methods, and addressing chamber
permeability issues. By incorporating a ceramic composite liner within an ablative thrust chamber in critical areas that are subjected to the highest temperatures, a low erosion, high performance chamber is obtained that eliminates costs and complexities that have limited the insertion of ceramic composite thrust chambers. The Phase I effort will produce a ceramic composite lined ablative thrust chamber, identify the degree of film cooling required and conduct a static hot fire test evaluation
of the material to demonstrate the perfromance benefit of a CMC liner within an ablative thrust chamber.
Impact Technologies, in collaboration with Georgia Institute of Technology, proposes to develop and demonstrate innovative technologies to integrate prognostics into Automated Contingency Management (ACM) for advanced aircraft controls. Without consideration of prognostic information, the traditional reactive fault tolerant control approaches may fail to provide optimal fault mitigation/accommodation strategies over a longer period of time. The project team will create a platform level simulation environment that demonstrates the fault propagation from the component level, using electromechanical flight actuators (EMAs) as a testbench problem, to the high level flight envelope and mission objectives. The proposed ACM system accepts input from discrete diagnostics, grayscale diagnostics and prognostic modules and will be split into a real-time reactive component and a "planning" component that considers temporal parameters and the potential impact of being proactive with mitigating action. Specifically, innovative prognostics enhanced stochastic programming and receding horizon control techniques are proposed for high and low level ACM controllers respectively. A subset of core algorithms will be implemented on embedded systems and used in hardware-in-the-loop demonstrations to justify a Technology Readiness Level of 4.
The objective of the proposed SBIR Phase I program is to develop novel
laser-based instruments that provide rapid, in situ, simultaneous
measurements of gas temperature, velocity and mole fractions of several
important species in rocket plume exhaust flows at NASA Stennis Space
Center.  Based on laser absorption spectroscopy techniques, the
instrument will employ room temperature near-IR and mid-IR lasers to
determine the concentrations of several combustion products, pollutants
and unburned hydrocarbons with high sensitivity.  The Phase I instrument
will be demonstrated in combustion flows at University of
Wisconsin-Madison Engine Laboratory, at LGR and at a NASA test facility.
The fast response of the instrument will enable engineers and scientists
to record precise measurements gasdynamic parameters in rocket engine
flows to identify temperature and species nonuniformities, combustion
instabilities and to refine and improve computational models.
Spaceports of the future will utilize new granular materials in unique applications including insulation for cryogenic tanks and Lunar regolith processing for usable resources. New granular insulation materials such as microspheres provide the opportunity to construct and operate safe and energy-efficient cryogenic storage tanks in the future. These materials have been demonstrated in small-scale tanks; however, no basis for reliable extrapolation to larger scales currently exists. Technology Applications, Inc. and the Colorado School of Mines propose to develop Advanced Granular Systems Modeling (AGSM) software to provide for reliable predictions of detailed mechanical behavior in these applications. AGSM is an innovative approach in modeling the behavior of granular materials through modified distinct element modeling (DEM) combined with a unique experimental validation technique leading to predictions in larger (macroscale) systems currently unattainable. The Phase 1 work plan will focus on the case of microsphere-based cryogenic insulation and is expected to result in a clear correlation in predicted stress concentration trends with respect to system scale and experimental results. In Phase 2, AGSM will be developed to provide predictions of granular material behavior for other materials, containment geometries, and scales to meet the needs of NASA as well as other industrial applications.
In this work Luna Innovations in partnership with Pennsylvania State University proposes to develop a new thermo-ultrasonic technology for the real-time in-situ monitoring of critical metallic, composite and bonded structural health parameters during space exploration missions. The potential applications of the proposed technique include characterization of component response to loading, monitoring load distribution, and identifying stresses exceeding design in a variety of structural materials and geometries. Another important usage area is assessment of the effects of structural defects on the system's performance, early detection of damage, and prediction of the remaining service life of critical components. The technology will utilize sparse networks of built-in or surface-mounted miniature lightweight ultrasonic sensors with low power consumption levels suitable for space deployment. A combination of specially designed sensor excitation mechanism and accurate velocimetry yields very high sensitivity to critical structural performance parameters. In Phase I we will demonstrate feasibility of the proposed approach on laboratory specimens subjected to load, and verify the results against mathematical models and FEM simulation. In Phase II we will develop a full-featured prototype unit and demonstrate all the benefits of the new technology on a representative flight component.
Long duration missions to the Moon and Mars will place new demands upon components and systems leading to increasingly stringent requirements for safety, quality, maintainability and repair.  In-Situ Fabrication and Repair (ISFR) of components is a key exploration initiative technology element managed by NASA's Marshall Space Flight Center.  In this Phase 1 STTR project, Luna Innovations Incorporated (Luna) and the University of Alabama in Huntsville (UAH) propose to extend technology development of a high-resolution acoustic spectrometer to materials characterization for components manufactured in space.  Luna and UAH will demonstrate the utility of ultrasonic phase-sensitive measurements with a laboratory Nondestructive Checkout Center (NCC) using Luna's PHLITETM technology to characterize the engineering performance of space manufactured components and to complement traditional NDE methods.  The high resolution measurements have been shown in previous NCC development work to be direct indicators of stress, strain, structural stiffness and other material properties critical to aerospace applications.  The current project seeks to extend the application of the technique to materials systems and manufacturing processes currently identified in the ISFR program element.
Rocket plume impingement may cause significant damage and contaminate
co-landed spacecraft and surrounding habitat structures during Lunar
landing operations. Under this proposed SBIR program, CFDRC and the
University of Florida will develop an innovative high-fidelity
simulation system for predicting surface erosion and debris transport
caused by rocket plume impingement on lunar surface. This simulation
system will combine 1) a unified continuum-rarefied flow solver capable
of simulating plume impingement flow in lunar vacuum, 2) granular flow
solid-fluid interaction technology for developing lunar soil grain
erosion and debris particle release mechanism models, and 3) particle
tracking tools to simulate debris kinetics, dispersion and contamination
after liberation. In Phase I, the plume stagnation layer flow conditions
at the soil surface will be modeled and computed. The solid-fluid
interaction physics in the soil layer in response to this surface flow
environment will be simulated and a generalized soil erosion model will
be derived. The erosion model will then serve to prescribe debris mass
and initial conditions for the debris-tracking module embedded in the
flow solver. In Phase II, the individual modules will be combined into a
single simulation system. The simulation system will be essential for
predicting the severity and range of dust and debris transport and for
designing lunar settlement layout, dust and debris impact mitigation
measures. He will spend at least 35 &amp;#37; of his time on this project and
his commitment to other projects is less than 50 &amp;#37;.
In order to meet the challenges of long-duration space exploration
(e.g., missions to the Moon, Mars and beyond), onboard real-time health
management of spacecraft that responds rapidly to system and subsystem
events is essential.  In response to this need, Qualtech Systems, Inc.
(QSI), in cooperation with Vanderbilt University, proposes to develop a
distributed multi-agent fault diagnosis and reconfiguration control
(FDR) approach for addressing the health management problem.  The
proposed solution uses &amp;quot;intelligent&amp;quot; schemes to coordinate
local health assessments of multiple interconnected subsystems
(&amp;quot;local diagnosers&amp;quot;) to a convergent and correct global system
health assessment.  In addition, the solution recommends relevant system
recovery functions based on fault isolation information and fault
severity estimates.  Design of local diagnosers for subsystem health
assessment utilizes a combination of both model-based and data-driven
diagnostic methods in an integrated development environment for accurate
root cause isolation.
Future lunar and planetary explorations will require the storage of cryogenic propellants, particularly liquid oxygen (LOX) and liquid hydrogen (LH2), in low earth orbit (LEO) for periods of time ranging from days to months, and possibly longer.  LEO is a relatively warm thermal environment and without careful thermal management, significant quantities of stored liquid cryogens can be lost due to boil-off.  This requires that larger volumes of cryogenic fuels must be launched into orbit so that sufficient quantities are available to satisfy the mission propulsion requirements.  It has been shown that active cooling using space cryocoolers has the potential to result in Zero Boil-Off (ZBO) of stored cryogens.  The launch-mass savings using active cooling exceeds that of passive cooling of LOX for mission durations in LEO of less than 1 week.  The savings advantage of active cooling for LH2 begins after about 2 months in LEO.  The proposer is developing a Modified Collins Cryocooler that offers the potential for higher efficiency cooling with better system integration for ZBO storage than can be provided by Stirling or pulse-tube type cryocoolers.
Luna Innovations Incorporated proposes in this STTR Phase II project to continue development and validation of Luna's amplitude-dependent, nonlinear ultrasonic inspection technique applied to friction stir welded (FSW) components.  The technique was successfully demonstrated in the Phase I project on samples made from aluminum-lithium alloy 2195.  The proposed Phase II project will focus on refining the ultrasonic hardware and software needed to implement the technique on materials and weld geometries with near-term application in support of the Constellation launch vehicle development program.  A multi-channel sensor implementation is planned.  Luna's results will be compared to conventional NDE techniques currently used; this testing will be conducted primarily by collaborators at the University of Alabama ? Huntsville (UAH).  The project will also include a review of state-of-the-art NDE techniques applied to FSW joints and early planning for comprehensive probability of detection experiments needed to fully qualify the new technique.
The objective of the proposed SBIR Phase II program is to develop, deploy and deliver novel laser-based instruments that provide rapid, in situ, simultaneous measurements of gas temperature, velocity and mole fractions of several important species in rocket plume exhaust flows at NASA Stennis Space Center.  Based on proven laser absorption spectroscopy techniques and successful demonstrations in Phase I, the instrument will employ novel room temperature near-IR and mid-IR lasers to determine the concentrations of several combustion products, pollutants and flowfield parameters (gas temperature and velocity) with high sensitivity.  The Phase I instrument will be tested and refined in combustion flows at University of Wisconsin-Madison Engine Laboratory and at LGR and demonstrated in realistic flows at NASA Stennis Space Center.  The fast response of the instrument will enable engineers and scientists to record precise measurements of several important gasdynamic parameters in rocket engine (including Space Shuttle Main Engine) flows to identify temperature and species nonuniformities, combustion instabilities and to refine and improve computational models.
Manned spacecraft are vulnerable to air leaks caused by micrometeoroid and space debris impact.  The ability to detect and quickly locate and mitigate a pressure vessel breach is critical to the safety of any long duration spacecraft, such as the International Space Station or a proposed lunar base or mission to Mars.  Current NASA protocol for finding a spacecraft leak uses a handheld ultrasonic directional microphone, similar to those widely deployed industrially, to detect the 40 kHz airborne ultrasonic hiss generated by the downstream leak turbulence.  However, known limitations exist regarding the use of airborne ultrasonic emissions for locating leaks in the spacecraft environment because the downstream side of the leak occurs into the vacuum of space, creating reduced leak noise inside the pressure vessel.  Blockages of the transmission of airborne ultrasonic energy by structural components, avionics, and equipment racks also limit the detection range of such systems.  An alternative approach that we propose is to monitor the spacecraft structure itself---the pressure vessel skin---for leak-generated surface-borne ultrasound by means of a flexible and modular electronics package with fully integrated surface sensor arrays, data acquisition electronics, and radio frequency communication capabilities.
Our objective is to develop and demonstrate a novel microfluidic device for non-destructive identification, sorting and counting of radiation damaged cells. A major thrust, using microarray experiments, is the discovery of unique cell surface markers for identification of radiation-damaged cells.
We propose to design, build and evaluate a prototype of a compact, robust, optically-based sensor for making temperature and multi-species concentration measurements in propulsion system ground and flight test environments. This system will utilize a widely tunable near infrared light source to make absorption measurements of combustion reactant and products in the combustion zone (with accuracy from 100-1000 ppm).  Although possible to tune over a very wide wavelength range, during phase-II we propose to develop the light source which will be able to continuously tune from 1.4 to 1.8 microns while maintaining a narrow bandwidth of 0.01 cm-1 using a novel combination of acousto- and electro-optically controlled devices.  The rapid tunability of this light source will obviate the need for dense multiplexing of multiple wavelengths as signals can be multiplexed in time while maintaining fast temporal response. Furthermore, the wide spectral bandwidth allows for the selection of the optimum absorption transitions, without regard for the commercial availability of narrow bandwidth diode lasers. The proposed instrumentation will be environmentally rugged, with the ability to withstand extreme ranges of temperature, humidity, vibration and shock conditions.  Further, the system will possess auto-calibration capabilities, fast response time (few microseconds) and can be battery operated.
Abstract

There is a valid scientific data paradigm where no loss of data can be tolerated.  However, transmission of raw data requires unacceptable bandwidth and storage resources such that the net data received is uncomfortably low.  Lossless data compression can be used to preserve all data with no information loss and also help meet bandwidth and storage constraints.  The current Universal Source Encoder of Space (USES) has been meeting many lossless compression needs for a decade.  However, USES is not able to successfully address higher speed instruments, beyond 20 MSamples/sec, or function at quantization levels higher than 15 bits.  The proposed work provides a new solution and presents a lossless data solution that should be valid for at least a decade or more. 

A radiation tolerant high performance (100M Samples/second) 32-bit lossless custom processor will be delivered in the proposed work which meets the CCSDS 121-0-B 1 recommendation.  The processor will be implemented in a radiation tolerant 0.25 micron CMOS process which realizes a proven algorithm developed at GSFC and implemented in a 15-bit version 10 years ago.  The new compressor is 5 times faster and has twice the input quantization range, suitable for modern spacecraft requirements.   The net-list (design) of the processor can be used to synthesize a future 200 Msamples/sec plus data rates when a sub-100 nm radiation tolerant fabrication process is available.
We have designed a compact two-color, polarization-sensitive instrument to measure cloud characteristics from a high altitude UAV and can
also be widely deployed as inexpensive ground-based ceilometers and aerosol finders. The instrument is modular, can operate
with one or two wavelengths, and can measure depolarization or not depending on the need. The instrument is in two pressurized
boxes, an optics box and an electronics box, each about half a cubic foot in size. If desired, the two boxes can be attached for a
single box solution. Fiber optical technology is used to minimize critical optical alignments and permit field replacement of the
laser and detectors. Micro-optic fiber components are used to separate the colors before detection. We propose to build, test, and calibrate the instrument in the Phase 2 effort.
In order to meet the challenges of high probability of mission success for space exploration, ground support system for various launch operations that responds rapidly to system events and anomalies is essential.  In addition, the vast amount monitored parameters (around 50,000) for ground support system requires systematically supportablity analysis and trade-off studies for sensor optimization.  Qualtech Systems, Inc. (QSI), in cooperation with Vanderbilt University, proposes to develop an integrated ground support system for addressing the ground support health management problem.  The proposed solution provides supportability analysis for LOX system and real-time monitoring for select target system (e.g. hydraulic system).  The supportability analysis uses QSI's TEAMS modeling of a candidate Liquid Oxygen (LOX) system which covers ground fueling facilities, mobile launcher and launch pad.  An efficient sensor optimization schemes is developed to evaluate current available sensors and proposed upgrade sensor groups.  Real-time monitoring collect sensor data from candidate system to the integrated test layer (wherein advanced tests are designed) and passed to the real-time diagnostic reasoner.
Rocket plume impingement can cause significant damage and contaminate co-landing spacecraft and surrounding habitat structures during lunar landing operations. CFDRC and the University of Florida will develop an innovative simulation system for predicting surface erosion and debris transport caused by lunar surface rocket plume impingement. This simulation system combines 1) a unified continuum-rarefied flow solver capable of simulating plume impingement flow in lunar vacuum, 2) granular solid-fluid interaction simulation models for developing databases for lunar soil erosion and debris particle release mechanism, and 3) particle tracking tools to simulate debris kinetics and dispersion after liberation. During Phase I, the Unified Flow Solver (UFS) capabilities in simulating hybrid rarefied-continuum plume flow, and the debris dispersion tracking capabilities were demonstrated. The fluid-solid simulation tools realistically simulated jet induced soil grain response characteristics, clearing the path towards establishing working models of erosion and particle release mechanisms. In Phase II, the individual modules will be refined, validated and integrated into a coherent simulation system. The solid-fluid interaction physics will be refined for the peculiar lunar soil layer characteristics and consequently soil erosion models will be derived. The erosion models will serve to prescribe debris initial conditions for a debris-tracking module developed and integrated with the flow solver. The simulation capability will be essential for predicting the severity and range of dust and debris transport and for designing lunar settlement layout, dust and debris impact mitigation measures.
In this proposal, we describe a program to develop a high-performance, cost-effective and robust microwave receiver prototype for multi-purpose Non-Destructive Evaluation (NDE). Currently, NDE of space transportation vehicles is primarily carried out on the ground, between missions.  For future space missions, as duration and frequency increases, more inspection will need to be performed in space in order to monitor the aging process of the structure and to insure its integrity. For this purpose, NDE equipment that is compact, lightweight, easily operated by human with limited mobility or robot, and that exhibits low power consumption is required. Furthermore, in order to minimize the quantity of embarked equipment, the inspection equipment must be able to perform as many different inspection tasks as possible. Our innovative receiver is based on the integration of a microwave interferometer coupled with a pulsed laser to generate the ultrasound. . Based on the results obtained during Phase 1, we strongly think that we will be able to overcome the limitation generally associated with classical optical receiver: 1) Inability to work in factory environment where thermal, mechanical and optical propagation (fumes, water drops,..) perturbations are present; 2) Reduction in sensitivity caused by the speckle nature of the light reflected from rough surfaces; 3) High system cost due the price of the probe lasers, optics and engineering to develop an optical system working in a harsh environment (fumes, water drops, strong mechanical vibration?) and 4) high maintenance cost (Lasers and optics need to be checked and re-aligned frequently). Our proposed approach will lead to a cost-effective prototype with good sensitivity and performances in industrial environment.
The goal of this STTR program is to employ nanostructured materials in an advanced device design to enhance the tolerance of solar cells to extreme environments while maintaining high solar electric power conversion efficiency.  By using InN-based quantum dots embedded within a higher band gap GaN barrier material, a larger fraction of the solar spectrum can be harnessed while minimizing the effects of high temperatures and high-energy radiation with this promising photovoltaic device.  The wide range of energies accessible to InN-based materials provides unique flexibility in designing quantum dot solar cell structures.  Phase I work demonstrated the feasibility of synthesizing device quality InN-based quantum dots.  InN quantum dot assemblies were grown on GaN templates via metalorganic chemical vapor deposition and exhibited well defined x-ray diffraction peaks with dot densities up to 1E10 cm-2.  More importantly, strong room temperature photoluminescence has been observed, with peak emission energies ranging from the infrared to the ultraviolet.  These promising optical properties suggest it will be possible to build structures incorporating InN quantum dots within a GaN p-n junction to test the basic concepts of quantum dot solar cells during the Phase II effort.  The principal Phase II objective is to develop an InN-based quantum dot solar cell capable of high performance in near-sun and extreme radiation environments.  Ultimately our approach provides a pathway for realizing solar cells with over 2,000 W/kg of specific power and power conversion efficiency approaching 60&#37;.
Aerotonomy, Incorporated, the Georgia Tech Research Institute, and the Boeing Company propose here to continue work towards the development of commercially viable enabling technologies for a Cruise Efficient, ESTOL-capable Transport Aircraft (CEETA).  Results of the Phase I effort provide a broad, systems-based assessment of several innovative Combined Circulation Control (C3) techniques that represent a significant potential solution in the space of high lift technologies.  Highlights of the proposed Phase II program will be:
1)	Significant enhancement of the overall systems-based C3 impacts analysis by refining the weight, compressed air requirements, propulsion system, flight performance, environmental, cost, and reliability impacts analyses as well as conducting a meaningful examination of Figure of Merit weighting schemes.
2)	Low speed wind tunnel tests of a 3D half-span, subscale CEETA with integrated C3 systems to generate detailed 3D aerodynamic data that include interaction effects among the various circulation control devices.
3)	Execution of an experimental flight program using a subscale, mass-scaled CEETA testbed that enables direct performance comparisons between an aircraft equipped with C3-based high lift devices and an aircraft equipped with conventional high lift devices at the same wing loading, as well as evaluations of real-world issues associated with integrating C3 devices into a flight-ready vehicle.
A rocket engine turbopump design using a partial emission pump combined with a zero net positive suction pressure inducer design is proposed to achieve a robust, deep throttling capability in 5k to 15k lbf thrust range rocket engines. A partial emission pump can provide better low-flow/thrust stability at a better efficiency than full emission pumps in this throttle range.  A zero net positive suction pressure inducer will be able to perform with boiling flow at the inlet and at low flow conditions.  This will enable deep throttling as well as restarts with minimal turbopump/engine thermal conditioning.
The purity of hydrogen fuel is important in engine testing at SSC. The hydrogen may become contaminated with nitrogen, argon, or oxygen. The hydrogen from the fuel tanks or feed lines is analyzed beforehand. Therefore, there is a need for a non-intrusive, on-line, near real-time monitor for H2. The analytical technique should measure various impurities (molecular and atomic) simultaneously and be easy to implement in the field. The objective of this proposed research is to develop an analytical technique based on Laser Induced Breakdown Spectroscopy (LIBS) to measure simultaneously the concentrations of nitrogen (N2), argon (Ar) and oxygen (O2) contaminants in hydrogen (H2) gas storage tanks and supply lines. Advanced sensors for monitoring multiple species in H2 feed-lines and storage tanks will be useful before engine testing and will increase understanding of engine performance. Phase I will provide necessary information to build an improved prototype in Phase II, with better sensitivity and ease of implementation at NASA/SSC. In Phase II, a prototype LIBS system will be developed to measure impurities in H2 fuel at different places in the H2 feed line. This system will be delivered to NASA/SSC at the end of Phase II.
The recent advances in data collection and storage capabilities have led to information overload in many applications, including on-line monitoring of spacecraft operations with time series data. Such datasets present new challenges in data analysis, especially for implementation in memory-constrained DECUs.  Also, the traditional statistical methods break down partly because of the increase in the number of observations (measurements), but mostly due to an increase in the number of variables associated with each observation ("dimension of the data"). One of the problems with high-dimensional datasets is that not all the measured variables are "important" for understanding the underlying phenomena of interest. In addition to the computational cost, irrelevant features may also cause a reduction in the accuracy of some algorithms.  The first key issue we propose to address is that of data reduction techniques for onboard implementation of data-driven classification techniques in memory-constrained onboard processing units. Some of the classification techniques we intend to use with the above data-reduction techniques include, support vector machine (SVM), probabilistic neural network (PNN), k-nearest neighbor (KNN), principal component Bayesian analysis (PCA). To improve the diagnostic accuracy and efficiency of the above classifiers, we will apply classifier fusion techniques such as AdaBoost, Error correcting output codes, Voting to find which architecture will enhance the accuracy and under what conditions. Finally we will investigate Dynamic Multiple Fault Diagnosis that can work with imperfect fault/anomaly detection tests. As part of this task, we will develop novel factorial hidden Markov model-based inferencing techniques such as Lagrangian relaxation and Viterbi decoding algorithms to solve this difficult combinatorial optimization problem, for on-board vehicle health monitoring and fault diagnosis.
The minimization of vibration-induced damage has become a critical issue for rocket launch ground support electronics (GSE). GSE located near a major rocket launch can be exposed to damaging environments including heat, rocket plume impingement, vibration, and acoustics. This extreme vibratory environment results in the need for extensive check out and frequent repairs of GSE systems after each launch. Another consequence is the need for extensive design and qualification testing to ensure equipment survivability.

Passive GSE vibration isolation systems often have natural resonances within the broad excitation spectrum, resulting in poor equipment protection. Additionally, passive isolation systems can only be tuned for one excitation type (amplitude / frequency) and one GSE rack arrangement. If the expected vibration spectrum changes, the passive isolation system is no longer optimized and requires redesign. Furthermore, if the inertial properties of the GSE rack itself changes (rack or drawer is replaced or rearranged), the passive isolation system will no longer function properly which may lead to catastrophic failure.

To overcome these deficiencies, Techno-Sciences Inc, in collaboration with the University of Maryland, proposes to develop an innovative Adaptive Magnetorheological Isolator (AMI) system that will automatically adjust its energy absorbing capabilities to real-time environmental measurements as well as GSE rack properties. Such a system will utilize internal motion sensors coupled with an on-board microcontroller to provide automatic adaptation to the excitation as well as the inertial properties of the supported rack. In doing so, the system will eliminate damaging natural resonances and provide optimal vibration isolation at all times. Because of its adaptability and optimal vibration isolation capabilities, the AMI system will significantly reduce design and life-cycle costs and enhance equipment reliability.
This Phase I STTR project will develop a highly reflecting, broadband, radiation resistant, low-stress and lightweight, membrane integrated into an electrostatically actuated microelectromechanical systems (MEMS) device for wavefront control applications in space telescopes. The underlying technology builds on nanomaterial coatings and electro-optical modeling competency of the company. InnoSense LLC (ISL) will collaborate with Dr. Harold Kahn, Research Associate Professor, Department of Materials Science and Engineering at Case Western Reserve University, to integrate the low-cost, flexible nanocomposite membrane mirror into a MEMS device. The Phase I project would demonstrate: (a) a membrane mirror capable of high broadband reflectivity; (b) deflections &gt; 20-30 micron; and (c) large temporal bandwidth at frequency &gt; 1 KHz. The focus of Phase II will be optimization of the reflecting membrane, refinements to the design of the deformable membrane mirror (DMM) device, accompanied by extensive evaluation of prototype DMMs for their ability to correct for large wavefront aberrations at high frequencies to mitigate the effects of atmospheric turbulence, and enable high fidelity imaging capability. To ensure success of this project, ISL has assembled a technical team with a cumulative 70 person-years of experience in nanomaterials coatings, MEMS, mechanical and electro-optical modeling.
The challenges of designing, developing, and fielding man-rated propulsion systems continue to increase as NASA's Vision for Space Exploration Program moves beyond the Space Shuttle and RSRM.  The number and type of different propulsion elements required are significant, and predicting internal solid motor behavior and characteristics and assessing external environments due to plume impingement on vehicle structures is a top priority.  Solid motors do not require pre-start thermal conditioning but can be throttled by grain shape and pintle design, and thus the analysis tools must be flexible and prepared to meet the appropriate simulation readiness level.  Our proposed innovation will enhance existing engineering software by combining new flow solution methodologies with appropriate boundary conditions to create a novel toolset for complex multi-phase solid rocket analyses.  The innovation will be based on the LOCI/CHEM multi-physics analysis package and will utilize new LOCI features, new multi-phase flow models, and theoretical and phenomenological boundary conditions to create a unique software tool for solid propellant burning, particle breakup, surface erosion, and environment characterization for next generation solid motors.  Our research products will provide NASA with the important capability to simultaneously analyze solid propellant combustion, heat transfer, and nozzle erosion within a single numerical framework.
Robots will be precursors to human exploration of the lunar surface.  They will be expected to prepare the lunar surface for human habitation as well as conduct scientific investigations.  As humans arrive, first for short-term stays, the robots should be able to shift to providing direct assistance to human exploration activities. Such tasks require a new generation of robotic vehicles ? a generation that has flexible, dexterous manipulation that can be scaled to include teams of machines.  Since it will be impossible to tightly script complex operations ahead of time, it will be essential for planetary robots to be effective in unmodeled environments and unanticipated situations.  Our proposal addresses four fundamental areas in mobile manipulation: 1) Motion Planning for Cooperative Mechanisms; 2) Task Sequencing &amp; Monitoring; 3) Coordinated Control of Redundant Mechanisms; and 4) Human Robot Interface. Together, these innovations will create robots that can accomplish a wide variety of tasks to support NASA's exploration missions.  We will demonstrate our approach using scenarios that involve several mobile robots with dexterous manipulators moving and assembling structures on the lunar surface and being supervised by remote operators.
We propose a novel MEMS-based digital phase shifter targeted for Ka-band operation, but scalable down to X-band and up to W-band.  This novel phase shifter will incorporate MEMtronics' state-of-the-art microencapsulated, capacitive MEMS switches to control phase.  The envisioned phase shifter behaves much like a switched-line phase shifter with broadband matched impedance, but without sacrificing size normally needed to accommodate multiple signal paths.  Many MEMS-based phase shifters have been created with good results utilizing a loaded line approach.  While this technique works well for smaller bits, larger bits suffer from narrow bandwidths and a poor impedance match in one or both states.  Additionally, cascading multiple bits results in a relatively long multi-bit phase shifter.  As insertion loss is dominated by conductor loss, these long multi-bit phase shifters become rather lossy reducing advantages that MEMS-based phase shifters may offer.  This proposed project seeks to overcome these limitations by maximize phase shift per unit length, while increasing bandwidth, to arrive at a low-loss Ka-band phase shifter with significant performance and size improvements over currently available technologies.
We propose a key innovation to improve wavelength-sensitive lidar measurements (such as wind velocity) using photon-counting receivers. A novel binning technique to track the wavelength shifts of the outgoing laser pulses on a per-shot basis before accumulation in the receiver electronics is described. This allows creation of a narrow histogram in the backscattered signal accumulation process while using less expensive, less stable lasers than are traditionally required. This technique relaxes the stringent stability requirements on the laser, and therefore its size, weight, complexity, and cost. We propose to demonstrate the technique in existing lidars more compact and suitable for airborne platforms in terms of size, weight and power requirements of the system. We utilize recent solid-state laser and high-speed signal processing technologies in the wavelength tracking system. The direct application of the wavelength corrector is in a direct detection Doppler wind lidar. This innovation will significantly reduce the cost of wind lidar systems permitting their installation at airports to look for dangerous wind shears as well as for weather forecasting. Also, this innovation will significantly reduce the cost of a space-based Doppler wind lidar system because of the relaxed laser stability requirements.
Out-of-autoclave thermoplastic tape/tow placement (TP-ATP) is nearing commercialization but suffers a moderate gap in mechanical properties compared with laminates fabricated via thermoset autoclave processing.  Out-of-autoclave thermoplastic processing significantly lowers composite aerospace part costs, but the property gap must be closed.  This STTR program, endorsed herein by Boeing and Cytec Engineered Materials, will remedy the mechanical property shortfall and enable large composite aerospace structure important to NASA to be manufactured without an autoclave.  Accudyne is teaming with University of Delaware ? Center for Composite Materials to apply their state-of-the-art TP-ATP process/property models to elucidate the physical mechanisms affecting microstructural quality that cause the property gap.  Models will be applied to the NASA LaRC TP-ATP deposition head to optimize the head configuration and machine operating parameters, and the control systems for full mechanical properties.  Laminates will be manufactured to demonstrate the property improvements.  The process, head, and equipment changes will be upgraded on the NASA-LaRC thermoplastic tape head.  In Phase 2, process/head modeling will be extended through laminate fabrication and testing, and a component of interest to NASA will be fabricated demonstrating the improved "autoclave level" mechanical performance.
For photovoltaic cells used to power space missions, such as those based on silicon, CuInGaSe2, and III-V materials, optical-to-electrical conversion efficiency is reduced by at least 25&#37; because the energy of solar photons in excess of the band gap of the semiconductor absorber is lost. The excess photon energy is converted to heat. In addition, the quantum efficiencies of solar cells tend to degrade for high energy photons due to surface recombination effects. Optical down-conversion has been suggested as a method to recoup this lost energy, providing an increase in the theoretical single junction photovoltaic conversion efficiency from 30.9&#37; to 39.6&#37;. If substantial gains in PV efficiency could be achieved with a thin film coating of an efficient two photon downconverting layer, it would have a tremendous benefit not only to NASA payload burden, but also the the economics of terrestrial solar cells.  However, the absence of materials with suitable time constants for the relevant electronic processes has hindered the realization of this method. Our proposed solution, being developed by the University of Arizona, is to use the unique optical properties of nanocrystals to produce efficient downconverting emitter materials. Phase I will entail synthesis of the new materials at EIC Laboratories and their optical evaluation at Arizona, with a goal of demonstrating the first practical examples of such a thin film material.
ZONA Technology, Inc (ZONA) and Arizona State University (ASU) propose a R&amp;D effort to develop a ground flutter testing system without wind tunnel, called the Dry Wind Tunnel (DWT) system. The DWT system consists of a ground vibration test (GVT) hardware system and a real-time unsteady aerodynamic force generation software developed from an aerodynamic reduced order model (ROM). The ground flutter test using the DWT system operates on the real structural model, thereby no scale-down structural model is involved.  Furthermore, the impact of the structural nonlinearities on the aeroelastic stability can be automatically included.  Moreover, the aeroservoelastic characteristics of the aircraft can be easily measured by simply including the flight control system in the loop.  In addition, the unsteady aerodynamics generated computationally is interference-free from the wind tunnel walls.  Finally, the DWT can be conveniently and inexpensively carried out as a post GVT test with the same hardware. In Phase I, we will validate this DWT concept on a rectangular flat plate with a reference flutter solution. Through this validation process, the most significant hardware issues will be resolved to pave the way for a successful Phase II validation on a complex structure, such as a real aircraft.
Robots that can move about in terrestrial environments and manipulate large and small objects serve a critical role in NASA's Moon/Mars initiative.  Such systems will need to serve as precursors to human missions, collaborate with humans on-site, and carry on when humans have departed.  This proposal concerns a control suite and teleoperator interface for whole-body mobile manipulators (WBMMs).  WBMMs are a class of redundant, mobile, multi-limbed platforms able to use their entire bodies for manipulation tasks.  Such platforms are extremely versatile and can address NASA's need for platforms that perform useful work on the surface of the Moon or Mars.  To exploit WBMM, a control framework capable of exploiting redundancy and new man-machine interfaces are required.  digitROBOTICS and the Laboratory for Perceptual Robotics at UMass propose to build a WBMM control suite and teleoperator interface to address these challenges. We propose to use control basis framework developed at UMass  over the past two decades and used to advance the state-of-the-art in many robotic task domains including grasping and manipulation.  The WBMM control suite will simplify controller design and allows control knowledge to be easily ported between robots and operating contexts.  The WBMM teleoperator interface will allow for varying levels of autonomy, and can preserve safety constraints using control mechanisms from the WBMM control suite.   
The anticipated result of the Phase 1 effort is preliminary software for controlling WBMMs as described above at TRL 4, and a proof of concept teleoperator interface at TRL 3.  The anticipated result of a Phase 2 effort would be a commercial-grade version of both the control suite and teleoperator interface, and to have the control suite and teleoperator interface running on one of NASA's WBMMs (ATHLETE or Robonaut, for example).  The results of the Phase 2 effort are estimated to be at TRL 5-6.
Metal matrix composites (MMC's) are of great interest in aerospace applications where their high specific strength provides a weight saving alternative to standard materials. To date however their use has been limited by the difficulty in fabricating complex shapes. Most current methods for manufacturing MMC's are limited to relatively simple shapes that often still require further machining. It is the machining of MMC's that is the biggest drawback to their application. Grinding or single point diamond turning are generally the methods of choice but in each case tool wear is excessive and surface damage is apparent. A very attractive alternative for rapid machining of MMC's is Laser Assisted Machining (LAM). LAM has been successfully applied to ceramics and some recent work has indicated that LAM can successfully machine MMC's with high material removal rates and no surface damage. In this proposal, Nanohmics Inc. and Dr. Y. C. Shin of Purdue University propose to apply the recently developed technique of laser assisted machining coupled with a specially designed dynamic tooling system to develop a means of machining MMC's into complex shapes.
The proposed innovation is to use the refrigerant capabilities of nitrous oxide (N2O) to provide the cooling required for reusable operation of an aerospike nozzle in conjunction with an N2O-HTPB? hybrid rocket motor.  The phase change cooling as liquid N2O is flashed into a vapor is crucial to limiting to acceptable levels the erosion of both the nozzle throat and spike, thereby enabling reusable operation and/or long burn times.  The N2O used for cooling the nozzle throat will be reintroduced into the combustion chamber, and the N2O used for cooling the spike will be used to provide base bleed, virtually eliminating any performance penalty associated with using a severely truncated, and therefore significantly lighter, spike. Because of its high vapor pressure, N2O can be self-pumping, thereby making it an ideal choice of oxidizer for simple, low-cost applications. As a simple, practical nozzle, the proposed innovation fits well with N2O-HTPB hybrid rocket designs, which tend toward simpler, less expensive design alternatives. 
Because of their high efficiency due to altitude compensation, aerospike nozzles could play an important role in bringing to fruition inexpensive access to low Earth orbit.  In addition, these altitude compensating nozzles could provide significantly increased performance for a wide array of tactical missiles.  Although a few rocket flights powered by liquid propellant rocket engines and two flights powered by solid propellant rocket motors have used aerospike nozzles in the last several years, the lack of a comprehensive flight test database has precluded the use of these nozzles in current as well as next-generation space vehicles. 
The simple, low-cost, reusable, oxidizer-cooled aerospike nozzle for operation on an N2O-HTPB hybrid rocket motor that is proposed herein is a device that will enable much-needed flight research of aerospike nozzles.
Long-term exposure to microgravity and radiation during space exploration can pose a critical threat to the health of a flight crew. Real-time monitoring of urine protein levels is an effective way to follow the onset and progress of many diseases and guide the prompt selection of proper therapy. The success of such diagnostic tasks, which is strongly desired for flight missions, critically depends upon the degree of automation and reliability of such trace level detection. To meet this need, we propose to develop a novel on-chip, nano-plasmonic sensor cartridge to concurrently quantify the presence of different urine proteins. The envisioned device is compact, lightweight, fully integrated and automated, and highly cost- and power-effective. The program objectives will be accomplished via several innovations: (a) a new nano-plasmonics chip technology-based SPR sensor that is compatible with miniaturization, (b) tailored array modifications, allowing for concurrent screening of multiple proteins, (c) microfluidic platform for automated biochemical processes, and (d) simulation-based design for rapid prototype development. In Phase I, we will develop and demonstrate the critical microfluidic components (i.e., filter, mixer and network architecture) guided by physics-based simulations, and experimentally demonstrate the two-type-assay on a single nanoplasmonics chip for protein detection. The simulation-based design will conform to specifications that are amenable to mass-production-friendly lithographic techniques. In Phase II, the nano-plasmonic sensor will be optimized to increase sensitivity, stability, and the response to regular urine samples. Finally, the sensor will be integrated with microfluidic components and control/transmission electronics to form a portable protein assay cartridge.
Real-time Onboard and Remote Vehicle Health Management Project
Integrated software toolbox for aeroelastic modeling and dynamic stability analysis of air vehicles Project
Nanostructured High Temperature Optical Filters for Protection of Spectroscopic Instrumentation Project
Intelligent Control For Autonomous Remote Spacecraft Project
FINITE ELEMENT MULTI-DISCIPLINARY ANALYSIS OF FLIGHT VEHICLES Project
Specific Impulse Analysis of Solid Materials for Ablative Laser Propulsion Project
Novel Very Fast Tunable Filter for Hyperspectral Imaging Project
Graphic Displays to Support Treatment of Medical Emergencies Project
Utilizing MIL-STD-1553B Digital Data Bus Devices Across an IEEE-1394A Serial Bus Project
Multifunctional Nanostructured/Microporous Materials Project
Coatings for Foil Seals/Foil Bearings for Gas Turbine Engines Project
Comprehensive Atomization/Spray Module for Advanced CFD Combustion Codes Project
Multifunctional Thermal Protection System for Future Space Transportation Vehicles, Phase II Project
AUTOMATED LEARNING FOR REAL-TIME EXPERT SYSTEM IN MONTORING AND CONTROL Project
Development of Space Based Emergency Medical Procedures Using Simulation Technology Project
Fan Flow Control for Improved Efficiency and Noise Reduction Project
Intelligent Medical Systems for Aerospace Emergency Medical Services Project
Multi-Application Survivable Tether (MAST) Experiment Project
Novel Identification Tools for Multiresolution Analysis of Aeroservoelastic Flight Test Data Project
Refractory Open-Cell Foam Fuel Matrix for High-Efficiency Nuclear Space Propulsion Systems Project
Ultra-large Solar Sail Technology Project
CFD-Based Multidisciplinary Analysis for Flight Vehicle Simulation and Control Project
Autonomous Intelligent Health Monitoring for Robust Fault-Tolerant Control of Multi-Modal System Project
Robust Aeroservoelastic Toolbox for Nonlinear Data-Based Modeling and Analysis Project
Autonomous Spacecraft Power Scheduling Project
Development of a Modular Solar Thermal Propulsion Engine Project
An Intelligent Fault Diagnosis and Accommodation Approach for Nonlinear Aircraft Project
An Autonomous Wireless Instrumentation Network for Antarctic Research Project
Finite Element Multidisciplinary Simulation of a Reusable Launch Vehicle Project
Light Weight Concepts for Mirrors Project
Tethered Artificial Gravity Spacecraft (TAGS) Project
Adaptive, Learning Control for Unmanned Vehicles Project
Embedded Software Technologies for Dynamic Goal Determination and Execution Project
Integration of Garnets and Magnets for Waveguide Isolators Project
Energy-Based Acoustic Measurement Techniques and Sensors Project
Cascaded Injection Locked Diode Laser Transmitter For Lidar Measurements Project
Non-Axisymmetric Infrared Plume Tomography for Rocket Plume Species and Temperature Distributions Project
Non-Intrusive Continuous Wave Acoustic Flowmeter STTR Proposal Project
Wavelength-Agile Optical Rocket Propulsion Sensor (WORPS) Project
Micro ElectroMechanical Systems Optical Beam Steerers Project
Stochastic Optimization of Aeroelastic Response (SOAR) Project
Intelligent Medical System for Space and Ground Project
Development of Space Based Emergency Medical Procedures Using Simulation Technology Project
Fan Flow Control for Improved Efficiency and Noise Reduction Project
USE OF MULTIPLE A I METHODOLOGIES TO PRODUCE A FOUNDATION FOR AN INTELLIGENT MEDICAL SYSTEM Project
In this NASA Phase I STTR effort, the feasibility of fabricating isolated ridge waveguides in 5&#37; magnesium-doped lithium niobate (5&#37; MgO:LN) will be established.  Ridge waveguides in MgO:LN will significantly improve the power handling and conversion efficiency, increase photonic component integration, and be well suited to space based applications.  The key innovation in this effort is to combine recently available large, high photorefractive damage threshold, z-cut 5&#37; MgO:LN with novel ridge fabrication techniques to achieve high optical power, low cost, high volume manufacturing of frequency conversion structures.  The proposed ridge waveguide structure should maintain the characteristics of the periodically poled bulk substrate, allowing for the efficient frequency conversion typical of waveguides and the high optical damage threshold and long lifetimes typical of the 5&#37; doped bulk substrate.  The low cost and large area of 5&#37; MgO:LN wafers and the improved performance of the proposed ridge waveguide structure will enhance existing measurement capabilities as well as reduce the resources required to achieve high performance specifications.  For these reasons, the development of ridge waveguides in 5&#37; MgO:LN directly addresses NASA's Innovative Sensors, Detectors and Instruments for Science Applications, STTR subtopic T4.01: Lidar, Radar and Coherent Fiber Bundle Arrays.
Middle-wave infrared (LWIR, 3.2-3.6 m) photodetectors with a high
specific photodetectivity (D*) are of great importance in NASAslidar and
remote sensing applications. However, existing MWIR photodetectors are
required to be operated at low temperature of below 77K to achieve high
photodetectivity (D*). The requirement for cryogenic cooling systems
adds cost, weight and reliability issues, thereby making it unsuitable
for space and planetary exploration applications. The proposed STTR
research aims to develop a new type of MWIR photodetector with a
significantly enhanced quantum efficiency of ~ 60&amp;#37;  and photodetectivity
of &amp;gt; 10^10 cm Hz^1/2/W. Successfully developing the proposed
innovation is expected to provide an enabling technology for compact
high performance MWIR detection and imaging systems suitable for NASAs
space exploration and earth remote sensing applications. In phase I, a
preliminary MWIR photodetector with the high specific photodetectivity
(D*) will be developed and delivered to NASA for proof-of-concept
demonstration. In Phase II, an ultra-compact highly-sensitive focal
plane array (FPA) prototype will be developed and hybridized with
readout circuits. A preliminary high sensitivity LWIR camera will be
also demonstrated and delivered to NASA in Phase II.
Over the next decade, a host of new technologies and capabilities will be needed by NASA to support Project Constellation. For risk reduction considerations, it is desirable that they be flown on other missions prior to use on vehicles such as Orion or Altair.  An innovative and cost-effective approach to doing so is to use picosats, which are miniaturized spacecraft with masses on the order of a few kilograms. Because of their size, weight and power requirements, they are ideal for low-cost, quick-turn-around technology demonstration missions. Picosats are now being developed at universities by teams of students for "hands on" experience with real space hardware. The University of Texas at Austin (UT) and Texas A&amp;M University (TAMU), for example, are working with NASA Johnson Space Center to implement a series of four picosat missions that would culminate in an on-orbit demonstration of autonomous rendezvous and docking (AR&amp;D). This is a mission-critical, system-level technology needed by Project Constellation, especially Orion. Accordingly, Emergent Space Technologies, Inc. (Emergent) proposes to team with UT to move the Platform for Autonomous Rendezvous and Docking with Innovative GN&amp;C Methods (PARADIGM) picosats out of the university research realm and into the commercial marketplace.  These spacecraft are being built by UT students to fly in concert with the picosats being built by their TAMU counterparts. The Flight 1 spacecraft are being readied for launch in early 2009 and are primed for transition to industry.  Emergent will work with UT and TAMU in Phase 1 to design the 3 missions that will follow Flight 1. In Phase 2, we will use our considerable engineering expertise and AR&amp;D spaceflight experience to help achieve a successful Flight 2.  In Phase 3, we will successfully implement Flights 3 and 4 and in the process develop a picosat product line that can be applied to a variety of commercial space applications.
The objective of this NASA STTR program is to develop conformal thin
film sensors and sensor arrays for the direct measurement and mapping of
distributed skin friction on the surfaces of flight-test vehicles and
wind tunnel models at DFRC and other NASA centers. NanoSonic would use
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 materials to fabricate the patterned &amp;quot;sensor skin&amp;quot; arrays.
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 is a free-standing self-assembled nanocomposite that acts as a
transducer to convert shear stress into changes into electrical
impedance. During this program, NanoSonic would work cooperatively with
Virginia Tech to develop an improved mechanical and electrical model of
skin friction sensor performance that will allow quantitative
optimization of material properties and suggest optimal methods for
sensor attachment and use for NASA applications. We will perform
synthesis of sensor skin materials with optimized transduction,
hysteresis and environmental properties, specifically for high Reynold's
number flow and also varying temperature use. We will fabricate
patterned two-dimensional sensor arrays and internal electronics using
optimized materials. NanoSonic and Virginia Tech will perform complete
analysis of sensor cross-sensitivities and noise sources to allow
optimization of signal-to-noise ratio and practical sensor sensitivity.
Support electronics will be developed to acquire, multiplex, store and
process raw sensor array data. NanoSonic and Virginia Tech will also
experimentally validate sensor array performance through extended water
and wind tunnel evaluation, and possible flight testing, and produce a
first-generation skin friction sensor array and data acquisition
electronics system for sale.
Intelligent Automation Inc., (IAI) and University of Central Florida (UCF) propose to develop a comprehensive numerical test suite for benchmarking current and future high performance computing activities. The key innovation in this effort is development of a comprehensive numerical test suite for benchmarking current and future high performance computing activities. Our technical approach builds on our experience in cluster computing, distributed agents system, parallel model developments for High Performance Computing (HPC) and our teams expertise in these areas for problem selection.
The developed benchmarking numerical suite (HPC benchmark  suite NMx) will include (1) dense and unsymmetrical matrix problems faced in space aviation and  problems in thermally driven structural response and radiation exchange, (2) implicit solution algorithms with production models and benchmarks for indefinite matrices and pathological cases (3)  configurations scaling for large systems (64, 256, 512, 1024  distributed high performance system) in shared, distributed and mixed memory conditions (4) documentation for strengths, weaknesses, and limitations of the toolkits used together with recommendations and (5) precision and round-off studies on serial and parallel machines, comparison of solutions on serial and parallel hardware with study of wall clock performance with respect to the number of processors.
Maxion Technologies, Inc. (Maxion) and Professor Mario Dagenais and his group at the University of Maryland (UMD) jointly propose to develop a compact, efficient, single mode, narrow linewidth tunable laser source in the 3.2?to?3.6 micron wavelength region. This effort, if successful, will assist NASA in its trace gas detection objectives by supplying NASA with the most critical (and difficult to obtain) laser source required. During the Phase 1 portion of this effort, Maxion and UMD propose to: a) develop/demonstrate a low-loss IC laser design, b) develop ultra-low modal reflectivity anti-reflection (AR) output facets on interband cascade laser (ICL) gain chips, and c) validate the AR coating quality by demonstrating continuous tuning of an ECL using the high temperature, state-of-the-art AR-coated gain chip developed during this program. The low-loss ICL design is important to improve the maximum cw operating temperature of IC lasers, currently limited to near-room-temperature values. The ultra-low reflectivity coating will permit the maximum possible wavelength tuning range to be achieved. This is important as it will realize tunability throughout the widest possible range (the goal being 3.2-to-3.6 microns) using a single semiconductor laser chip. The new low-loss IC design and the ultra-low reflectivity output facet represent, together, the two central roadblocks Maxion sees to achieving a compact, tunable laser source in the mid-infrared wavelength region. Consequently, the Phase I effort will represent a feasibility study to see if our approaches to overcoming these two roadblocks can be successful.
We propose to design, construct and test a first implementation of a
non-dispersive technique for the measurement of atomic absorption in the
plumes of liquid rocket engines in altitude test facilities.  Led by
NASA Stennis Space Center (SSC), the observation of metal atom emission
from liquid rocket engine exhausts at sea level conditions has become a
highly successful health monitoring technique, but in altitude tests
emission intensities are low.  SSC developed an atomic absorption system
which has provided useful measurements, but improved sensitivity is
required.  Non-dispersive atomic absorption presents a far simpler,
smaller, lower cost alternative to other techniques with comparable
spectral resolution and, of particular importance, should allow a more
forgiving receiver geometry, so that noise-modulated source light or
plume emission can be eliminated.
The objective of this project is to demonstrate intelligent health and maintenance status determination and predictive fault diagnosis techniques for NASA rocket engines under online and offline conditions from either on-board or maintenance, test and analytic data. AGNC proposes a Health and Maintenance Status Determination and Predictive Fault Diagnosis System (HMSD/PFDS). The fuzzy qualitative model for model-based residual generation and the rule-based evaluation of residuals using neural-fuzzy combination are defined. Intelligent data fusion strategies for health and maintenance determination and predictive fault diagnosis are developed for rocket engine systems/subsystems. The goal is to ensure safety, cost reduction, graceful degradation and re-optimization in the case of failures, malfunctions and damages. Kalman filter based and rule based evaluation of residuals using neural-fuzzy combination are developed. The use of fuzzy qualitative models takes into account the uncertainties associated with behavior descriptions and incorporates available expert failure symptom knowledge to recognize the particular failure features. Actual or simulated rocket engine sensed or derived data are utilized to evaluate the effectiveness of the health and maintenance determination and fault prognosis approaches for NASA platforms. Phase I is devoted to the HMSD/PFDS design and simulation. Phase II will result in development of a functional prototype.
Intelligent Automation, Inc (IAI) and its university partner, University
of Oklahoma (OU), Norman, propose a forward-looking airborne environment
sensor based on active weather radar technologies. The sensor consists
of a software-defined radar transceiver, compact dual-polarized array
antenna operating in the X-band as well as an integrated RF analog
front-end. By leveraging dual-polarization processing, the system will
be able to extract atmospheric parameters; thus it will be able to
identify and classify the atmospheric conditions as well as local
obscurants. The software defined radar transceiver has a Direct Digital
Synthesis (DDS) component which can easily generate high bandwidth chirp
waveforms (bandwidth &amp;gt;=200 MHz) and pulse shaping can be defined
digitally to reduce the side-lobes considerably.  IAI is currently
developing a software defined radar (SDR) platform that can adaptively
switch between different modes of operation for radar, by modifying both
transmit waveforms and receive signal-processing tasks on the fly.  The
proposed multi-channel radar technique and the system design will
leverage IAI's vast experience in SDR, RF hardware design and antenna
design and OU's capabilities in microwave design and field-proven
atmospheric hazard modeling and detection algorithm development.
Instabilities associated with fluid handling and operation in liquid rocket propulsion systems and test facilities usually manifest themselves as structural vibrations and may cause structural damage such as the cracks observed in the space shuttle hydrogen feed liners. While the source of the instability is directly related to the performance of a component such as a turbopump, valve or a flow control element, the associated pressure fluctuations as they propagate through the system have the potential to amplify and resonate with natural modes of the structural elements and components of the system. The innovation described in this proposal directly relates to an innovative multi-level approach that involves integration of analysis, at both the component and systems level, into a unified simulation framework. The primary source of the unsteadiness is modeled with a high-fidelity hybrid RANS/LES based CFD methodology that has been previously used to study instabilities in feed systems. System response to the driving instability will be simulated through a lumped element modeling (LEM) technique that will approximate the behavior of all the distributed elements that constitute the system.
Self-Deploying Foam Antenna Structures Project
Meteor Detection and UV Spectral Analysis System Project
Passive/Active Imaging Spectroscopy tools for in vivo detection of Plant Transformation Events and M Project
Graphic Displays to Facilitate Rapid Discovery, Diagnosis and Treatment of Medical Emergencies Project
A TOOL FOR THE DESIGN OF SAFETY-CRITICAL SPACE CREW SURVIVAL SYSTEMS Project
Utilizing MIL-STD-1553B Digital Data Bus Devices Across an IEEE-1394A Serial Bus Project
An Innovative Method of NOX Reduction Through Fuel Additives for the UEET Program Project
Multifunctional Nanostructured/Microporous Materials Project
Superhard Nanocrystalline Homometallic Stainless Steel on Steel for Seamless Coatings Project
Coatings for Foil Seals/Foil Bearings for Gas Turbine Engines Project
Bio-inspired Processing of Composite Films having Negative-Stiffness for Mechanical Damping Project
Using Expert Knowledge to Augment Simulation-Based Operational Analysis of Space Transportation Conc Project
An Advanced Nanotube Composite Fiber for High Temperature Components in Turbomachinery Project
Comprehensive Atomization/Spray Module for Advanced CFD Combustion Codes Project
Multifunctional Thermal Protection System for Future Space Transportation Vehicles Project
AUTOMATED LEARNING FOR REAL-TIME EXPERT SYSTEM IN MONTORING AND CONTROL Project
Multifunctional Spacecraft Coatings via Nanostructuring of Materials in Controlled Porosity Medium Project
High-Temperature Aeropropulsion Sensors Using Sapphire Microoptomechanical Systems Project
Intelligent Fiber Optic Systems Corporation (IFOS) in collaboration with Washington State University (WSU) proposes an approach of utilizing structurally integrated, distributed optical FBG sensor/piezo actuator arrays to monitor the health of a structure with accurate interpretation of sensor signals and real-time data processing.  Our method involves a dynamic response-based damage detection technique that offers a simple identification method with easy implementation.  We use electrically passive, electromagnetic interference (EMI) immune, multiplexable, fiber optic sensing technology with many sensors on a single light-weight small diameter optical fiber.  This is currently the most cost-effective and aerospace friendly way to overcome the sensor impoverished state of present day structures. This method has the capability of inspecting large area structures to provide global as well as local structural health information in real time.  As well as providing weight reduction, the miniaturization enabled by our optical fiber technology is key to diverse spin-off applications such as for sensor matrices in NASA's extra-vehicular and planetary exploration robots as well as sensor arrays for medical applications and homeland security robotic disarming of bombs.
A Multiscale GasKinetic/Particle (MGP) computational method is proposed to simulate the plume-crater-interaction/dust-impingement(PCIDI) problem.  The MGP method consists of a multiscale gaskinetic (MG) method for gasdynamics of rocket plume-in-vacuum flowfield, an Overlay method for gas-particle interaction.  MG combines BGK Gaskinetics (BGK) and direct simulation Monte Carlo (DSMC) methods with a domain decomposition technique to account for various scales of rarefied gasdynamics, covering continuum to free-molecular regimes. The dust particles are modeled by an additional distribution function in BGK, thus carried by the MG-generated flowfield through an overlay method. Dust properties are to be modeled using Discrete Element Method (DEM) simulation, which will lead to comprehensive continuum equations for crater formation. Phase II will extend the present MGP method to 3D, with more advanced dust particle properties and complex crater formulation.
ORBITEC and Duke University have teamed on this STTR to develop the ALERT (Advanced Lunar Exhaust-Regolith Transport) code which will include new developments in modeling of regolith erosion and entrainment as well as plume transport with full mass and momentum conservation. The Plume is handled in a Vlasov formalism with drag force on dust grains, dust equations of motion are solved over a size spectrum.  Because of its significant gravity and lack of atmosphere landing on the Moon's surface must involve impingement of the rocket plume directly on the Lunar regolith. The experience in the Apollo landings, both from the perspective of the astronauts viewing surface conditions during decent, and the effects on the exposed surfaces of the Surveyor 3 from the nearby landing of Apollo 12 have alerted us to the importance of good modeling of rocket exhaust plume regolith interactions.
Computational codes in physics and engineering often use implicit solution algorithms that require linear algebra tools such as Ax=b solvers, eigenvalue, optimization, or graph algorithms. Developers face major challenges in selecting linear algebra tools that can support their algorithms, numerical schemes, meshes, and computing hardware and to minimize the time, space and complexity. The existing libraries such as PETSc or LAPACK are "stretched" to the limits by new generation application codes which create big, unsymmetric, often dense, and poorly conditioned matrices. One of the obstacles in effective utilization of linear algebra libraries is lack of benchmark quality representative test cases and benchmarking toolkits for these types of problems. This project will develop, demonstrate and deliver a comprehensive numerical test suite for benchmark evaluation of linear algebra solvers for computational application software on High Performance Computers. Unlike existing benchmarks on static, Ax=b matrix, problems CFDRC-TACC team proposes new generation of dynamic, discipline specific and multidisciplinary functional benchmarks accounting for sparse/dense and unsymmetric matrices using web accessible benchmark matrix/problem generators. Our team has excellent expertise and tools (multiphysics solvers, sparse/dense solver libraries, benchmark cases, related projects, and understanding of NASA engineering/scientific challenges) as well as HPC resources to achieve this goal.
Current autonomous rendezvous and docking (AR&amp;amp;D) capability in low
Earth orbit (LEO) is constrained by sensor and effector mass, power, and
accuracy limits.  To this end, NASA Johnson Space Center has developed a
GPS receiver, called DRAGON (Dual RF Astrodynamic GPS Orbital
Navigator), specifically to address the sensor constraints.  The
proposed innovation includes creating a small, low-cost, and versatile
technology demonstrator to validate and increase the technology
readiness level of DRAGON and other state-of-the-art miniaturized
sensors and effectors in an on-orbit AR&amp;amp;D operational scenario.  For
Phase 1, a demonstration platform will be developed that utilizes two
picosatellites in LEO, and relative GPS as the primary sensor.  These
satellites will be launched as a single unit from the SSPL (Space
Shuttle Payload Launcher) on STS 127, then separate and transmit DRAGON
GPS data.  The picosatellite technology demonstrator will be at a TRL of
7 at the end of Phase 1.  For Phase 2, the demonstration platform will
be further developed to further validate DRAGON, and validate IMU
sensors, a 1st generation reaction control system, a 1st generation
guidance navigation and control system, communication links, and an
undocking mechanism.
Thermoelectric (TE) generators/refrigerators have the advantages of lack of moving parts, quiet operation, and flexibility in deployment, but their use has been limited because of their relatively low conversion efficiency.   Two major loss components are conductive (phonon) heat transfer through the TE lattice and parasitic losses at fabrication interfaces.   Shock wave consolidation of thermoelectric nanopowders to produce TE devices will reduce both loss sources, leading to enhanced efficiency devices.  

The conversion efficiency of a TE device will always be thermodynamically limited by the Carnot ratio of (Th-Tc)/Th, where Th and Tc are the temperatures of the hot and cold junctions.   Present technology thermoelectric devices can provide conversion efficiencies up to a third of the Carnot limit.  With the restrictions on phonon transport acruing from nanopowder consolidation, conversion efficiencies of over 50&#37; of the Carnot limit should be possible.
Orbital Technologies Corporation (ORBITEC) and the University of Alabama at Huntsville (UAH) propose to develop the Advanced Microwave Electrothermal Thruster (AMET), a high-efficiency thruster which will use water propellant to enable various Lunar and Mars missions.  The proposed AMET will incorporate a number of innovations to dramatically improve upon existing designs, including the use of a lower microwave frequency (915 MHz) to permit the achievement of very high microwave generation efficiency with commercially-available magnetrons.  The AMET is a particularly attractive option for this class of missions because it provides specific impulse (~800 seconds) well beyond the reach of chemical propulsion, it provides high thrust per unit power to keep transit times acceptably short, and it permits the use of an easily-storable propellant (water) which is known to be available on both the Moon and Mars.  ORBITEC staff has experience operating microwave electrothermal thrusters with water vapor as propellant.  In Phase I, the AMET will be demonstrated with water vapor propellant to demonstrate feasibility, reaching TRL 4.  In Phase II, a flight-like AMET will be developed and demonstrated and a design will be prepared for an entire AMET flight propulsion system, reaching TRL 6.
Aurora Flight Sciences, The MIT Manned Vehicle Laboratory (MVL), and the MIT Humans and Automation Laboratory (HAL) together propose to adapt existing software, algorithms, and human interfaces into a software system that performs command and control of a heterogeneous team of mobile robots, operating in a variety of modalities, to perform multi-agent planetary exploration.  The system will provide ground control user interfaces and data management that (1) allows for interactive user control of the team in a time-delayed control environment, (2) maintains operator situation awareness, providing a human interface for setting up a task queue that can be autonomously executed with limited/no human interaction,  (3) allows the multi-robot team to optimize task performance as geospatial, navigation and other sensor information is gathered, and (4) is supported by recent algorithm and software developments in the military multi-vehicle control regime (including human interfaces).
Advanced pump inducer design technology that uses high inlet diffusion blades, operates at a very low flow coefficient, and employs a cavitation control and stability device.  A preliminary scoping inducer test with this technology indicated a doubling of the suction specific speed capability over current inducers.  A three to four fold increase over current technology is the goal of this research effort.  This increase would significantly enhance the capability of rocket engine systems through increased thrust-to-weight, specific impulse, simplicity, operational safety, and turbopump life.  It would also reduce turbopump and propellant tank weight and system costs by eliminating boost pump systems and allowing for thinner lower pressure tank walls.  Ultimately, the technology opens up the rocket engine/vehicle design space and allows for a large increase in vehicle performance by significantly moving the pump suction performance constraint from its current position.
The proposed effort is to investigate a novel uncertainty quantification (UQ) approach based on non-intrusive polynomial chaos (NIPC) for computationally efficient and accurate quantification of uncertainties in spacecraft system models within a multidisciplinary analysis and optimization (MAO) framework.  The UQ approach will include the modeling of both inherent (probabilistic) and epistemic uncertainties and the propagation of these with NIPC. Comparisons between crude Monte-Carlo sampling will be made during validation of the approach.  Software will be developed to implement the UQ approach in a generic way.  With scalability in mind, this software will be utilized within a space system MAO framework containing many uncertain parameters. Also in Phase I, a simple graphical user interface will be created to implement the UQ approach. Both the software and UQ approach developed will be tested on a model spacecraft simulation problem with uncertainties. This proposed work will compliment M4 Engineering's expertise in developing modeling and simulation technologies that solve relevant demonstration applications. The researchers from Missouri S&amp;T (RI) will guide the implementation of UQ methodology and contribute to the proposed effort with their experience and expertise in UQ in aerospace simulations.
The proposed innovation is the replacement of existing test stand and parking lot  fixtures with current SSL LED technology. The replacement fixtures will reduce energy consumption, generate less heat and provide maintenance free operation for over 50,000 hours. An explosion-proof fixture is capable of containing an internal combustion event without allowing flames or hot gasses to escape to the surrounding environment. The lighting fixture defined is an explosion-proof fixture for use in hazardous hydrogen/oxygen atmospheres. Current fixtures contain a 110 Watt reflectored incandescent lamp. SSL sources are remarkably efficient compared to incandescent sources. The 110 Watt lamp in existing explosion-proof fixtures will be replaced by an SSL fixture requiring only around 29 Watts for the equivalent lighting output.  The proposed Energy Focus solution will be an efficient, solid-state, explosion-proof  fixture for use in hydrogen/oxygen atmospheres which is compatible with current systems and provides the required lighting distribution. It will do this through advanced thermal and electrical power management to ensure long fixture life
The proposed innovation utilizes carbon nanotubes (CNTs) coated with pseudo-capacitive MnO2 material as nano-composite electrode and ionic electrolyte for the construction of ultracapacitors. This novel approach of using nano-structured CNTs architectures provides high surface area of attachment of MnO2 nano-particles to maximize the charge efficiency and power capacity and to reduce series resistance. Preliminary results at Vanderbilt University using this CNTs/ MnO2 nano-composite as electrode of an ultracapacitor has demonstrated enhanced capacitor behavior of &gt;400X over pristine CNTs as electrode.

During Phase I, we will demonstrate in the laboratory that the proposed novel concept is feasible and measure the power and energy generation capacity, efficiency, and charging/discharging cycle durability. The key factor to successful exploitation of the CNT/ MnO2 nano-structured composite for ultracapacitor applications is closely related to further understanding and control of the physics, materials, and micro-fabrication technology. The proposed Phase I work provides a systematic, logical, and coherent investigation of the material issue, device fabrication, characterization, simulation, evaluation, and optimization to meet high power requirements.
Radioisotope Power Systems (RPS) are critical for future flagship exploration missions in space and on planetary surfaces.  Small improvements in the RPS performance, weight, size, and/or reliability can have a dramatic effect on the scientific capability of the vehicle and the overall mission costs.  Radioisotope Thermophotovoltaic (RTPV) energy converters are a particular type of RPS that directly converts the heat produced by a General Purpose Heat Source (GPHS) to electrical power using a specialized Photovoltaic (PV) cell.  A key element in an RTPV system is the power conversion electronics system that efficiently converts the low-voltage current from each PV cell into useable, stable bus voltage for powering spacecraft systems despite issues such as non-uniform illumination, PV cell degradation, and decay of the GPHS source.  In this project, Creare and the Massachusetts Institute of Technology (MIT) propose to develop an advanced, multi-channel maximum power point tracking module (MPPT) that is optimized for RTPV systems.  The converter will provide stable output voltage from a 16-cell PV array that, when coupled with advanced PV technology of the RTPV system, will provide high system efficiency.  In Phase I, we will design a prototype power tracking module, which will be fully characterized for conversion efficiency.  We will also assess the impact of this new MPPT on the overall RTPV system design and performance.
NASA seeks to develop high specific energy primary batteries that are safe and capable of performing under a wide temperature range, for manned space missions. To meet this goal, CFX Battery Inc. proposes to develop, characterize, and establish technological feasibility of a new Li/SF-CFx based high capacity lithium primary battery that offers higher rate capability and enhanced safety than conventional Li/CFx primary systems. In Phase I of the project, CFX Battery will develop the sub-fluorinated CFx cathode materials that offer high capacity (&gt;700 mAh/g) and rate capability. In addition, novel non-flammable electrolytes that are highly conductive and electrochemically stable at a wide temperature range will be developed to increase the safety of the Li/SF-CFx system. The technological feasibility of the sub-fluorinated CFx cathode and non-flammable electrolyte combination will be demonstrated using small coin and pouch cells. Phase II of the project will implement the developed technology in large cell formats and perform any refinement and optimization that will be needed to bring the technology to a commercially usable stage.
The process of aircraft design requires the integration of data from individual analysis of aerodynamic, structural, thermal, and behavioral properties of a flight vehicle. At present, there is no simple way to integrate the results of the analyses early in the design process.  Aurora Flight Sciences and the Massachusetts Institute of Technology Aerospace Computational Design Laboratory propose to create a system level analysis framework called the Extensible Data Set Architecture to facilitate this integration, and therefore provide rapid system-wide impact assessment of design changes to a flight vehicle. 

The Extensible Data Set Architecture (EDSA) is a generic data storage structure ready for use by a diverse and extendable set of software tools and codes. The EDSA can be arbitrarily extended to allow additional functionality and provides a natural framework for future development of aerospace systems. The framework includes as part of its structure the relevant metadata for ensuring version control, traceability, context-specific documentation, and interface data for relevant tools, while providing a simple structure for extending an existing data set to transparently include new members.

The four primary components of this framework will be 1) an extensible data set used by all codes and analysis tools to store and exchange relevant information; 2) a tool set which can take advantage of the data set, made up of both existing programs and user defined vehicle specific codes; 3) a controller which provides organization, operates the tools, and manages iteration and optimization of the design, and 4) a display code which presents the results of the analysis to the user.
This NASA Phase I STTR effort will establish the feasibility of developing a compact broadband near to mid-IR programmable optical comb for use in laser based remote sensing and communications.  The comb generator will use a waveguide-based optical parametric gain block technology that can have ultra wideband (&gt;250nm) operation with very high gain (&gt;25dB) in a very compact footprint. This approach is enabled by advances both in waveguide processing and in substrate growth, which allows for fabrication of complex waveguide structures to be formed in commercially available large-diameter nonlinear optical substrates.  Optical comb sources are increasing the achievable sensitivity and system performance for a range of applications including gas sensing, optical communications, frequency metrology, precision spectroscopy and optical coherence tomography and thus directly addresses NASA's mission to advance remote sensing measurements to improve the scientific understanding of the Earth specified in 2009 STTR call: T4.01 Lidar, Radar and Passive Microwave.
This Small Business Innovation Research Phase I effort focuses on development of novel metal-oxide-carbon nanocomposites for application in pseudocapacitive electrochemical supercapacitors.  Specifically, nanocomposites based on manganese, titanium, tantalum and vanadium oxides will be incorporated, at the nanoscale level, with electrically conductive carbon supports.  Our focus will be to combine the desired pseudocapacitive characteristics of metal oxides with high surface area and large electrical conductivity of carbon supports while achieving economical and scalable manufacturing.  The proposed nanocomposite materials will be tested as electrode materials in aqueous and nonaqueous supercapacitors.    
The proposed project will be a joint effort on NanoScale Corporation and Battelle Memorial Institute.  NanoScale's role in the effort will be to synthesize nanocomposite materials, characterize their physical and chemical properties, and to optimize them based on results of electrochemical testing carried out by Battelle.  Battelle's role in the effort will be to take the metal oxides prepared by NanoScale and fabricate them into supercapacitor elements to be tested in half-cell and full-cell devices.
NanoScale is uniquely qualified to carry out the proposed research due to its rich experience in development and scaled-up synthesis of nanosized materials, including materials for battery applications.  NanoScale has worked previously on several projects related to battery technologies.
NASA has very specific requirements when it comes to power generation technology. Solar panels are an obvious solution but making them suitable for the grueling space environment. Panels must withstand intense radiation bombardment and extreme temperature swings while maintaining acceptable levels of efficiency. Additionally because of the exorbitant costs of current technology NASA would like to reduce the costs associated with power generation. We propose to introduce a new class of solar cells that utilize the environmental strengths and absorption properties on InGaN technology. This material has an amazingly high defect tolerance but even more impressively can be tuned to capture any wave length of light in the solar spectrum. Our proposal offers the possibility of solar cell efficiencies exceeding 70&#37; while providing excellent radiation resistance and a price point similar to that of silicon, 100 times cheaper than current space age technology.
NASA space exploration missions stand to benefit from reliable means to
conserve energy that is otherwise given off as waste heat.
Thermoelectric generators have demonstrated the potential for scavenging
waste heat energy, yet are still limited by technical and geometrical
boundaries that must be overcome for long term reliability in
applications such as interplanetary missions. To address these
limitations, Nanohmics Inc. and Professor Kevin Stokes at the University
of New Orleans propose to fabricate conformable thermoelectric
generators for long-term radiation resistance in space applications. The
proposed device will incorporate thermoelectric p- and n-doped high ZT
thermoelectric legs that aredeposited onto a substrate.
The innovation proposed here is a computational framework for high performance, high fidelity computational fluid dynamics (CFD) to enable accurate, fast and robust simulation of unsteady turbulent, reacting or non-reacting flows involving real or ideal fluids in several applications.  This framework will provide a state-of-the-art unsteady turbulent flow simulation capability employing Hybrid RANS-LES (HRLES) methods which are a blend of Reynolds Averaged Navier-Stokes (RANS) and Large Eddy Simulation (LES) approaches.  Low-dissipation schemes will be employed which will enable high-fidelity modeling of unsteady flows as well as acoustic fields.  Additionally, Lagrangian particle tracking and Eulerian multiphase models will be incorporated to enable simulation of multiphase combustion involving solid particles or liquid droplets.  The work proposed here will result in a state-of-the-art design and analysis tool to enable the accurate modeling of: (a) multiphase combustion in solid and liquid rocket engines, (b) combustion stability analysis (c) acoustic fields of space propulsion syatems in near-ground operation, (d) small valves and turbopumps, etc. which constitute critical components of versatile space propulsion engines part of NASA's Constellation Program.
Radioisotope Power Systems (RPS) are critical for future flagship exploration missions in space and on planetary surfaces.  Small improvements in the RPS performance, weight, size, and/or reliability can have a dramatic effect on the scientific capability of the vehicle and the overall mission costs.  Radioisotope Thermophotovoltaic (RTPV) energy converters are a particular type of RPS that directly convert the heat produced by a General Purpose Heat Source (GPHS) to electrical power using a specialized Photovoltaic (PV) cell.  A key element in an RTPV system is the radiative emitter that converts GPHS thermal energy to radiative energy that illuminates the PV cell.  In this project, Creare and the Massachusetts Institute of Technology (MIT) propose to develop an advanced, 2-D, photonic crystal radiative emitter that is optimized for RTPV systems.  The emitter will provide high emittance in the bandgap of the PV cell with low emittance elsewhere that, when coupled with advanced PV cell filter technology, will provide high system efficiency.  In Phase I, we will design the emitter and fabricate test samples, which will be fully characterized for high-temperature emittance and durability.  We will also assess the impact of this new emitter on the overall RTPV system design and performance.
Intelligent robots for planetary exploration produce a wealth of information ? both science data collected by the robots and data about remote robotic operations.  The management and analysis of this data provides unique opportunities as well as significant challenges for both science and rover operations, including understanding and summarizing what data have been collected and using this knowledge to improve data access. TRACLabs proposes to develop software for automatically building semantic summaries of data and images collected by remote rovers and using this information to retrieve subsets of this information for manipulation and visualization.  We will use these semantic summaries to construct scripts for spatial and event-based data retrieval (e.g., retrieve data collected at a location).  This ability to retrieve and manipulate a subset of data relevant to a situation of interest will be used to provide details on demand displays as well as support data exploration starting from a situation or event.  Semantic interpretation has focused on document interpretation and database indexing while the proposed approach provides in-line semantic annotation and summarization of data streams.  TRACLabs and its partner Carnegie Mellon University bring extensive experience in advanced software development and rover operations enabling integrated software solutions for NASA's planetary exploration.
The proposed innovation is an aircraft flight envelope monitoring system
that will provide real-time in-cockpit estimations of aircraft flight
envelope boundaries, performance, and controllability.  The adaptable
monitoring system will provide information on current and predicted
aircraft performance and controllability, alerting the pilot to any
aerodynamic degradation of the control effectiveness.  This includes
high angle-of-attack, heavy rain, in-flight icing encounters,
environmental contamination of surfaces, and structural or battle
damage.  The real-time monitoring system measures the time-averaged and
RMS control surface hinge moment from all aircraft aerodynamic controls.
Control surface hinge moment is sensitive to the aerodynamic
characteristics of the flying surface, including separation.  These data
are processed and information on the current and predicted future state
of aircraft control (including asymmetric cases) is made available to
the pilot or flight management system.  As opposed to other single-point
monitoring systems, the proposed system has the distinct advantage that
it functions by measuring the integrated effect over the entire control
surface.  The use of real-time control surface hinge moment monitoring
is an innovative and robust concept for predicting aircraft flight
envelope boundaries and controllability.
NEI Corporation and University of Florida propose to develop a mixed
metal oxide cathode that is a composite of two and three dimensional
structures. At the atomic level, the crystal structure is expected to be
both open (for fast Li-ion intercalation/diffusion) and stable (for good
reversibility). The cathode materials developed in this program are
expected to have high capacity and high rate capability, as well as long
cycle life. Additionally, the crystal structure of the proposed material
is expected to be stable over a wide temperature range upon Li-ion
deintercalation, without oxygen evolution. This will allow the Li-ion
cells to operate at high energy and power levels without compromising on
safety. The target specific capacity of the proposed cathode is &amp;gt;200
mAh/g with a nominal working voltage of 4.8V, which gives out &amp;gt;960
Wh/kg specific energy. A unique feature of the proposed program is that
it integrates theoretical and experimental work to enable a new
generation of high capacity and high voltage cathode materials: the
composition range and structure will be determined utilizing first
principles calculation techniques developed by our STTR partner at
University of Florida, and NEI Corp. will produce the cathode materials
using its scalable and low cost process. The structure, composition,
particle morphology and electrochemical performance will then be
determined. The objective of the Phase I STTR program is to demonstrate
the feasibility of a new high capacity and high voltage cathode material
for rechargeable Li-ion batteries. In Phase II, the composition and
morphology of the powders will be optimized, and integrated into large
format prototype Li-ion batteries by working in partnership with a
battery manufacturer(s). The objective will be to design and fabricate
battery packs that meet the functional performance requirements set by NASA.
The challenges of designing, developing, and fielding advanced propulsion systems continue to increase as NASA's Vision for Space Exploration Program moves forward with new solid propulsion elements ({i.e., Ares I and V).  Our existing computational tool for solid motor analysis (BurnSurf) generates modest surface recession, but the mesh deformation techniques employed often fail as the surface regression increases, particularly near corners.  For complex grain designs with highly complicated surface topologies (e.g., star shapes), simple mesh deformation is no longer desirable.  Our proposed innovation will utilize surface mesh modification and volume mesh generation to locally rebuild the burning surface mesh and the adjacent volume mesh.  The innovation will address integrated surface and volume mesh regeneration and reconnection techniques for modifying mesh topologies along with two phase burning surface models to create a unique 3D software tool for next generation solid motor internal environment characterization.  Our research products will provide NASA with the important capability to simultaneously analyze solid propellant combustion, heat transfer, and grain burnback within a single framework.  We will demonstrate feasibility of the approach using a two phase grain burning model coupled with surface recession for a simple shape in the TRL range of 3-4.
The Keystone and MSU team propose to demonstrate the feasibility of solid-state joining high strength and temperature alloys utilizing the Thermal Stir Welding process. The alloy selected for this proposed effort is Haynes 230; the alloy of choice typically utilized in rocket engine nozzel skirts. This class of alloys is difficult to fusion weld and has not been shown weldable by friction stir methods. Thus, the Keystone team is proposing to utilize the Thermal Stir Welding process; a solid-state welding process that decouples the stirring and heating features of the process to enable optimization of each key parameter. By independently controlling and optimizing these two process parameters, the best metal working parameters can be identified and utilized to plasticize and stir the Haynes 230 alloy to achieve solid-state welding. Achievement of this objective will enable superior mechanical properties in the weld joint and thus maximize the capability of the weld for the intended application.
A non-intrusive method for measuring velocities in a rocket exhaust is proposed in a joint effort by MetroLaser and Vanderbilt University. Hydroxyl Tagging Velocimetry (HTV) uses an ultraviolet laser to tag a region of the flow with OH molecules, and interrogates them after a short delay with a second laser to obtain velocity from time-of-flight data. The method relies on the dissociation of H2O molecules naturally present in the flow, and thus requires no seeding. Being an all-optical technique, it is not adversely affected by high temperatures or high dynamic pressures. Analyses and experiments conducted during the Phase I effort demonstrated feasibility by showing that OH tag lifetimes in a simulated rocket exhaust environment were sufficiently long to enable accurate determination of tag displacements corresponding to typical rocket exhaust velocities. The method was demonstrated by measuring velocities in the exhaust gases of a laboratory scale burner at temperatures and chemical compositions representative of a H2/O2 rocket exhaust. Design tradeoff studies predicted that at measurement ranges of 20 to 50 feet the accuracies would be from two to five percent. This proposal outlines a plan to develop a prototype HTV instrument and demonstrate it in a rocket engine exhaust.
This project will demonstrate the benefits of a partial emission pump coupled with a zero net positive suction pressure inducer design to achieve robust, deep throttling capability. This pump application is well suited for 5k to 15k lbf thrust range rocket engines.
Automated Contingency Management (ACM) is an emerging and game-changing area of engineering and scientific research that integrates prognostics and health management concept and intelligent control. As leaders in this field, Impact Technologies and Georgia Institute of Technology, propose to build off a strong foundation of ACM research performed with NASA and DARPA in the past few years to both mature the applicability of ACM technology for real aerospace components and push the envelop on the capability and breadth of the technology itself. A prognostics-enhanced, three-tiered ACM architecture for critical aerospace systems has been conceptualized and demonstrated in Phase I. The proposed Phase II effort is focusing on utilizing prognostics at the higher levels of the control hierarchy and is introducing novel concepts to address the fault-tolerant control design at the middle level from the areas of model predictive control, system dynamic inversion, intelligent search techniques, and optimization / system identification algorithms for mission adaptation at the high level. Game theoretic notions are exploited to distribute optimally the available control authority between the components. An electromechanical flight actuator and a UAV platform will be utilized as testbeds for performance evaluation. Significant benefits are anticipated to NASA, DoD, and industry.
ZONA Technology, Inc (ZONA) and Arizona State University (ASU) propose a R&amp;D effort to further develop the ground flutter testing system in place of a wind tunnel (WT), called the Dry Wind Tunnel (DWT) system. The DWT system consists of a ground vibration test (GVT) hardware system and a real-time unsteady aerodynamic force generation software system developed from an aerodynamic reduced order model (ROM). 

The DWT system can serve as a replacement or complimentary means for flutter/ASE instability testing to a WT.  Our Phase I effort has successfully demonstrated the validity of the DWT concept. That is, DWT testing can truly simulate in real time the unsteady aerodynamics through a GVT hardware system, namely the shakers and sensors.  Merits of a DWT are many: It can use real full-size aircraft/wing structure including inherent structural nonlinearity and flight controller in-the loop, instead of a flutter model for WT, hence a cost/time effective test system.  It can be carried out with a GVT setup, and because of the simulated aerodynamics the DWT measured data is wall-interference free. The DWT system can be applicable to flutter envelope expansion and flying quality programs of military and civil transport as well as general aviation aircraft.
The objective of the Phase II STTR project is to develop a prototype multi-analyte sensor system to detect gaseous analytes present in the test stands during propulsion test activities. Data on the concentrations of propellant-derived species are important to assure proper integration of safety protocols with testing activities to comply with environmental regulations.  InnoSense LLC (ISL) has utilized its Chemical Fingerprint(TM) sensor array fabrication technology in Phase I to establish the feasibility of the multi-analyte approach.  In particular, we have detected carbon dioxide, isopropanol, carbon monoxide, kerosene and ethylene as potential target analytes in the test stands. We have employed pin printing-based fabrication strategies, which would allow us to customize the sensor suite specific to engine types using different propellants. Concerning the placement of the sensors at the test stands, NASA users will use their discretion in deciding the location based on CFD (Computational Fluid Dynamics) reports. The sensors developed under this project can be used to validate these CFD models. ISL has received endorsement letters on the technology from two NASA prime contractors. ISL has also secured Phase III funding commitment from two commercialization partners. For assuring success of this project, ISL has assembled a technical team with a cumulative 90 person-years of experience in developing commercially viable sensor systems.
We propose to develop and demonstrate an receiver system utilizing our novel technique for tracking and compensating for laser wavelength shifts in lidar systems.  During Phase 1, we demonstrated that in addition to tracking and correcting for laser frequency drift, the system is able to track and correct for etalon frequency drift (in fact, only this relative frequency drift can be tracked).  Data was collected before, during and after a frequency drift over a period of time typical of lidar data integration times.  It was seen that integrating without the correction resulted in data too blurred to have any value, but that the correction system compensated for the shift and allowed for proper wavelength measurements.  We now look to incorporate this technique into a lidar receiver system and demonstrate its viability in measuring wind velocity.  This receiver would prove the ability to reduce the cost and technical difficulties in building a wind lidar system both for NASA programs (NASA-GSFC CATS wind lidar) and commercial systems for use in weather forecasting and airport wind shear monitoring.
Future lunar and planetary explorations will require the storage of cryogenic propellants, particularly liquid oxygen (LOX) and liquid hydrogen (LH2), in low earth orbit (LEO) for periods of time ranging from days to months, and possibly longer. LEO is a relatively warm thermal environment and without careful thermal management, significant quantities of stored liquid cryogens can be lost due to boil-off.
Advanced liquid rocket propulsion systems must achieve longer burn times without performance degradation to allow the lowest cost per kilogram access to space. Ablative thrust chambers have an extensive heritage and are the low cost approach to fabricating rocket thrust chambers.
The Launch Abort System (LAS) for the Orion Crew Exploration Vehicle (CEV) will provide a safe escape for the crew in the event of an emergency during launch.  A key component of the LAS is its Attitude Control Motor (ACM).  Recent testing of the ACM valve assembly has resulted in failure during hot-fire testing.  These failures are believed to be the result of the molybdenum alloy component distorting during firing.  Based on these results, alternative materials with higher temperature capability are needed for the ACM valve assembly.  During Phase I, innovative electrochemical forming (EL-FormTM) techniques will be developed for producing ACM hot gas components near net shape.  Both rhenium and rhenium coated graphite composite materials will be evaluated.  PPI will partner with Southern Research Institute, a leader in the testing of advanced, high temperature materials, for the materials properties testing.  During Phase II, ACM hot gas components will be fabricated and hot fire tested.  In addition to rhenium and rhenium coated graphite composites, alternative materials such as molybdenum-rhenium and tungsten-rhenium materials will be evaluated.
Soil debris liberated by spacecraft landing on the lunar surface may damage and contaminate surrounding spacecraft and habitat structures. Current numerical simulations of these events lack credibility because lunar environment complexities have never been captured in suitable models: the mixed rarefied-continuum nature of the plume's surface layer flow, and the highly irregular soil particle shapes with peculiar granular stresses, particle aerodynamics, and particle collision characteristics. CFDRC and the University of Florida (UF) propose to apply their uniquely capable simulations simulation tools to derive credible lunar gas and granular flow physics sub-models from first principles. CFDRC's unified continuum-rarefied flow solver will be applied to characterize the surface layer flow structure and assess interference effects from surface craters and rocks. The code's unique ability to resolve highly irregular shapes with an automated adaptive Cartesian approach will be applied to compute realistic particle aerodynamics. A Lagrangian particle collision model developed for efficiently simulating dense particle streams will characterize particle collision and dispersion effects. A novel fundamental soil model developed by UF to describe all constituent stresses in a single fundamental model for arbitrary particle shapes mixtures will be applied. Phase I will demonstrate the unique capabilities of the proposed simulation tools. During Phase II, these tools will be applied to create high fidelity physics sub-models for integration in current erosion simulation models.
While in the 1970's and 1980's, composites were adopted for aerospace structure for increased performance and weight savings, the 1990's and 2000's witnessed the attention towards cost-effective fabrication.  All thermoset processes that utilize such machines rely on autoclaves to consolidate the laminates, at significant acquisition and operational expense.  Autoclaves to consolidate wings are hugely expensive.  Autoclaves for fuselages are nearly cost-prohibitive (only one exists).  Autoclaves for the Ares V do not exist.  The marketplace would welcome a proven out-of-autoclave fabrication technology.

The tasks in the ASI/UD-CCM STTR phase 1 was to assess the performance of the current TP-ATP heads, do a model based parametric study to determine possible head and process parameter changes and demonstrate an improved understanding of the head, with a goal of autoclave level properties.

A set of models for the in situ Automated Tow/Tape Placement (ATP) processes that capture the important process phenomena were developed by UD-CCM.   Accudyne then measured the laminate roughness, fabricated samples using a variety of conditions and tested the samples.    Testing of the laminates indicate: placing with flat tape and using improved head chilling increases mechanical properties.  Compacting with only a < load reduces properties.  Using a vacuum bag oven reconsolidation is ineffective, and even reduces mechanical properties.

The phase 2 program innovation is to develop and deploy University of Delaware process models to Accudyne's thermoplastic tow and tape placement head to remedy the mechanical property shortfall between the two fabrication processes used to manufacture large composite aerospace structure important to NASA.  An additional advantage that would accrue by adopting TP-ATP would be the use of novel thermoplastic materials with thermal stability and toughness far in excess of what thermosetting materials can achieve.
In Phase I the team completed all scheduled initial efforts, 1) evaluation of relevant current simulation capabilities, 2) development of aero-thermo-elastic-propulsion simulation of air-breathing hypersonic flight vehicles (AHFVs) and other flight vehicles, and 3) generation of a set of recommendations for multidisciplinary simulation capability, as planned. Numerical examples of this capability are also presented herein.  In Phase II we propose to complete our ongoing effort in the developmental area and further extend the tasks that will include acoustics. This team will complete development of an independent, Multidisciplinary Design and Analysis (MDA) tool, primarily employing their respective numerical, finite element based, computer codes in disciplines as Aerodynamics, Thermal, Structures, Propulsion, Acoustics, and Controls, among others. The resulting MDA code, designed in modular form, could be effortlessly interfaced with existing commercial or user-provided codes, if desired. Once completed, the code is expected to have extensive applications in the design and analysis of flight vehicles with a TRL level of 6 or so.
The NASA SBIR/STTR solicitation emphasizes the area of MDA as a current topic of primary importance for ARMD Fundamental Aeronautics Program, and this proposal is highly relevant to such a solicitation.
Limited downlink data rate constrains the amount of data that can be sent to earth from a spacecraft. Data from the onboard health monitoring sensors needs to be accommodated within a small fraction of this downlink bandwidth. The problem is more acute for interplanetary missions, where the downlink data rate is significantly lower than the low earth orbit missions. Such constraint prohibits transmission of the complete set of health monitoring data. 

This proposed Phase-II effort is geared towards providing enhanced remote diagnostics using limited telemetry bandwidth. Diagnostic accuracy of health management system depends more on the information content of the monitored data, than on its sheer volume. We propose accommodating more information within the allocated downlink bandwidth for health monitoring by performing intelligent data reduction. The onboard data reduction process employs sensor fusion, dimensionality reduction and temporal fusion techniques.
The minimization of vibration-induced damage has become a critical issue for rocket launch ground support electronics (GSE).  In particular, the effect of high acoustic and exhaust blast loading during launch results in large amplitude motions of the support structures, which can transmit damaging loads to the GSE.  This results in the need for extensive check out and frequent repairs of GSE systems after each launch, as well as extensive design and qualification testing to ensure the survivability of this equipment.  To this end, Techno-Sciences Inc. (TSi), in collaboration with the University of Maryland (UMD) and LORD Corporation, has developed an innovative Adaptive Magnetorheological Isolator (AMI) system for GSE.  The AMI system utilizes the continuously adjustable energy absorption capabilities of magnetorheological (MR) fluid dampers to automatically adjust to real-time environmental measurements as well as GSE rack properties.  Because of its adaptability and optimal vibration isolation capabilities, the AMI system significantly reduces design and life-cycle costs as well as enhances equipment reliability.
During our Phase I STTR effort, Balcones Technologies, LLC and The University of Texas Center for Electromechanics (CEM) successfully achieved all Phase I objectives and developed a concept design for an active Vibration Isolation System (VIS) that fully meets all requirements defined or implied in STTR 2007-1 Subtopic T6.02.  Now the Balcones Technologies - CEM team proposes to develop, test, and deliver a prototype version of our active VIS.  Furthermore, the delivered prototype system, coupled with our proposed Phase II commercialization activities, will be substantially advanced from a proof-of-principle system and will embody the critical aspects of pre-production systems, ready to quickly transition to the NASA qualification process and finished product.

	Our Phase I effort yielded a high performance, cost effective, highly reliable, actively controlled Vibration Isolation System (VIS) for ground support electronics racks or groups of racks on the Mobile Launch Platform (MLP).  Some features are listed below.
?	does not rely on predictable vibration input
?	applies across broad range of ground support electronics or other sensitive systems
?	does not depend on detailed knowledge or testing of the components being protected
?	is compatible with operation from a self-contained power supply if desired by NASA
?	offers up to 18x reduction in payload peak accelerations compared to passive approaches and up to 5x reduction compared to semi-active approaches
?	can be configured to isolate electronics racks individually, in small groups, or via an isolation system for an entire floor
?	is modular in both hardware and software, exploiting COTS and previously developed CEM technology to facilitate rapid development and commercialization
?	exploits approximately $24M of highly successful active suspension R&amp;D at CEM for military vehicles for the controls, architecture, and actuator development technology.
Thermoelectric (TE) devices already found a wide range of commercial, military and aerospace applications. However, at present commercially available TE devices typically offer limited heat to electricity conversion efficiencies, well below the fundamental thermodynamic limit, calling for the development of higher efficiency materials. The team of MicroXact Inc and UCLA DRL is proposing to develop a revolutionary ultrahigh efficiency thermoelectric material fabricated on completely new fabrication principles. The material comprises the three-dimensional "wells" of Ge/Si Quantum Quantum Dot Superlattices fabricated by a conformal coating of macroporous silicon (MPSi) pore walls. Such a material will provide very high ZT values at macroscopic thicknesses of the material, permitting 30&#37; or more conversion efficiencies. In Phase I of the project the team will develop a thorough model of the proposed TE material, will theoretically predict the achievable efficiency of the material and will demonstrate the growth of the single layer of QDs on the pore walls. In Phase II the team will fabricate the proposed material and will demonstrate the efficiencies exceeding 30&#37;. After the Phase II the team will attract VC funding to commercialize the technology.
A compact, low-power GN&amp;amp;C system is essential to the success of
pico-satellite Automated Rendezvous and Docking (AR&amp;amp;D).  Austin
Satellite Design (ASD) proposes to deliver a working design of an
integrated six-degree-of-freedom (DOF) Guidance, Navigation, and Control
(GN&amp;amp;C) system for pico-satellites at the conclusion of Phase 1 of
this STTR.  A six DOF translation and rotation determination and control
system will be designed for a pico-satellite form-factor to generate the
onboard guidance and control necessary to demonstrate autonomous control
stability and perform simple proximity maneuvers.  An existing NASA/JSC
GPS receiver will be utilized for navigation.  Added sensors, such as a
magnetometer, will be combined with GPS signals for attitude
determination.  A thruster actuator concept will be identified and a
design produced that satisfies anticipated operational requirements and
that fits within the mass and power constraints of the pico-satellite
mission.  Flight hardware will not be procured until Phase 2; however,
component characteristics will be documented and modeled during Phase 1
and GN&amp;amp;C algorithms will be written to include them.  Software that
can be deployed to embedded systems will be written and validated in
simulation.  At the conclusion of Phase 1, simulated GN&amp;amp;C will be
demonstrated within a pico-satellite form factor using embedded software
such that a Technology Readiness Level (TRL) of 3 or 4 is achieved.
SMI has teamed with a leading thermoelectric (TE) research group in order to optimize and convert high-performance TE materials developed in laboratory-scale into economically producible products for NASA missions and commercial applications.  Recent results with nanocomposite films have shown that Figures of Merit (ZT) much greater than 1.0 are possible at laboratory-scale; however a technology road map with the view towards large-volume and low-cost manufacturing processes of such TE devices has not previously been envisioned. We propose to develop a scalable manufacturing process of large-volume and cost-effective nanocomposite TE device films with ZT values exceeding 2.0.  In Phase I, SMI and our partner will demonstrate a scalable manufacturing technology for nanocomposite films required for high-performance TE devices. In Phase II, we will continue materials development, device optimization, and process scaling to large-scale production.  Further, we will market the technology with end product producers.  The Phase III result will be the availability of high-performance TE devices that utilize nanocomposite films for NASA applications, commercial uses in general, and the new energy frontier of waste heat recovery.
Complex space systems such as lunar habitats generate huge amounts of data.   For example, the International Space Station (ISS) has over 250,000 individually identified pieces of low-level telemetry and commands.  Innovative algorithms for collecting and analyzing this data are leading to new technologies for managing large, complex and distributed systems.  Lunar habitats will have multiple interacting subsystems that govern their behavior and performance.  Assessing the health of the different subsystems and their effect on the overall system will be crucial to effective and safe control and operation of lunar habitats.  There are three complementary approaches to diagnosis, prognosis, and recovery: 1) model-based approaches that rely on a priori models of the systems; 2) data-driven approaches that mine sensor and command data using machine learning and statistical methods; and 3) procedure-driven approaches that perform system tests and branch on the results until a root cause is found and a recovery strategy executed.    We are proposing to build a comprehensive and integrated approach to fault diagnosis, prognosis and recovery that combines all three of these approaches emphasizing their strengths and negating their weaknesses.  The resulting system will monitor spacecraft systems, detect and diagnose failures and respond to mitigate those failures.
ASSURE - Aeroelastic / Aeroservoelastic (AE/ASE) Uncertainty and Reliability Engineering capability - is a set of probabilistic computer programs for isolating uncertainties in simulation, manufacturing, test, measurement, and test to analysis correlation affecting the AE/ASE characteristics of advanced flight vehicles in flight and on the ground, and for studying the effects of such uncertainties.  ASSURE will provide a quantitative assessment of the statistics of AE/ASE stability and dynamic response of aircraft at given flight conditions, throughout the flight envelope, on the runway, and throughout the aircraft fleet and its missions.  It is designed to have significant flexibility in the types of problems analyzed, the solution methods used, and how problems are defined.  ASSURE will be unique in the scope of problems tackled, systems complexity involved, and the inclusion of all elements affecting the ASE behavior of flight vehicles; including detailed models of structures, aerodynamics, sensors, actuators, control systems, landing gear, and flight operations and maintenance procedures.  Uncertainties of the undamaged and damaged / repaired systems (structural, actuator, sensor, control computer, and landing gear, including possible aerodynamic consequences of damage) will be covered, with applications to test planning and analysis, design, certification, and fleet operation and maintenance.
Balcones Technologies, LLC proposes to adapt actively controlled suspension technology developed by The University of Texas at Austin Center for Electromechanics (CEM) for high performance off-road vehicles to address STTR 2009-1 Subtopic T1.02, Information Technologies for Intelligent Planetary Robots.  In particular, our team will develop a concept design for an actively controlled ElectroMechanical Suspension (EMS) system, including algorithms, software and hardware, that dramatically improves mobility for MER to MSL scale rovers.  Our system exploits and adapts approximately $25M of highly successful active suspension R&amp;D at CEM since 1993.  It also exploits CEM's experience developing electromechanical systems for space applications gained during NASA funded programs to develop flywheel energy storage system technology for the International Space Station.  Finally, it exploits our team's extensive experience migrating University technology to commercially viable manufacturable products.  Relevant features of our anticipated solution include:
?	Capable of vehicle speeds exceeding 3 m/s over lunar relevant terrain while maintaining hyper-stability for payloads of 100 kg or more
?	Large suspension travel to enable obstacle negotiation 
?	Control system that can operate autonomously or slaved to higher level vehicle controller for specialized operations such as obstacle negotiation
?	Four quadrant actuator control, capable of power regeneration for damping operations to improve system efficiency
?	Passive springs to support rover static weight (no power consumption to support static weight)
?	Highly efficient electromechanical suspension actuators for each wheel station,  individually sized to support a high proportion of vehicle mass to enable obstacle negotiation
?	Modular control system, based on our highly successful control system for terrestrial manned and unmanned vehicles
?	Scalable technology for rover sizes representative of MER to MSL rovers
Impact Technologies, in collaboration with the Georgia Institute of Technology and its industrial partners, proposes to develop and demonstrate innovative technologies to integrate anomaly detection and failure prognosis algorithms into automated fault mitigation strategies for advanced aircraft controls. Traditional reactive fault tolerant control approaches fail to provide optimal fault mitigation over a long period of time to guarantee the integrity of the platform for the mission duration. We will create a generic simulation environment to demonstrate fault detection and progression at the component level, using electromechanical actuators as a testbench.  The proposed Anomaly Detection/Mitigation system accepts sensor inputs, extracts features from raw data and employs an anomaly detection module to determine the presence of an anomaly with performance guarantees; a prognostic routine, built on Bayesian estimation (particle filtering) techniques to estimate the remaining useful life of the component; finally, a mitigation strategy trades off between performance and control authority to extend the life of the failing component until the mission is completed. This innovative prognostics-enhanced approach to fault mitigation uses Model Predictive Control techniques running in real time. Core algorithms will be implemented on embedded systems and used in hardware-in-the-loop demonstrations.
Space Life and Physical Sciences Research and Applications Program
The proposed innovation is a scalable gravity off-load system that enables controlled integrated testing of  Surface System elements such as rovers, habitats, and space suits in planet-relevant gravity which addresses T6.02 in the direct solicitation of a gravity off-load system. Phase I delivers a nominal design in the form of a final report, Phase II builds this design and delivers hardware, and Phase III commercializes the gravity off-load system as a commercial product/service of Astrobotic Technology.
Liquid hydrogen is used extensively by NASA to support cryogenic rocket testing.  In addition, there are many commercial applications in which delivery and use of cryogenic hydrogen is more economical than gaseous hydrogen.  Unfortunately, loss of hydrogen resulting from boiloff can both increase the cost of the end product and create safety concerns.  Sustainable Innovations and its teammates, The University of Connecticut and FuelCell Energy, Inc., are developing a highly efficient Hydrogen Recovery System (HRS) based on an electrochemical process that converts cool, gaseous hydrogen to pure, high pressure hydrogen that can be stored for subsequent use.   We anticipate that this can bring significant cost savings to NASA's rocket test facilities, and open up exciting new avenues for product commercialization.
The innovation proposed here is a high performance, high fidelity simulation capability to enable accurate, fast and robust simulation of unsteady turbulent, reacting flows involving cryogenic propellants (such as LOX/LH2 and LOX/LCH4).  The key features of this proposed capability are: (a) Hybrid RANS-LES (HRLES) methodology, and (b) flamelet modeling for turbulent combustion incorporated in a proven existing solver called Loci-STREAM which has been developed by the proposing personnel under funding from NASA over the last several years.  The proposed enhancement in Loci-STREAM is anticipated to yield an order of magnitude improvement in simulation turnaround times relative to existing capability for turbulent reacting flow applications. The work proposed here will ultimately result in a state-of-the-art design and analysis tool to enable the accurate modeling of for multiphase combustion in solid and liquid rocket engines, combustion stability analysis, etc. which constitute critical components of versatile space propulsion engines part of NASA's deep space missions.
The constantly evolving science of nanotechnology keeps coming around to old ideas re-tooled with new technologies.  Though much work has been done examining the potential for nanotechnology to be used in ablative materials in a rocket nozzle, there have been relatively few testing opportunities of this application.  Carbon nanofiber (CNF) composites have been identified as a lightweight and effective material that could be used in rocket motor applications.  This technology when used in rocket nozzles could exhibit increased ablation resistance in the throat area and lower backside temperatures that would allow higher temperatures inside the nozzle.  This could translate into a nozzle lighter in mass and higher in durability than conventional ablative nozzles.  Benefits from this application could trickle across the board of high-temperature and dynamic pressure environments of different types of rocket motors.
The NASA Constellation program has a need to non-destructively test (NDT) non-metallic materials (foams, Shuttle Tile, Avcoat, etc) for defects such as delaminations and voids.  While imaging systems at terahertz frequencies (0.3 to 3 THz) have been demonstrated for 2D imaging of similar materials, they have not yet demonstrate full 3D volumetric imaging.  To meet this need, LongWave Photonics proposes to use high-power, low-frequency terahertz quantum cascade lasers (QCLs) developed at MIT, to demonstrate 3D imaging using Laser Triangulation.  By using high-power QCL sources, large signal to noise ratios (SNRs) are attainable, resulting in resolution of subtle defects at fast scan speeds.  The shorter wavelengths emitted by QCLs, 60 to 250 5m, allow high lateral and depth resolution.  The feasibility of a second system based on Swept-Source Optical Coherence Tomography will also be explored using a recently developed tunable THz QCL from MIT.  In addition to the benefits of high SNR, this technique allows sub-wavelength depth resolution.  The current generation of QCLs are compatible with a cooling package that is &lt;1 Kg, with &lt;100 W power consumption. Phase II work will package a second generation of QCLs in a compact system to meet NASA's portable 3D NDT needs.
ACTA and Sandia National Laboratories propose to quantify and propagate substructure modeling uncertainty for reduced-order substructure models to higher levels of system assembly, thereby enabling predictive simulations of engineering designs with quantified margins and uncertainties for model-based flight qualification of complete spacecraft.  A critical part of this process is the accurate modeling of interface structures, especially nonlinear interface structures that connect major substructures, and the quantification of their uncertainties.  By developing generic uncertainty models for reduced order models of specific substructures, NASA will be able to quantify margins and uncertainties for structural systems outside the domain of model validation tests.
The objective of this NASA STTR program is to develop single wall carbon nanotube (SWCNT) based ultracapacitors for energy storage devices (ESD) application, using NanoSonic's patented molecular level self-assembly process performed at room temperature. Specifically, we would combine advances in metallic SWCNTs, metal and oxide nanoclusters, and polymeric materials and electrostatic self-assembly (ESA) processes, to enable large-area, low-cost and integrated device manufacturing on rigid and flexible substrates. Such a combination of solution-based thin film deposition approaches to form ultracapacitor based devices and materials offers advantages over conventional high temperature and costly processes such as vacuum processes and vapour-phase deposition, in that very different materials can be incorporated uniformly at room temperature and pressure. We will perform synthesis of SWCNT and other precursors that can be used for ESA processing and transitioned to deposition of two-dimensional patterned materials.  Layer by Layer fabrication of multilayered CNT enhanced ultracapacitors leads to the analysis of chemical, physical and optical properties during and after synthesis, and verification of material morphology and response. We will study the cyclic voltammetric (CV) behavior and derive the power density from the inner integrated area. We will also investigate the specific capacitance as a function of discharge current density. From here, NanoSonic and Virginia Tech will develop an equivalent circuit model of the CNT ultracapacitor device for NASA applications. NanoSonic and Virginia Tech will also experimentally validate CNT ultracapacitor performance through extended field test evaluation, and possible testing with industrial partners, and produce first-generation ultracapacitors and energy storage systems for sale.
The ability to restore large amounts of vented gaseous helium (GHe) at rocket test sites preserves the GHe and reduces operating cost.  The used GHe is vented into the atmosphere, is non-recoverable, and costs NASA millions dollars per year.  Helium, which is non-renewable and irreplaceable once released into the atmosphere, is continuously consumed by rocket test facilities at NASA centers such as KSC, SSC, and CCAFS at a rate of more than 6.6 Mscf per year.  This use is projected to increase to more than 10 Mscf by the year 2018, assuming the same inefficient and costly operating procedures and facilities continue to be used.  Given the decrease in the world's supply of helium, NASA is heading toward to an economic, operational, and programmatic disaster.  New and highly innovative approaches are required to drive down launch operation life cycle costs.  Scaling-up of existing systems to meet an increased demand of helium is not an option.  Our team, Sierra Lobo, Inc. and University of Hawaii at Manao, proposes the use of PEM fuel cells to remove most of the impure oxygen and hydrogen in the helium gas stream.  The small traces of oxygen and hydrogen impurities in the GHe will be removed by cryo-separation using commercial cryocoolers.
Robots will play an important role in NASA's exploration activities over the next several decades.  They will land on the Lunar surface ahead of humans and help prepare for human exploration.  They will explore the Lunar surface, build structures and move regolith.  As humans arrive these robots will shift to assisting humans in exploration activities.  All of these activities require a new generation of robotic vehicles -- ones capable of flexible, dexterous manipulation -- that can work in closely coordinated teams.    This work focuses on coordinating the use of mobility and manipulator degrees of freedom to achieve a common manipulation purpose. We coordinate multiple mobile manipulators so as to achieve a common goal, such as grasping or manipulating an object so that it can be transported or mated.  The coordinated control architecture has four components: 1) motion planning for cooperative mechanisms; 2) task sequencing and monitoring; 3) coordinated control; and 4) operator interfaces for robot teams.  The architecture will be evaluated with respect to an assembly scenario implemented both in simulation and using several mobile manipulation robots.
Long-term exposure to microgravity and radiation during space exploration can pose a critical threat to the health of a flight crew. Real-time monitoring of urine protein levels is an effective way to follow the onset and progress of many diseases and guide the prompt selection of proper therapy. The success of such diagnostic tasks, which are vital for future space missions, critically depends upon the degree of automation, reusability and long-term lifetime of such trace level detection devices. To meet this need, this program will develop a novel on-chip, reagent-free, nano-plasmonic sensor cartridge to concurrently quantify the presence of different urine proteins. The envisioned device is compact, lightweight, fully integrated and automated, and highly cost- and power-effective. In Phase I, a new nano-plasmonics chip technology-based SPR sensor has been developed and successfully demonstrated for protein detection with excellent sensitivity. Critical microfluidic components, used in sample preparation, and adaptable to the sensor chip have been developed and validated by multi-physics-based simulations and modeling. In Phase II, the nano-plasmonic sensor will be optimized to increase sensitivity, stability, and the response to regular urine samples. The sensor chip will be integrated with the system-engineered microfluidics network to form a seamless urine protein assay cartridge (PAC) that enables automated surface modification, sample pretreatment, analyte detection and sensor regeneration for reuse. We will use modular design of the PAC that is compatible with existing NASA astrobiological instruments and will enable high-throughput proteome profiling analysis.
The challenges of designing, developing, and fielding man-rated propulsion systems continue to increase as NASA's Vision for Space Exploration Program moves beyond the Space Shuttle and RSRM.  The number and type of different propulsion elements required are significant, and predicting internal solid motor behavior and characteristics and assessing external environments (e.g., plume impingement on vehicle structures and launch acoustic loading) is a priority.  Our proposed innovation will enhance existing engineering software by combining new physical modeling capabilities with appropriate boundary conditions to create a novel toolset for complex multi-phase solid rocket analyses.  The innovation will be based on the Loci/Chem multi-physics analysis package and will utilize new Loci features, new multi-phase flow models, theoretical and phenomenological boundary conditions, and modified real gas equations of state to create a unique software tool for particle breakup, surface heat transfer with particle deposition, launch environment characterization, and nozzle erosion for next generation solid motors.  Our research products will provide NASA with the important capability to simultaneously analyze solid propellant combustion, heat transfer, launch acoustics, and nozzle erosion within a single unified numerical framework.  We will validate the approach using appropriate two phase flow problems to achieve a TRL range of 3-4.
The innovation proposed here is a complete, wireless remote sensing solution using passive SAW Orthogonal Frequency Coded (OFC) sensors and a wireless interrogation system. Prior to the Phase I activity, wireless, passive sensors which could operate in a multi-sensor environment had not been successfully demonstrated. This is no longer the case. An experimental transceiver test bed has been built in Phase I and wireless temperature sensing has been demonstrated. Using OFC sensors developed by the University of Central Florida (UCF), remote temperature sensing at distances of up to several feet at 250 MHz has been accomplished. Further, work on electrically small antennas (ESA) has demonstrated that antennas more commensurate with the sensor size can be achieved. A smaller sensor/antenna package yields a more flexible sensor solution. Using the results form Phase I, it is proposed that a prototype interrogator be built and operation demonstrated at 915 MHz in a multi-sensor environment.
The proposed innovation is to use the refrigerant capabilities of nitrous oxide (N2O) to provide the cooling required for reusable operation of an aerospike nozzle in conjunction with an N2O-HTPB (hydroxyl-terminated polybutadiene, a synthetic rubber that is used as a binder in solid rocket motors and as a fuel in hybrid rocket motors) hybrid rocket motor.  The phase change cooling as liquid N2O is flashed into a vapor is crucial to limiting to acceptable levels the erosion of both the nozzle throat and spike, thereby enabling reusable operation and/or long burn times.  The N2O used for cooling the nozzle throat will be reintroduced into the combustion chamber, and the N2O used for cooling the spike will be used to provide base bleed, virtually eliminating any performance penalty associated with using a severely truncated, and therefore significantly lighter, spike. Because of its high vapor pressure, N2O can be self-pumping, thereby making it an ideal choice of oxidizer for simple, low-cost applications. As a simple, practical nozzle, the proposed innovation fits well with N2O-HTPB hybrid rocket designs, which tend toward simpler, less expensive design alternatives.  Because of their high efficiency due to altitude compensation, aerospike nozzles could play an important role in bringing to fruition inexpensive access to low Earth orbit.  The simple, low-cost, reusable, oxidizer-cooled aerospike nozzle for operation on an N2O-HTPB hybrid rocket motor that is proposed will enable much-needed flight research of aerospike nozzles.  These oxidizer-cooled altitude-compensating nozzles promise significant improvements in propulsion efficiency for a wide range of space vehicles and tactical missiles.
The purity of hydrogen fuel is important in engine testing at SSC. The hydrogen may become contaminated with nitrogen, argon, helium or oxygen. The hydrogen from the fuel tank  s or feed lines is analyzed beforehand. Therefore, there is a need for a non-intrusive, on-line, near real-time monitor for H2. The analytical technique should measure various impurities (molecular and atomic) simultaneously and be easy to implement in the field. The objective of this proposed research is to develop an analytical technique based on Laser Induced Breakdown Spectroscopy (LIBS) to measure simultaneously the concentrations of nitrogen (N2), argon (Ar), Helium (He) and oxygen (O2) contaminants in hydrogen (H2) gas storage tanks and supply lines. Advanced sensors for monitoring multiple species in H2 feed-lines and storage tanks will be useful before engine testing and will increase understanding of engine performance. Phase I has provided necessary information to build a sensitive, compact, sturdy, user-friendly and fieldable prototype in Phase II, with ease of implementation at NASA/SSC. In Phase II, a prototype LIBS system will be designed and fabricated to measure impurities in H2 fuel at different places in the H2 feed line. This integrated system will be delivered to NASA/SSC at the end of Phase II.
A prototype wearable smart reconfigurable antenna for the Suit will be built to be used during NASA's EVA operations on lunar surface. The design is based on the Self-Structuring Antenna (SSA) technology utilizing MEMS switches for configuration of the aperture. Electrothermally and electrostatically actuated MEMS were studied via modeling and experiments and electrostatically actuated switches were recommended for use in Phase II due to their low actuation power requirements. The proposed smart antenna offers both adaptive beam steering and MIMO options for increasing the signal to noise ratio (SNR) and extending range. The antenna provides enhanced RF link for surface-to-surface voice, data, and video communication while also supporting contingency voice communication with the Lunar Relay Satellites (LRS). The technology is expected to reach TRL of 6 at the end of Phase II.
Wireless, passive, Surface Acoustic Wave (SAW) temperature sensors, which can operate in a multi-sensor environment, have recently been successfully demonstrated. A network of four (4) Orthogonal Frequency Coded (OFC) sensors developed at the University of Central Florida (UCF) has been successfully interrogated wirelessly at a distance of seven (7) feet with a transceiver system developed by Mnemonics, Inc (MNI).
In Sub-topic T8.02, NASA has identified a need for improved circuit boards to mitigate the hazards of internal electrostatic discharge (IESD) on missions where high energy electrons may lead to internal electrostatic discharge-based failure.  The proposed STTR program will transition polymer technology developed at the Research Institution, the College of William and Mary, to NASA programs and to the private sector through the aegis of the Small Business, International Scientific Technologies, Inc.  The program Technical Objectives include evaluation and selection of nanoparticle, organometallic, and metal-ligand additives compatible with polyimide resins to produce electrically  conductive circuit boards that reduce the effects of  IESD, fabrication of polyimide films incorporating metallic nanostructures to optimize both volume and surface electrical resistivities, and characterization of electrical conductivity, electron beam charging effects, and thermo-mechanical properties of the polyimide resin circuit board materials.  The innovation of the Phase I and Phase II programs is the development of polyimide nanocomposite circuit board materials that are resistant to Internal Electrostatic Discharge.  The Technology Readiness Level (TRL) is 2 at the beginning of Phase I and 4 or higher at the end of Phase I.
NASA has identified a critical need for pioneering advances in battery technology to give high performance, low-weight, durable and long-life power sources for future missions. In this Phase I proposal, CFX Battery, Inc. and Georgia Institute of Technology propose the chemical conversion of micron-sized, nano-structured templates available from renewable resources into functional electrode materials. In nature, diatom species form complex cell wall structures made of silica through biological self-assembly. We will take advantage of these intricate structures to generate hierarchically-ordered functional nanocrystalline oxide architectures, and investigate the application of these materials in electrochemical devices. We intend to establish that electrodes fabricated from these nanostructures are innovative materials that display improved electrochemical performance compared to traditional electrodes. This will enable us to address the significant increases in energy capacity, power capability and cycling stability necessary to meet the NASA requirements for advanced Li-ion battery technology. Our manufacturing strategy is conceptually-straightforward, rapid, scalable and amenable to commercialization.
Computational tools that accurately predict the performance of electric propulsion devices are highly desirable by NASA and the broader electric propulsion community. Large investments in running the long duration test programs (&gt; 20 kHrs) at NASA GRC can be reduced with computer models and allow more focus on exploring the NEXT ion thruster design for future space missions. The current state of electric propulsion modeling relies
heavily on empirical data ? frequently taken directly from the device of interest ? and relies on numerous computational "knobs". A self-consistent particle model that minimizes the number of free parameters used in thruster modeling, and allows accurate electric thruster
simulations is desired. We propose a kinetic model that simulates the dynamic electric fields inside the NEXT ion thruster discharge chamber plasma. This will be the first time that this has been done. In addition kinetic erosion models will be used for modeling the ionimpingement
effects on thruster components. We envision one seamless model of the plasma from emission within the hollow cathode to ejection to outer space in the exhaust plume. This model will help NASA GRC to predict the lifetime operation of the high power ion propulsion options for earth-orbital applications.
Firefly, in collaboration with Rochester Institute of Technology, proposes an STTR program for the development of a wide-bandgap GaP-based space solar cell capable of efficient operation at temperatures above 300oC. Efficiency enhancement will be achieved by the introduction of InGaP quantum wells within the active region of the wide-gap base material. The introduction of these nanoscale features will enable harvesting of low-energy photons that are normally lost by transmission through the wide bandgap material. 

Successful completion of the proposed work will combine the high-temperature, radiation-tolerant wide-bandgap material with current-enhancing nanostructures to produce a high efficiency space solar cell capable of operating at higher temperatures suitable for near-sun missions. This achievement can result in significant cost savings as active cooling of PV systems would be unnecessary with this technology.
Current autonomous rendezvous and docking (AR&amp;D) capability in low Earth orbit (LEO) is constrained by sensor and effector mass, power, and accuracy limits. To this end, NASA Johnson Space Center has developed a GPS receiver, called DRAGON (Dual RF Astrodynamic GPS Orbital Navigator), specifically to address the sensor constraints. The proposed innovation includes creating a small, low-cost, and versatile technology demonstrator to validate and increase the technology readiness level of DRAGON and other state-of-the-art miniaturized sensors and effectors in an on-orbit AR&amp;D operational scenario. For Phase 1, a demonstration platform was developed that utilizes two picosatellites in LEO, and relative GPS as the primary sensor. These satellites were launched as a single unit from the SSPL (Space Shuttle Payload Launcher) on STS 127, to separate and transmit DRAGON data. The picosatellite technology demonstrator was at a TRL of 7 at the end of Phase 1. For Phase 2, NASA plans a second flight, and the technical objectives are to further characterize the DRAGON receiver and develop navigational solutions using DRAGON data. Additional technologies addressed include the development of a simple low-cost, low-mass three-axis stabilization and pointing system for small satellites, WiMax transceiver capabilities, and video camera capabilities. The technologies should be at a TRL of 6 at the end of Phase 2.
Currently used cathode materials in energy storage devices do not fully satisfy the power density and energy density requirements for NASA's exploration missions. Working in collaboration with our STTR partner at University of California ? San Diego, we propose to develop layered-layered composite cathode materials that offer superior performance over commercially available positive electrode materials such as, LiCoO2, or LiNi1-xCoxO2.
Space policy direction is shifting, particularly with respect to human goals.  Given the uncertainty of future missions to the moon, Mars, and other bodies, a tool that allows for informed analysis of the option space is particularly relevant.  Aurora Flight Sciences and MIT propose to further develop the Multi-Robot Planetary Exploration Architecture (MRPEA) methodology, a suite of software tools and analysis algorithms developed to provide decision aides to architecture planners of planetary surface exploration missions.  MRPEA provides 1. A logical and graphical representation of the system space (e.g. interrelated decision variables with constraints), 2. Structural reasoning for rapid exploration of architectural spaces, 3. Simulation, and 4. Results viewing for a set of feasible architectures.  Given the robots available or predicted to be available, the expected duration, and the mission goals, our methodology provides analysis results such as knowledge benefit-vs.-mass Pareto front graphs, to allow the designers to provide the best possible architecture for the planned mission or missions.  The MRPEA analysis methodology primarily addresses the planning requirements of planetary surface missions, providing useful analyses of the many elements of the architectural decision space; in addition, the principles and techniques developed to analyze and select multi-robot architectures on planetary surfaces can also be applied to future fractional satellite systems, an area of increasing interest.
3D visualization has proven effective at orienting remote ground controllers about robots operating on a planetary surface.  Using such displays, controllers can watch a robot move through surface terrain maps and react to objects in that terrain.  Readings taken in the robot's surroundings can be overlaid on terrain maps to improve human understanding.  3D visualization, however, focuses a controller's attention on what is happening in the vicinity of the robot.  The effectiveness of visualization at centering attention on the robot means that information not spatially linked to that view could be missed.  TRACLabs, Carnegie Mellon University, and Stinger Ghaffarian Technologies propose to develop software for notifying users of 3D visualization about important new information that may not be spatially linked to the current view.  We will identify use cases where notification is needed when using 3D visualization and design software for constructing and presenting notices for these use cases.  We will evaluate this design for use in K10 rover operations by defining an approach for integrating notification with the Visual Environment for Remote Virtual Exploration (VERVE). The extensive experience of this team in developing advanced software for robotic surface operations will contribute to the timely delivery of the proposed technology.
ProtoInnovations, LLC and Carnegie Mellon University have formed a partnership to commercially develop rover-autonomy technologies into Reliable Autonomous Surface Mobility (RASM).  Our aim is to provide safe and reliable means for lunar rovers to travel at substantial speeds and operate in proximity to astronauts and other vehicles.  Our unique partnership brings together state-of-art technologies for autonomous rover navigation with experience in delivering and supporting mobility systems for NASA.

The RASM project will create an autonomy framework that is capable of supporting off-road vehicle speeds beyond 3 m/s with planetary-relevant constraints including a lack of infrastructure (such as GPS) and limited communication and computing resources. Our RASM framework is based on environment modeling, obstacle avoidance, path planning, and localization algorithms developed by Carnegie Mellon and proven by hundreds of kilometers of traverse in planetary analog landscapes on Earth.

On the RASM project we will mature and package these algorithms in a reliable and portable software architecture that supports a variety of vehicle platforms, sensors, and middleware alternatives. Unique to RASM will be a failure-modes analysis of the autonomy system to model and mitigate hazards posed by operating alongside astronauts and lunar vehicles.

Mission constraints and operating scenarios will vary broadly, so RASM will be adaptable. We will develop abstraction layers to enable portability across various vehicle chassis configurations, perception sensors, localization sensors, and communications protocols. In Phase 1 of our project, we will demonstrate the ease with which RASM can be ported by implementing it on a rover such as the Lunar All-Terrain Utility Vehicle (LATUV) developed by ProtoInnovations. Our goal is to advance autonomy-system TRL from 4 to 6 on the contract.
The purpose of this project is to advance the technology of interband cascade (IC) lasers and their facet coatings and to design, build, and deliver to NASA a tunable, narrow linewidth mid-infrared laser source operating in the 3.2 !V 3.6 micron wavelength band. Initial work will develop improved IC laser active regions as well as ultra-low-reflectivity anti-reflection facet coatings. We will also develop an effective epi-side-down die attach process for IC lasers using a Au/Sn solder. The objective of this initial work is to achieve laser chips emitting in the appropriate wavelength region and operating in continuous wave mode at heat sink temperatures &gt; 25aC and with several 10s of mW of output power. The team will then use our extensive experience with external cavity laser sources to design, build, and deliver a versatile, tunable mid-infrared source to NASA using the developed IC laser gain chip. The delivered tunable laser source will be at a TRL level of 5 and will enable sensitive earth science trace gas measurements and enhance NASA!&s existing measurement capability by significantly improving the sensitivity and performance of trace gas sensing by virtue of a considerably improved source technology.
In the phase II effort, Intelligent Automation Inc., (IAI) and University of Central Florida (UCF) propose to develop a comprehensive numerical test suite for benchmarking current and future high performance computing activities that will include: (1) dense and unsymmetrical matrix problems faced in space aviation and problems in thermally driven structural response and radiation exchange, (2) implicit solution algorithms with production models and benchmarks for indefinite matrices and pathological cases, (3) configurations scaling for large systems in shared, distributed and mixed memory conditions, (4) documentation for strengths, weaknesses, and limitations of the toolkits used together with recommendations and (5) precision and round-off studies on serial and parallel machines, comparison of solutions on serial and parallel hardware with study of wall clock performance with respect to the number of processors 
We successfully demonstrated in phase I that we can accurately and precisely benchmark run time solvers of dense complex matrices in hybrid-distributed memory architecture.  We achieved highly scalable super-linear speed-up and scalability of the algorithm for large problem sizes. The tools developed in phase II will greatly improve the performance and efficiency to adapt the benchmarks to HPC systems different hardware architectures at NASA facilities and for non-NASA commercial applications.
Instabilities associated with the operation of liquid rocket propulsion systems and test facilities usually manifest themselves as structural vibrations and may cause structural damage. While the source of the instability is directly related to the performance of a component such as a turbopump, the associated pressure fluctuations as they propagate through the system have the potential to amplify and resonate with natural modes of the system.
NASA's exploration and scientific missions will produce terabytes of information. As NASA enters a new phase of space exploration, managing large amounts of scientific and operational data will become even more challenging.  Robots conducting planetary exploration will produce data for selection and preparation of exploration sites. Robots and space probes will collect scientific data to improve understanding of the solar system.  Satellites in low Earth orbit will collect data for monitoring changes in the Earth's atmosphere and surface environment. Key challenges for all these missions are understanding and summarizing what data have been collected and using this knowledge to improve data access.  TRACLabs and CMU propose to develop context aware image manipulation software for managing data collected remotely during NASA missions. This software will filter and search large image archives using the temporal and spatial characteristics of images, and the robotic, instrument, and environmental conditions when images were taken. It also will implement techniques for finding which images show a terrain feature specified by the user. In Phase II we will implement this software and evaluate its effectiveness for NASA missions.  At the end of Phase II, context aware image manipulation software at TRL 5-6 will be delivered to NASA.
The proposed innovation is an aircraft flight envelope monitoring system that will provide real-time in-cockpit estimations of aircraft flight envelope boundaries.  The adaptable system will provide information on current and predicted aircraft performance and controllability, alerting the pilot to any aerodynamic degradation of the aircraft control surfaces.  This includes heavy rain, in-flight icing encounters, environmental contamination of surfaces, and structural damage such as bird strikes or battle damage.  The real-time monitoring system measures the unsteady control surface hinge moment from all aircraft aerodynamic controls.  Control surface hinge moments are sensitive to the aerodynamics of the section, including separation.  These data are processed and information on the current and predicted future state of aircraft performance and control (including asymmetric cases) is made available to the pilot or flight management system.  Phase I results have shown that the hinge moment sensor concept is a viable technology for the monitoring and prediction of airfoil stall.  The hinge moment monitoring system was able to provide reliable stall warning and prediction across an incredibly wide range of simulated aerodynamic hazards.  The proposed aircraft flight envelope monitoring system is an integral part of an overall integrated vehicle health management system.
This proposal addresses methods for efficient quantification of margins and uncertainties (QMU) for models that couple multiple, large-scale commercial or proprietary simulation codes, effective methods for treating epistemic uncertainty in large scale simulations, scalability to models with hundreds or thousands of uncertain parameters, and competition with traditional Monte Carlo Based methods. The Reduced-Order Clustering Uncertainty Quantification (ROCUQ) methodology described in this proposal has been under development over the past several years at the University of Illinois, and is being commercialized by IllinoisRocstar LLC. ROCUQ uses a combination of common stratified Monte Carlo techniques, coupled with well-chosen reduced order models, statistical clustering, and a few (less than tens) high-fidelity simulation runs to provide estimates of the uncertainty distributions for the System Response Quantities (SRQs) of interest to the modelers. The goal of the ROCUQ methodology is to minimize the number of high-fidelity, computationally-intensive simulation runs that are needed in order to provide estimates of output uncertainties of interest, especially when it is not possible to run the high-fidelity model more than a few (e.g., 5 to 10) times. ROCUQ has been, or is currently being applied to solid propellant rocket internal ballistics uncertainties, coupled fluid-structure interaction modeling of stresses in an Air Force Training Fighter wing, and structural dynamics/vibration of a specially-designed experimental apparatus for studying simulation validation under uncertainty.
An efficient and accurate software package named ZMGP (ZONA Multi-scale Gaskinetic/Particle simulation package) is proposed as a 3D tool to predict the lunar dust trajectory and crater formation process when a retro-rocket lands on the lunar surface. ZMGP has many special features including: 1, the hybrid flow module by coupling the gaskinetic Bhatnagar-Gross-Krook (BGK) model and the direct simulation Monte Carlo (DSMC) method (BGK/DSMC) to efficiently compute the rarefied flowfield; 2, by divi
IFOS and its research institute collaborator, Washington State University (WSU), have demonstrated feasibility of a structural health monitoring (SHM) system for aerospace vehicles such as Unmanned Aerial Vehicles (UAVs) or commercial airliners. In Phase 1, a unique high-speed, high-channel count fiber Bragg grating (FBG) sensor interrogation system enabling a new Lamb wave-based damage detection method was demonstrated. This SHM system allows accurate detection of damage in rectangular composite plates simultaneously collected from a plurality of strategically placed FBG sensors using  relatively few piezo actuators. Utilization of structurally integrated, distributed sensors to monitor the health of a structure allows for high-speed collection and interpretation of sensor signals, coupled with real-time data processing. The proposed system provides automated diagnosis and prognosis capabilities, greatly reducing the overall inspection burden. Phase 2 is designed to advance the technology towards specific NASA flight research testbed platforms, particularly Ikhana. During Phase 2, IFOS will collaborate with prime system contractors to address challenges and risks associated with the intended operational environment, including (a) generation of a complete flight worthy design, (b) performance enhancement and ruggedization of the interrogator and sensors, (c) optimization of damage detection algorithms and their implementation, and (d) total system performance validation and evaluation.
The Keystone and MSU team propose to build on the successful feasibility demonstration conducted during Phase I to complete the development of solid-state joining of high strength and temperature alloys utilizing the Thermal Stir Welding process. The focus alloy for this project is Haynes 230; the alloy of choice typically utilized in rocket engine nozzel skirts. This class of alloy is difficult to fusion weld and with the successful Phase I demonstratipon has now been shown weldable using solid-state methods. Therefore, the Keystone team is proposing to utilize a Thermal Stir Welding process; a solid-state welding process that decouples the stirring and heating features of the process to enable optimization of each key process parameter. By independently controlling and optimizing these process parameters, the best metal working parameters can be established and utilized to plasticize and stir the Hanyes 230 alloy. Achievement of this objective will enable superior mechanical properties in the weld joint and thus maximize the capability of the weld for the intended application. During Phase II the Keystone team will complete process development and demonstrate TRL-4 readiness by producing a 24" diameter subscale nozzel skirt for testing and evaluation by NASA.
Pico-satellites are an emerging new class of spacecraft. Maneuverable pico-satellites require active guidance, navigation, and control (GN&amp;C) systems to perform coordinated tasks such as formation flying and automated rendezvous and docking.
Radioisotope Power Systems (RPS) are critical for future space and planetary exploration missions. Small improvements in the RPS performance, weight, size, and/or reliability can have a dramatic effect on the scientific capability of the vehicle and the overall mission costs.
The innovation proposed here is a high-performance, high-fidelity framework in the computational fluid dynamics (CFD) code called Loci-STREAM to enable accurate, fast and robust simulations of unsteady multiphase flows such as combustion involving liquid-gas phases in liquid rocket injectors and solid-gas phases in solid rocket motors, and cryogenic cavitation in delivery systems of liquid rocket engines.  This framework will provide a state-of-the-art multiphase unsteady turbulent flow simulation capability employing Hybrid RANS-LES (HRLES) methods which are a blend of Reynolds Averaged Navier-Stokes (RANS) and Large Eddy Simulation (LES) approaches.  Robust primary atomization models for liquid jet breakup and both phenomenological and stochastic secondary droplet breakup models will be developed.  Lagrangian particle tracking and Eulerian multiphase models will be coupled to enable simulation of multiphase combustion involving solid particles or liquid droplets.  The work proposed here will result in a state-of-the-art design and analysis tool to enable the accurate modeling of: (a) multiphase combustion in solid and liquid rocket engines, (b) combustion stability analysis (c) acoustic fields of space propulsion systems in near-ground operation, (d) small valves and turbopumps, etc. which constitute critical components of versatile space propulsion engines part of NASA's space near- and long-term space programs.
Multidisciplinary design, analysis, and optimization (MDAO) tools today possess limited disciplines with little fidelity modeling capability.  These tools are typically developed as a single large software application that performs analysis for all disciplines but has little or no capability to integrate multi-fidelity and multi-discipline components that have already been developed as stand-alone analysis codes.  Even though a multitude of tools have been developed and well adapted to the interdisciplinary aircraft design/analysis, they have not been developed to work together.
The objective of the development of the MDAO tool is to generate a "central executive" that can integrate disparate software packages in a cross platform network environment so as to perform optimization and design tasks in a cohesive streamlined manner.  This object-oriented framework can integrate the analysis codes for multiple disciplines, instead of relying on one code to perform the analysis for all disciplines.
ZONA Technology and its team member Virginia Polytechnic Institute propose to develop three object-oriented components that will fully leverage tools currently under development within NASA's MDAO framework.  The three major components are:
(1) an automatic re-meshing tool that can provide a fast and efficient mesh generation capability for complex structures like curved panels with curved stiffeners and aircraft wings of any shape with curved spars and ribs. 
(2) a hybrid optimization tool that combines a non-gradient based optimization method and a gradient based optimization method.  The advantage of this hybrid optimization is that a global optimum point can be achieved through the non-gradient optimization and acceleration of the convergence can be obtained by aiding gradient based optimization algorithm.
(3) a fast transonic unsteady aerodynamics method for accurate aeroelastic analysis and shape sensitivity information due to the change of external wing shape.
In providing an innovative solution to improving information technologies and health management systems, AGNC is proposing a significant technological achievement with the Advanced Structural Health Monitoring System for Comprehensive Real-Time Vehicle Characterization. During in-flight conditions, this system is able to not only provide the status of information such as regarding the flight envelope, but also make accurate diagnostic and prognostic statements of aircraft subsystems. Real-time capabilities are enabled using intelligent algorithms and advanced techniques to provide both time and frequency localization of data. As such, the health management system is able to provide information quickly enough as to monitor an aircraft subsystem in a highly dynamic environment and to make statements regarding anomalies as well as future problems. A key enabling technology is newly developed low-power sensors that offer significant advantages over traditional sensor methods. In addition, automated reasoning technologies to improve sustainability, increase identification of system degradation, and enhance scientific understanding include data fusion, and advanced decision-making, among others. With this system, a comprehensive image of the system/subsystems, and in particular, the structural components, is provided in real-time.
Scientic, Inc. and Vanderbilt University propose to dramatically improve the performance of ultracapacitors to address several applications within NASA. As power-supply components, ultracapacitors provide extremely high power densities, fast recharging rates, and long cycle life; when used in tandem with batteries, they can greatly extend battery life. We note that ultracapacitors can assume almost any form factor that an application might require. Our recent success with a flexible substrate supports this claim. Finally, commercialization of our ultracapacitor will rely on the use of environmentally friendly materials and well understood industrial manufacturing processes in common use today.

We propose to develop a novel hybrid electrochemical ultracapacitor which will combine desirable attributes such as extremely high energy-power density, excellent life-cycle reliability and safety characteristics, with low production cost and have the potential for widespread deployment in energy delivery/storage applications for the NASA.  In this innovative, hybrid, demonstrated approach we will grow vertically-aligned carbon nanotubes (CNT) directly on conducting flexible substrates to reduce contact resistances, and we will exploit the more controllable CNT nano-architectures for optimum attachment of inexpensive pseudocapacitive manganese-dioxide (MnO2) nanoparticles to enhance charge efficiency and energy-power capacity.  Our approach employs "green" electrolyte that increases cell voltage.
This Small Business Technology Transfer Phase 2 effort focuses on development of a supercapacitor energy storage device based on novel metal oxide-carbon nanocomposites. In the Phase 1 project, NanoScale discovered a group of cathode nanocomposites with an exceptionally high capacitance of 270 F/g and a large potential window of 3.
The work will focus on the 3D implementation of the Phase 1 CHARM mesher, with solution-adaptive iteration for CFD and non-CFD applications. The proposed 3D method will incorporate and extend a previously developed method of generating field-guided hexahedral elements from a metric tensor field. While the fundamental technical approach ? a combination of metric tensor conditioning, metric-tracing mesher, and cell-packing mesher ? remains the same, there are many technical challenges specific to the 3D domain, including the following:

 - Investigation into conditioning of volume metric tensor fields
 - Investigation into the topology (structure) of volume metric tensor fields
 - Developing algorithms for the generation, repair, and adjustment of streamsurface arrangements
 - Developing algorithms to convert streamsurface arrangements to hex-dominant meshes
 - Developing algorithms to combine streamsurface- and packing-based meshes
 - Investigation into designing these algorithms for mesh adaptation rather than adaptive remeshing
 - Investigation of time and storage efficiency of these algorithms in a large-scale parallelism context

In addition to the above, the goal is to generalize the solution in order to support its packaging and commercialization for a number of problem sets and target applications. This includes generalization of the solver-adaptive framework, creation of APIs to programatically expose core functions, and provide UI access to appropriately control and configure the application.
ProtoInnovations, LLC and Carnegie Mellon University have formed a partnership to commercially develop rover-autonomy technologies into Reliable Autonomous Surface Mobility (RASM). Our aim is to provide safe and reliable means for lunar rovers to travel at substantial speeds and operate in proximity to astronauts and other vehicles.
Propagation of parameter uncertainties through large computer models can be very resource intensive. Frameworks and tools for uncertainty quantification are generally geared to individual codes, are research codes, or are single-purpose tools such as LHS matrix generators. The Reduced-Order-Clustering-Uncertainty-Quantification (ROCUQ) methodology discussed in this proposal is specifically designed to circumvent many of the issues associated with uncertainty quantification of large simulation codes. The ROCUQ methodology has been applied in several different physical disciplines with good results. The computational methodology is a combination of reduced-order modeling, stratified sampling (Latin Hypercube Sampling ? LHS), statistical clustering of results (K-means clustering) and a few (five to ten) full-physics runs of the high-fidelity model under investigation. The method should be applicable to hundreds of uncertain variables when required. ROCUQ enables estimates of system response quantities (SRQ) uncertainty distributions for situations where it is not feasible to use purely sampling, collocation, or other techniques where many runs would be required. For some organizations, uncertainty analysis has never been possible due to resource limitations, and thus is not part of the organizational culture. Many analysts know that uncertainties can be important, but have no way to expend sufficient resources (money, CPU cycles, time) to do the work needed to quantify uncertainties. A methodology such as ROCUQ promises to open doors in organizations that know that they have the need, and may now be able to actually perform the analyses. Successful completion of the Phase II project will produce not only new software that will be able to be used by researchers and industry, but will assemble insights on the use of reduced order models in a variety of disciplines, and provide guidance and rules for the use of ROCUQ for the estimation of SRQ uncertainty distributions.
The NASA application requires a system that can generate 3D images of non-metallic material when access is limited to one side of the material. The objective of this proposal is to demonstrate the feasibility of developing and build a new, practical, potentially portable, battery operated, self-contained Compton x-ray backscatter 3D imaging system by using a specially designed automated rotationally movable x-ray source, a 2D x-ray detector with a highly collimator system and the development of a suitable 3D processing computer model. In the proposed x-ray imaging system, the primary technical advance will be to extend methods that normally supply a 2D projected image through a sheet of material, to a 3D image with more complicated features at different depths, such as voids, cracks, corrosion or delaminations. The portability of the proposed imaging system will allow bringing it to the object to be imaged. Phase 2 will be conducted with a focus on technology transition and an understanding of what it will take to demonstrate and qualify the proposed method in a prototype for use in an actual imaging system and a realistic environment. Also in Phase II, time reduction in setup, data image acquisition, and 3D-image reconstruction analysis will be realized by remote automated control of the operation and movement of a brighter x-ray source and a state-of-the-art digital flat panel detector in conjunction with a highly  collimator system.
The proposed effort will develop a solid-state LED replacement lamp for rocket engine test stand lighting and more general hazardous-location lighting.  The LED lighting will produce a smoother lighting spectrum compared to the existing arc lamp sources which will improve the visual accuracy and quality of high-speed engine photography.  The LED lighting will also last significantly longer than arc lamps which require frequent replacement in hazardous-gas environment.  A specialized array of optical collectors will redirect the light more effectively to the needed test areas using principles on non-imaging optics.  The result will be improved lighting for engine diagnostics, lower operating costs for the test stand, much longer lamp life and a safer environment by reducing or eliminating lighting maintenance operations in an explosive environment.  

The housing will also be shock, vibration and heat resistant to be able to withstand the proximate effects of live-fire rocket engine testing.  The electronic controls for the lighting will be sited remotely from the lamp head to be consistent with the existing facility and for thermal and reliability considerations. Additionally, a hazardous-location LED lighting device for general illumination which is not for high-speed engine diagnostics will also be developed and tested.
GHe reclamation is critical in reducing operating costs at rocket engine test facilities.  Increases in cost and shortages of helium will dramatically impact testing of rocket engines for launch vehicles and space propulsion systems as the global supply of this non-renewable element diminishes.  Extremely large quantities of helium are being used during rocket engine testing each year at various test facilities.  It is critical for program successes to minimize developmental and testing costs by reclaiming helium utilized in those programs and, equally important, to preserve this rare element for future generations.  Phase I innovative solution efforts have proven the effectiveness of utilizing hydrogen (H2) Proton Exchange Membrane Electrochemical Cell (PEMEC) technology to purify an inert gas stream of helium (He) consisting of hydrogen contaminants in a cost-effective manner.  This method allows in-situ, on-site helium re-utilization, returning the helium to cleanliness standards required for rocket engine test facility use.  Phase I identified the challenges for dilute hydrogen operation of the PEMEC and provided viable solutions for improved efficiency, which allows the PEMEC's to provide high purity, 99.995&#37; helium.  Phase I also identified a possible configuration in which the exit stream of H2 can be added to a fuel cell operating in the galvanic mode to provide power back to the GHe reclamation system. Although Phase II efforts will not utilize that configuration, Phase I verified its feasibility and future system growth potential.  Phase II efforts will build upon all the results of Phase I to deliver a fully functional prototype system for further evaluation in an operational environment.  Technology Readiness Level (TRL) at the end of Phase I was five (5), while phase II will progress that level to six (6): System/subsystem model or prototype demonstration in a relevant environment.
Future NASA exploration missions will rely on remote operation of robots. As human explorers move further away from Earth, robotic precursors will scout destinations and robotic assistants will perform tasks to reduce astronaut risk and workload. 3D visualization is a key component of how humans will interact with robots for these missions. When the operator engages a robot using visualization, there is a risk that he or she will become too focused on what is happening now in the vicinity of the robot and will not be aware of other important events that are not apparent in the field of view. This risk only increases when operations involve multiple robots. It is essential to ensure that the user does not miss important events that do not manifest in the vicinity of the robot. TRACLabs, Carnegie Mellon University (CMU), and Stinger Ghaffarian Technologies (SGT) propose to develop software for notifying users of 3D visualization about important notices without distracting users unnecessarily or adding to the visual clutter around the robot avatar. This software will monitor events from the robot or user, identify which events should be brought to the user's attention, and alert users in the 3D pane. The appearance of alerts is altered to shift a user's attention to new notices based on an assessment of the importance and urgency of the notice specific to the user. Thus the same notice may be presented to different users in different ways. Because notices are anchored to a screen overlay, they are visible regardless of what location the user is viewing in the 3D space. In Phase II we will implement this software and evaluate its effectiveness for NASA missions.
Rocket test operations at NASA Stennis Space Center (SSC) result in substantial quantities of hydrogen gas that is flared from the facility and helium gas that is vented.  One way to save on the cost of test operations is to recover these gases using an electrochemical system.  This Hydrogen Recovery System (HRS) selectively removes hydrogen from the mixed stream, leaving behind high-value helium.  The system then removes residual water vapor from this helium and compresses it to commercial storage pressure.  The heart of the HRS is a system platform under commercial development by Sustainable Innovations, termed H2RENEW&lt;SUP&gt;TM&lt;/SUP&gt;, an electrochemical system package that separates and compresses hydrogen using Proton Exchange Membrane (PEM) technology.  The system being developed in this Phase II STTR program targets a hydrogen removal rate of 1.77 scfm, an outlet hydrogen pressure of 200 psi, and a product helium pressure of 2,000  2,500 psi.  This system leverages a robust novel Expandable Modular Architecture (EMA) electrochemical cell stack that is capable of being constructed with a very large production capacity and high operating pressure.
Advances in high power, photovoltaic technology has enabled the possibility of reasonably sized, high specific power, high power, solar arrays.  At high specific powers, power levels ranging from 50 to several hundred kW are feasible.  Coupled with gridded ion thruster technology, this power technology can be mission enabling for a wide range of missions ranging from ambitious near Earth NASA missions to those missions involving other customers as well such as DOD and commercial satellite interests.  Indeed the HEFT clearly identified the need for high power electric.  The appeal of the ion thrusters for such applications stems from their overall high efficiency, typically &gt;70&#37; and long life.  In response to the need for a single, high powered engine to fill the gulf between the 7 kW NEXT system and a notional 25 kW engine, a Phase I activity to build a 25 kW, 50 cm ion thruster discharge chamber was completed with a laboratory model fabricated. The proposed Phase II effort aims to mature the laboratory model into a proto-engineering model ion thruster.  The proposed effort involves the evolution of the discharge chamber to a high performance thruster by performance testing and characterization via simulated and full beam extraction testing. Through such testing the design will be optimized leading ultimately to the proposed design, build and preliminary checkout of a proto-engineering model thruster, thereby advancing the TRL level to 4-5 range.  Deliverables include the thruster, a design package, and a performance data document.
Computational tools that accurately predict the performance of electric propulsion
devices are highly desirable and beneficial to NASA and the broader electric propulsion
community. The current state-of-the-art in electric propulsion modeling relies heavily on
empirical data and on numerous computational "knobs". In Phase I of this project, we
developed the most detailed ion engine discharge chamber model that currently exists.
This is a kinetic model that simulates all particles in the discharge chamber along with a
physically correct simulation of the electric fields. In addition, kinetic erosion models are
included for modeling the ion-impingement effects on thruster component erosion. For
Phase II of this project, the goal is to make this sophisticated computer program a user
friendly program that NASA and other governmental and industrial customers are able to
utilize. In Phase II we will implement a number of advanced numerical routines to bring
the computational time down to a commercially acceptable level. At the end of Phase II,
NASA will have a highly sophisticated, user friendly ion engine discharge chamber
modeling tool that will save time and expense in designing new and different size ion
engines, as well as analyzing existing ion engine performance.
ASSURE - Aeroelastic / Aeroservoelastic (AE/ASE) Uncertainty and Reliability Engineering capability - is a set of probabilistic computer programs for isolating uncertainties in simulation, manufacturing, test, measurement, and test to analysis correlation affecting the AE/ASE characteristics of advanced flight vehicles in flight and on the ground, and for studying the effects of such uncertainties. ASSURE will provide a quantitative assessment of the statistics of AE/ASE stability and dynamic r
A scalable gravity offload device simulates reduced gravity for the testing of various surface system elements such as mobile robots, excavators, habitats, and deployables in a relevant environment.  The device is capable of simulating reduced gravity over an arbitrary terrain including such features as slopes, obstacles, and varying surface concavity.   The device consists of a linear movement system, a 2 degree-of-freedom manipulator, a passive force application mechanism, and a position tracking mechanism.  The manipulator travels along the linear movement system and is positioned perpendicular to the linear movement system's direction of travel.  The result is a rectangular working area whereby the gravity offload device can simulate reduced gravity in the area defined by the length of the linear movement system by the width (reach) of the 2 degree-of-freedom manipulator.  The force application mechanism is principled upon precision maintenance of a pressure in an air cylinder.  Precision regulation of supply pressure enables constant force over the throw of the air cylinder.  Varying the regulator supply pressure to the air cylinder(s) modifies the force experienced by the test article and therefore enables a gravity offload device to simulate a range of gravity fields proportional to the ability to regulate pressure.
Immense quantities of expensive liquefied helium are required at Stennis and Kennedy Space Centers for pre-cooling rocket engine propellant systems prior to filling with liquid hydrogen, for pressurizing tanks and for safely purging residual hydrogen. Presently, the helium used in these processes is discarded, along with substantial quantities of hydrogen. TDA Research proposes to design and build a compact, portable and cost effective membrane system for recovering, purifying and storing both helium and hydrogen. Recovered helium containing less than a few percent residual hydrogen can be re-used as a purge gas. The ultrapure hydrogen recovered concurrently may be burned as fuel or used to generate clean electricity in fuel cells. The performance of these high selectivity membranes has been demonstrated and is ready for implementation to solve this problem. In Phase I we will fabricate membranes and assess their performance by processing a simulated purge gas stream and determining the purities of the helium and hydrogen. We will also carry out a detailed engineering feasibility and cost analysis to determine the technical viability of scaling up the process in Phase II. TDA's system will help NASA conserve valuable hydrogen and the United State's rapidly dwindling and expensive non-renewable helium resource.
Fiber reinforce polymer (FRP) composite materials are seeing increasing use in the construction of a wide variety of aerospace structures. However, uncertainties regarding the material's impact durability continue to plague the FRP composites community.
NASA has a requirement for a large-area, high-quantum-efficiency, high-throughput optical receiver for ground-, air-, and space-based LIDAR systems. A radiation-hardened direct detection analog LIDAR receiver will be developed to address this need in the proposed STTR program. The rad-hard LIDAR receiver will be based upon a high gain (M &gt; 1000), low excess noise (k ~ 0.02) InGaAs APD technology with high quantum efficiency (&gt;80&#37;) between 1000-1600 nm, deployed in a 61-element segmented array with a 600-um-diameter aggregate sensitive area. Segmentation of the detector area will minimize pixel capacitance, reducing amplifier noise and enabling GHz-class bandwidth. In Phase I, the proposed hexagonal APD array will be fabricated and hybridized to a custom fanout board for operation with discrete amplifiers. In the Phase II effort, a custom low-noise readout integrated circuit will be developed to mate directly to the hexagonal array, enabling higher sensitivity and higher bandwidth due to reduced interconnect parasitics. At the end of Phase II, the APD receiver will be integrated into a LIDAR test bed by the Electro-Optical Systems Laboratory at Georgia Tech for evaluation in a 6-month measurement campaign.
Voxtel anticipates that its technology will enter the program at TRL=4, finish Phase I at TRL=5, and exit the Phase II program at TRL=7.
Physical Sciences Inc. (PSI) together with the University of Connecticut (UCONN) proposes to demonstrate the improved fuel cell catalyst support durability offered by directly incorporating nitrogen functionality into graphitic carbon supports.  In Phase I, PSI will utilize the functionalized carbon support in the construction of single cell fuel cells in order to demonstrate the performance and durability of the support material in the PEM fuel cell environment.  The performance of cells upon accelerated life testing will be characterized and compared with that of cells assembled using commercially available support materials to quantify the benefits offered by the functionalized support.  In Phase II, PSI will work with UCONN to optimize and scale-up the support production processes.  Incorporation of additional functionalities will also be investigated.  Demonstration cells will be constructed and delivered for functional and environmental testing at the completion of the Phase II contract.
Stir welding generates high-quality joints in fabricated structure and is the baseline joining process for most NASA aluminum alloy structures such as cryogenic tanks and lightweight structures. Incorporating ultrasonic vibration to critical stir welding machine components will enable and expand stir welding to other high-strength, high-temperature alloys using solid state joining.
A compact portable sensor for determining the purity of oxygen concentrations near 100 percent is proposed based on differential absorption of two beams from a diode laser. One beam passes through a cell containing the sample of gas to be analyzed and the second beam passes through a reference cell containing a known concentration of high-purity oxygen. An autobalanced detection system will be used for measuring the difference in photocurrents of the transmitted beams. Common mode noise such as laser intensity noise will be rejected to a high degree. The system should not be subject to drift because it would be possible to lock the laser wavelength to the oxygen line using the reference cell. We estimate that the proposed sensor concept should enable an accuracy of 0.05 percent to be achieved with a cell length of less than 10 cm. The sensor can be made rugged with a small footprint using microelectronics for laser control and signal processing. The proposed effort will test the feasibility of this sensor concept by seeking to demonstrate measurements of the desired accuracy using a breadboard system.
The team of Astro Terra Corp, Virginia Commonwealth University (VCU), and Virginia Tech (VT) propose the development of a composite polymer over Phase-I and Phase-II into a "Self-Healing Inflatable Extraterrestrial ShieLD (SHIELD) membrane with autonomic self-healing properties and active radiation protection. The multi-layer composite architecture of SHIELD membrane is envisioned to have three layers. The outer layer is fabricated from polyimide and the innermost layer made from a viscoelastic polymer. The middle layer will be a self-healing layer fabricated from ionomeric polymers or PDMS-based ionenes and will be the focus of research activities in this program..The team proposes to fabricate the self-healing layer from two polymers (i) an ionomer (Surlyn) and (ii) a novel PDMS-based polyionene and demonstrate autonomic self-sealing in Phase-I. In addition, this polymer layer will be embedded with magnetoelectric nanoparticles and carbon fibers bundles that are in electrical contact and connected to an external circuit.  The combination of magnetoelectric nanoparticles and carbon fibers will provide damage detection, resistive and/or inductive heating based self-healing and electromagnetic radiation protection. The polymer candidate that offers the most advantage in autonomic healing and radiation protection will be pursued for further development into a lightweight inflatable membrane in Phase-II.
Thermoelectric (TE) devices already found a wide range of commercial, military and aerospace applications. However, at present commercially available TE devices typically offer limited heat to electricity conversion efficiencies, well below the fundamental thermodynamic limit, calling for the development of higher efficiency materials. The team of MicroXact Inc., Virginia Tech and Sundew Technologies Inc. is proposing to develop a revolutionary ultrahigh efficiency thermoelectric material fabricated on completely new fabrication principles. The material comprises the three-dimensional "wells" of Bi2Te3/Bb2Te3 Quantum Well Superlattices fabricated by a conformal coating of macroporous silicon (MPSi) pore walls. Such a material will provide ZT &gt;2 at macroscopic thicknesses of the material, permitting 15&#37; or more conversion efficiencies. In Phase I of the project the thorough model of the proposed TE material was developed, the achievable efficiency and ZT of the material were confirmed through numerical modeling, and conformal coating of pore walls with Sb2Te3 was experimentally demonstrated, validating the proposed concept. In Phase II the team will fabricate the proposed material and device, and will demonstrate ZT&gt;2 and conversion efficiencies exceeding 15&#37;. After the Phase II MicroXact will commercialize the technology.
AdvR, Inc. proposes the development of an efficient process for fabricating ridge waveguides in magnesium-doped lithium niobate (MgO:LN).  The effort will include, but will not be limited to, fabricating ridge waveguides in periodically poled MgO:LN for highly efficient, single-pass, quasi phase-matched frequency conversion.  Ridge waveguides in MgO:LN will significantly improve the performance (power handling and conversion efficiency), increase photonic component integration, and be well suited to space based applications.  The key innovation in this effort is to combine recently available large, high photorefractive damage threshold, z-cut 5&#37; MgO:LN with novel ridge fabrication techniques to achieve high optical power, low cost, high volume manufacturing of frequency conversion structures.  The ridge waveguide structure maintains the characteristics of the periodically poled bulk substrate, allowing for the efficient frequency conversion typical of waveguides and the high optical damage threshold and long lifetimes typical of the doped bulk substrate.
Thermoelectric (TE) generators have the advantages of no moving parts and flexibility in deployment but suffer from low heat to electricity conversion efficiencies, with a major loss component being conductive (phonon) heat transfer through the TE lattice.  By using a high pressure shockwave consolidation, nanopowders can be fused into a solid bulk TE material while preserving the nanostructure.   The high density of grain boundaries and lattice defects impedes phonon transport while allowing electron flow.   Specific Phase 2 research thrusts will be directed at transitioning laboratory fabrication into volume manufacturing, at producing a graded thermoelectric that is optimized for different temperature ranges over the length of the element, and at preparing bulk thermoelectric material from transition metal trichalcogenides that are not appropriate for  melt or powder sintered fabrication.   

The overall conversion efficiency of a TE device will always be limited by the Carnot ratio of (Th-Tc)/Th, where Th and Tc are the temperatures of the hot and cold junctions.   With the restrictions on phonon transport accruing from nanopowder consolidation, conversion efficiencies in excess of 30&#37; of the Carnot limit are reasonable.
Current modeling of Lunar and Martian soil erosion and debris transport caused by rocket plume impingement lacks essential physics from the peculiar granular characteristics of highly irregular regolith particles. Current granular mechanics models are based on mono-disperse spherical particles empiricism unsuitable for capturing the poly-disperse irregularly shaped grain mechanics.
The ability to quickly and reliably simulate high-speed flows over a wide range of geometrically complex configurations is critical to many of NASA's missions. Advances in CFD methods and parallel computing have provided NASA the core flow solvers to perform these simulations. However, the ease of use of these flow solvers and the reliability of the results obtained are a strong function of the technologies used to discretize the domain. Many applications involve solutions with highly anisotropic features: boundary layers, shear layers, wakes, shocks etc. Efficient resolution of those features motivates matching the mesh resolution/anisotropy to the solution's anisotropy but, in the more challenging applications, the location and strength of those features is difficult to precisely estimate prior to solution. Currently available meshing tools are not capable of producing and controlling the required initial meshes, nor adapting the mesh to match evolving anisotropic features. This project will combine Simmetrix Inc. expertise in the development of meshing components for flow simulations, and Rensselaer's Scientific Computation Research Center expertise in the development of adaptive mesh control technologies, to provide NASA the mesh generation and adaptation technologies needed. New techniques will be developed to create highly anisotropic semi-structured and unstructured meshes suitable for CFD simulations with high Reynolds number flow features (e.g., boundary layers, bow shocks, free shear layers, wakes, contact surfaces). Techniques to adapt these meshes based on mesh correction indicators will be developed to enable fully automated adaptive simulations.  All procedures to be developed will work effectively in parallel on large-scale parallel computers and will support a wide range of flow solvers. The overall capabilities will be demonstrated through execution of fully automated parallel adaptive simulations on problems relevant to NASA.
Small and micro-spacecrafts require the efficient, micro-propulsion systems.  Chemical micro-propulsion is best suited for use as primary thrust, orbital insertion and attitude control because of its high energy density.  When grouped into arrays for larger thrust applications, micro-propulsion devices provide high propulsive flexibility or can be used as igniters.

The proposed effort will focus on thermo-catalytic ignition and combustion of advanced mono- and bi-propellants in micro-channels; and the development of a micro-propulsion device. An innovative near net shape forming technique, in combination with carbon nanotube deposition, will facilitate manufacturing of sub-millimeter diameter micro-channels and tubes with enhanced internal surfaces area for maximum catalytic reaction. The microchannels will provide thermo-catalytic ignition of bi-propellant rockets without needing high voltage igniters and can also provide stable and reliable ignition source for advanced, environmentally friendly, mono-propellants.
We propose to demonstrate key elements of feasibility for a single-sided time-domain terahertz reflection holographic tomographic imaging (TD-THz RHT) nondestructive evaluation (NDE) system which will provide high quality three dimensional images of the interior of complex aerospace composite structures.  Time-domain terahertz imaging in the 0.1 to 3 THz spectral range is currently being used to characterize defects in Space Shuttle insulation and related materials.  The principal imaging technique has utilized 2D raster scanning of a THz transmitter and receiver to generate a two-dimensional image from the reflected signal intensity.  The proposed STTR will use existing Picometrix THz imaging hardware, but incorporate measurements of the scattered THz fields, enabling full 3D reflection-mode reconstruction of non-metallic materials on a metallic substrate.  It will use holographic information consisting of phase and amplitude data collected through a 2D sampling plane.  The specific reconstruction algorithm to be developed is a novel model-based reconstruction algorithm.  This will algorithm will maximize the 3D reconstruction accuracy for the data available.  Various options for image angles and sample geometries will be explored.  The final imaging system will incorporate 2D or 3D scanning hardware and multiple angle data collection to maximize 3D image quality in rapid scanning applications.
Airfoils produce more lift and less drag when the boundary layer is attached to the airfoil.  With most aircraft there are combinations of airspeed and angle of attack where the boundary layer at least partially detaches from the airfoil.  Reducing boundary layer detachment will increase lift and reduce drag.  This will reduce fuel consumption saving money for the operator and improving control for the pilot.  Two methods are known to improve boundary layer attachment:  heating the air and supplying acoustic pressure at an airspeed and airfoil shape dependent frequency.  Carbon nanotubes can be used to produce heating elements as thin as a layer of paint.  Because they are thin they can be heated and cooled hundreds of times per second.  This combination means that carbon nanotube heating elements can be thermoacoustic speakers to both heat the air stream and generate the appropriate acoustic frequency to maximize boundary zone attachment.

All system components have been demonstrated individually achieving TRL 2.  Phase I will demonstrate multifrequency sound generation on surfaces in a wind tunnel using nanotube heating elements, and achieving TRL 3.
Phase II will include medium seals wind tunnel tests verifying the effects and achieving TRL 5.
Computational fluid dynamics (CFD) simulations are routinely used while designing, analyzing, and optimizing air- and spacecraft.  An important component of CFD simulations is mesh generation, or discretization into polygonal or polyhedral cells, of the domain being analyzed.  The overall computational cost and accuracy of simulations depend heavily on mesh quality ? the size, shape, and structure of the cells.  Another important aspect of CFD simulation is that solutions are achieved iteratively, with each subsequent pass decreasing error and increasing solution accuracy.  Grid adaption uses output from the last simulation to improve the mesh for the next.  FUN3D is a CFD simulator developed at NASA that requires both a tight integration with mesh generation software for grid adaption and the generation of high aspect ratio cells (i.e. 10,000:1) to accurately capture dynamics around boundary layers.
Current meshing methods use the well known advancing front or Delaunay algorithms, and the user must often perform multiple manual inputs and interactions to generate a mesh of sufficient quality.  Ideally, a meshing module would subdivide complex designs and perform grid adaption automatically, with little or no human intervention.  The proposed innovation is the development of a very high aspect ratio mesher that demonstrates a significant improvement over current techniques as measured by the time and effort necessary for FUN3D users to solve CFD problems.
We propose to develop an Action Languages which allows for the representation of time and time dependent processes and which allows for the valid composition of modules.  Furthermore, we will develop a provably correct translation from the Action Language into Logic Programs under the Answer Set Semantics.  Action Languages have already proven useful for the representation of intelligent agent that can perform planning and diagnosis. Our proposed work would allow for more robust agents as well as the ability to do tasks such as scheduling.  We will also develop proof techniques to ensure correctness of the agents.  We propose to support control systems developed for such agents in distributed real-time systems with a dynamic, on-line, verification of the system behavior with respect to time-based properties.
Structured Materials Industries, Inc. and Cornell University propose to develop high speed integrated photonic switches and WDM for LIDAR applications. The team has recently shown that single mode silicon nitride (Si3N4) waveguides to have very low propagation losses. This material is an ideal candidate for the propagation and manipulation of optical signals at LIDAR wavelengths (1.06 &amp;#956;m). It is possible to imbue electro-optic (EO) properties to these waveguides using an electro-optic polymer. Such polymers have been demonstrated to have very high switching speeds, where light signals were modulated at frequencies in excess of 1 THz.

The program will address the efficient integration of active hybrid materials for externally controlling the silicon nitride photonic structures for the goal of obtaining high speed (&lt; 1 ns) switches. Furthermore, these devices also will have qualities that are attractive to this LIDAR project with their compact size, low power consumption and power efficiency. Solutions to these technical challenges will enable the design of systems of unprecedented performance. This program begins at Technology Readiness Level (TRL) 2, will advance to TRL 3 at the end of Phase I and products will achieve TRL 6 at the end of Phase II.
This Small Business Innovation Research Phase I project is for the development of an asymmetric supercapacitor that will have improved energy density and cycle life. Supercapacitors that utilize an aqueous electrolyte are limited to a maximum voltage of 1 volt due to the decomposition of water. Methods used to increase voltage include use of an organic electrolyte, which introduces additional complexity, cost and undesirable environmental concerns, or to use an asymmetric or hybrid configuration, with two different electrode materials. Supercapacitors that utilize MnO2 and carbon as the electrodes have been developed. However, due to changes in the MnO2 while cycling the capacitor to 2 volts, the MnO2 will change over time and lose its ability to cycle. One method around this problem, reported in the literature, is to charge the capacitor to 1.5 volts, resulting in reduced power and energy storage. In this Phase I program Giner, Inc. will demonstrate a novel solution to this problem by modifying the MnO2 positive electrode through the use of magnetic microparticles dispersed throughout the electrode structure. Using a Giner, Inc. novel high-energy density carbon as the negative electrode, complete, button-cell capacitors will be assembled and tested.
Advances in high power, photovoltaic technology has enabled the possibility of reasonably sized, high specific power, high power, solar arrays.  New thin film solar arrays have demonstrated specific powers of over 4000 W/kg (exceeding the current SOA of ~130 W/kg).  At high specific powers, power levels ranging from 50 to several hundred kW are feasible for communication satellites.  Coupled with gridded ion thruster technology, this power technology can be mission enabling for a wide range of missions ranging from ambitious near Earth NASA missions to those missions involving other customers as well such as DOD and commercial satellite interests.  The appeal of the ion thrusters stems from their overall high efficiency, typically &gt;70&#37;.  At present, the most advanced and mature gridded ion thruster technology is that embodied in the 7-kW NEXT ion thruster.  The proposed Phase I effort seeks to design and fabricate a ion thruster discharge chamber with an equivalent beam area of a 50-cm-diameter cylindrical ion thruster with the capacity to fill the 7 to 25-kW void that currently exist for ion thrusters.  The overall effort (Phases I and II) will advance the TRL level of the discharge chamber for the 50-cm thruster by understanding and optimizing the discharge chamber.
The tracking of critical flow features (CFFs) such as stagnation point, flow separation, shock, and transition in flight provides insight into actual aircraft performance/safety. Sensing of these CFFs across flight regimes involves numerous challenges such as a wide temperature/pressure range from subsonic to hypersonic flows. Tao Systems, Mesoscribe Technologies and Virginia Tech propose to develop a novel direct-write sensor architecture for the in-flight measurement of skin friction and heat flux that is survivable to temperatures exceeding 1000 deg. C while simultaneously providing fast response necessary for real-time signal processing to obtain CFFs. As a consequence, this technology will extend the utility of CFFs for aeroservoelastic control from subsonic to supersonic and hypersonic flows, as well as provide test information from experiments in flight.
NanoSonic has demonstrated that Shape Memory Metal Rubber&lt;SUP&gt;TM&lt;/SUP&gt; (SM-MR) adaptive skins exhibit reconfigurable and durable RF properties.  It is hypothesized that such morphing skins shall also exhibit durable radiation resistance upon morphing; a property that few, if any, flexible materials offer.  Typical highly filled or metal evaporated nanocomposites crack and spall upon flexation, and cannot be repeatedly mechanically stretched without rupture after a few cyclic strains.  SM-MR nanostructured morphing materials are based on self-assembled high z, dense, Au and Ag nanoparticles, rather than Pb.  Our manufacturing process yields tough skins that can be repeatedly and severely mechanically morphed without loss of EMI shielding (-88dB).  NanoSonic, together with Colorado State University, have demonstrated that SM-MR is up to 50&#37; lighter in weight and provides greater gamma ray attenuation relative to commercial off-the-shelf shielding materials, without emitting harmful secondary radiation under a 137Cs source.  During Phase I, radiation shielding would be verified for SM-MR during potential disparate space array morphed configurations to demonstrate durability, stowability, and reconfigurability for space tolerant structures with self-healing properties to reach TRL6.  TRL8 and 9 shall be reached during Phase II and III with assistance from our space systems prime partner upon flight testing and integration.
This proposal offers to provide NASA with an automatic mesh generator for the simulation of aerodynamic flows using Reynolds-Averages Navier-Stokes (RANS) models. The tools will be capable of generating high-quality, highly-stretched (anisotropic) grids in boundary layer regions and transition smoothly to inviscid flow regions even in an adaptive context. The objective of the work is to offer a unified view for generating quality and robust RANS meshes coupled naturally with anisotropic mesh adaptation. Our innovation is to view the anisotropic mesh generation within the Riemannian metric framework which thus far has been used exclusively in anisotropic mesh adaptation. Using the metric-based framework allows much easier handling of the large mesh size ratios involved in the computation, whereas traditional methods use the Euclidean framework to compute distance and volume. This innovative view to generate these meshes makes the entire procedure more generic and much more robust. The emphasis is being put on deriving a completely automatic process to generate quality and robust anisotropic meshes. Our existing and proven software package will be modified to include these innovative methods.  A NASA test case will be computed for validation of the methods.  The software will be delivered in Phase II.
The overall objective of the proposal is to design, develop and demonstrate a potentially portable Compton x-ray scatter 3D-imaging system by using specially designed rotationally movable x-ray source and x-ray detector, and the development of a suitable 3D-processing computer model. 

The proposed rotational configuration will allow the acquisition of multiple projections or images 360?a around the region of interest, probing a conical volume of the object to be interrogated. The subsequent application of a computer model on these multiple projections, developed during Phase I, will allow a three-dimensional reconstruction of the object under study.

In the proposed x-ray imaging system, the primary technical advance will be to extend methods that normally supplied a 2D projected image through a sheet of material, to a 3D image with more complicated features at different depths, such as cracks, corrosion, voids, delaminations, land mines, or improvised explosive devices.  Also, the proposed system will be potentially portable, allowing it to be brought to the object to be imaged.

The Beta and Production Phases of the proposed system would incorporate a battery self-contained package and wireless data transfer capabilities. These systems would revolutionize the current imaging applications that rely on 2D x-ray imaging systems only.
Intelligent Fiber Optic Systems and Auburn University propose a Fiber Bragg Grating (FBG) integrated Structural Health Monitoring (SHM) sensor system capable of providing in-situ crack detection, location and quantification of damage, as well as validating structural models, using recent advances in non-contact, non-destructive dynamic testing of composite structures. The key innovation is an FBG-based SHM system for detecting, locating and quantifying crack and de-lamination in composite structures such as smart, composite jet engine vanes with embedded FBG sensor systems. These new techniques make it possible to analyze complex structures not only non-destructively, but also without physically contacting or implanting electrical elements into test samples. The state-of-art FBG sensor system will be capable of measuring strains, stress, temperature and pressure and monitor damage to the structure under test at the same time at wide temperature ranges. IFOS and its university research collaborator will investigate the feasibility of such multi-functional FBG sensors with great potential for SHM. Advanced signal processing, system identification and damage identification, location and quantification algorithms will be applied. Potentially, the solution could evolve into an autonomous onboard monitoring system to inspect and perform Non-Destructive Evaluation and SHM.
To address the NASA need for innovative methods to measure liquid propellant tank volume and tank fluid level with improved accuracy, repeatability, and minimal tank entries for maintenance and calibration, Luminit, LLC, proposes to develop a new non-contact Luminit Optical Tank-level Sensing system (LOTS), based on the optical measurement of a small spotlight shone on the surface of the liquid.  This approach incorporates commercial off-the-shelf components and Luminit opto-mechanical design, which enables us to meet NASA requirements for a novel liquid level sensor for low-density fluids such as liquid hydrogen, and offers the possibility of remote operation, compact size.  In Phase I, Luminit will demonstrate the feasibility of accurate measurement of a low-density fluid by building and testing a proof-of-concept prototype, which will reduce development risk in Phase II.  In Phase II, Luminit plans to build a functional prototype for cryogenic liquid level measurements.  The demonstrated results will offer NASA a replacement for the multiple float switches currently in use. LOTS is expected to be at TRL 2 by the end of Phase I, with the results of this project paving the way to reach TRL 6 by the end of Phase II.
NanoSonic's Shape Memory Metal Rubber&lt;SUP&gt;TM&lt;/SUP&gt; (SM-MR) exhibits reconfigurable and recoverable changes in structural and RF properties as it can be mechanically and repeatedly inflated without loss of EMI shielding (-88dB).  In support of NASA's goals for a robust space exploration program, it is anticipated that NanoSonic's lightweight low permeable bladders shall also exhibit long term radiation resistance upon morphing; a property that few, if any, inflatable materials offer.  Typical highly filled or metal evaporated nanocomposites crack upon flexing.  Conformal and compliant SM-MR is based on self-assembled high-z, dense, nanoparticles covalently bound to ultra-low glass transition temperature (as low as -145&amp;#61616;C, 128 Kelvin) elastomeric or shape memory polymers.  NanoSonic and our STTR partner, Colorado State University, have demonstrated that SM-MR is up to 50&#37; lighter in weight and provides greater gamma ray attenuation relative to commercial shielding materials, without emitting harmful secondary radiation under a 137Cs source.  During Phase I, low temperature flexibility, and radiation/micrometeorite (lunar dust) resistance would be verified under simulated Galactic Cosmic Radiation (GCR) conditions, using gamma radiation sources and an electron accelerator with uniform beams up to 20 MeV.  TRL9 shall be reached with our space systems partner upon infusion of Thoraeus Rubber&lt;SUP&gt;TM&lt;/SUP&gt; onto NASA habitats.
Innovative Imaging and Research, a small technology development company,
has teamed with the University of Southern Mississippi Instrument and
Cryogenics Research Laboratory to integrate existing NASA Stennis Space
Center heritage cryogen level monitoring technology with noncontact
optical methods and advanced signal processing to create a 21st century
liquid cryogen level measurement technique.  We propose to place a
fiber-optic laser range finder on the upper surface of a low pressure
cryogen run tank and use the existing Hall effect float system as an
optical target to reflect the light signal back to the range finder.  We
also propose combining measurements obtained with the fiber-optic range
finder with those taken by the heritage system using a custom Kalman
filter signal processing algorithm to reduce measurement noise and
increase overall accuracy.  Our optical technique has several advantages
over the existing Hall effect method.  It yields near continuous
measurements and is not dependent on the location of individual sensors.
It is based on an alternate physics approach and therefore yields
completely independent results.  The optical range finder instrument
calibration is performed outside the tank, so test operation is not
significantly impacted and run tanks do not need to be emptied.  In
addition, an optical fiber mounted on the upper surface of a cryogen
tank does not present foreign object debris (FOD) concerns.  During our
Phase 1 STTR project we will demonstrate our concept in a university
cryogen research laboratory using a commercial optical range finder.  In
Phase 2 we plan to demonstrate our concept with fiber-optic technology
using the SSC Instrument Test Apparatus under a NASA Space Act
Agreement.  Our Phase 1 concept is at a technology readiness level (TRL)
of 2.  We expect to complete Phase 1 at a TRL of 4 and complete Phase 2
at a TRL of 6.
Airfoils produce more lift and less drag when the boundary layer is attached to the airfoil. With most aircraft there are combinations of airspeed and angle of attack where the boundary layer at least partially detaches from the airfoil.
The proposed effort will develop a technology to wirelessly and efficiently transfer power over hundreds of meters via resonant inductive coupling.  The key innovation of this approach is the use of dielectricless high-temperature superconducting (HTS) coils to overcome the limitations in efficiency and range of existing solutions.  This approach is informed by existing research models that predict a nominal application of this technique is capable of delivering 100 Watts of power at a distance of 100 meters with over 90&#37; efficiency.  A notional application of the technology is to deliver power to rovers exploring the inside of craters at the Lunar poles, where solar power is not available.  The naturally low temperatures would eliminate the need for thermal control overhead on the rover, allowing the system to be charged from a completely unenergized state or powered directly.  Multiple rovers could be powered by the same transmission system and there would be no pointing requirements for operation.  The phase I effort will demonstrate efficient wireless power transfer using superconducting wires as a proof of concept (TRL 3-4), which will be integrated with existing thermal control technology (TRL 4) into a working prototype (TRL 6) at the end of Phase II.
The objective of this NASA STTR program is to produce ultra-lightweight electrical wire and cable harnesses to reduce the liftoff weight of future space flight vehicles.  In cooperation with materials scientists at Texas A&amp;M, NanoSonic would develop and manufacture ultra-lightweight Metal Rubber- and carbon nanotube-based rubber (CNT Rubber) wire and cables with performance equivalent to that of conventional copper cables but with only 10&#37; the weight.  Wiring harnesses contribute significant weight load to the spacecraft structure.  Ultra-lightweight Metal Rubber and CNT Rubber wires and cables can reduce that weight while offering comparable or superior electrical power and data transmission performance and EMI resistance.  During Phase I, NanoSonic would design, fabricate and test lightweight Metal Rubber and CNT Rubber wire and cable prototypes.  Texas A&amp;M's nanotechnology laboratory would co-develop methods for CNT Rubber production and evaluate resulting material properties.  The conducting core and outer shielding layers would be fabricated by molecular-level self-assembly.  Electrically-conducting cable shielding tape layers would be dimensioned using CAD-driven templating equipment at NanoSonic.  Wire and cable would be manufactured using wire feed, dielectric extrusion and shielding tape winding steps.  NanoSonic is working with a major U.S. cable manufacturer and a major U.S. spacecraft prime contractor on this program.
Innovative Imaging and Research has teamed with the University of Southern Mississippi to develop a novel energy efficient smart light system. Smart lighting adds an occupancy sensor, photosensor, controller, and dimming unit to a light source and has been shown to save up to 50&#37; of the energy required to power traditional lighting in existing buildings and up to 35&#37; in new construction.
The objective of this Phase I STTR project is to develop a highly sensitive oxygen (O2) sensor, with high accuracy and precision, to determine purity levels of high concentration (&gt; 99&#37;) O2 gas streams. This sensor will meet NASA applications for on-orbit O2 purity checks in portable life support systems (PLSS) and during in situ O2 production activities. InnoSense LLC (ISL) will utilize its proprietary Chemical Fingerprint (TM) sensor array fabrication technology in this project coupled with the combinatorial analysis and high throughput sensor evaluation capabilities of the STTR partner.  In Phase I, ISL will engineer a working model and demonstrate NASA use potential of the technology. Upon fine-tuning various parameters in Phase II, the system performance will be tested with a prototype hardware. For assuring success of this project, ISL has assembled a technical team with a cumulative 90 person-years of experience in developing commercially viable sensor systems.
Balcones Technologies, LLC proposes to adapt technologies developed by and resident in The University of Texas at Austin Center for Electromechanics (CEM) in the areas of dynamically controlled precision actuators and flywheel energy storage systems to address STTR 2011-1 Subtopic T3.01, Technologies for Space Power and Propulsion.  In particular, our team will develop a concept design for a replacement to traditional flywheel gimbal systems that is based on a parallel kinematic structure proposed by Dr. Canfield in approximately 1997 as a carpal wrist joint, now commonly known as the Canfield Joint.  The intended result will be a concept for an actively controlled Canfield-Joint Gimbal Replacement System (CGRS) that is considerably less expensive, simpler, and more reliable than current gimbal technology; does not require slip rings for power and control cables; does not have singularity issues, such as gimbal lock; and has relatively simple controls based on analytical kinematic solutions.  Our proposed Phase I project will fully evaluate requirements, develop appropriate simulations of the kinematics and control system for a flywheel with magnetic bearings in the CGRS, develop a concept design of the CGRS, develop a commercialization and production plan, and develop a Phase II program plan to demonstrate the system with an existing high-speed flywheel system on magnetic bearings.
Fibertek, Inc. and Univ. of Maryland, Baltimore County (UMBC) propose to optimize and verify, an advanced platform for direct-detection lidar transmitter, based on using a dual-wavelength fiber-lidar transmitter. The proposed lidar tramsitter is based on a recently developed fiber lidar platform at Fibertek, that is capable of high spectral resolution at both 1064nm/532nm, has flexible pulse capability from sub-nsec to micro-seconds, with arbitrary optical waveform generation. This will be integrated in the lidar measurement system at UMBC, and lidar calibration, validation, and performance analysis will be conducted under different atmoshperic aerosol loading conditions. Such measurements will also be compared to co-located measurements conducted via the ELF and MPLNET lidar systems.
During recent robotic field tests, NASA investigated the use of intelligent planetary rovers to improve the productivity of human explorers on planetary surfaces. For these field tests, a remote Science Team built rover plans to collect data that supplements astronaut EVA and a remote Flight Team supervised the execution of these plans. This model of operation requires the Science Team to generate and revise all plans, often taking a partially executed plan and quickly updating it in response to issues that may have nothing to do with science. As a result the Science Team pre-builds alternative plans, many of which are not used. In future exploration operations, astronauts orbiting a planet will supervise rovers operating on the surface below without benefit of real-time support from Earth because of time delay. In such cases it becomes important to provide a more flexible planning approach that permits the Science Team to distinguish essential tasks from tasks to be performed as time and resource permit, or in response to discovery (contingent tasks). TRACLabs and Carnegie Mellon University propose to build science alternatives into a single rover plan as contingent tasks, potentially reducing the time spent building plans and providing the Flight Team with more flexibility when executing plans. We will identify use cases describing how the Science Team will build plans with contingent tasks and how the Flight Team will execute these plans. We will design software for use by the Science Team to build plans with contingent tasks. We will design rover software for executing such plans and software for the Flight Team to supervise this execution. We will evaluate this design for use in K10 rover operations.
For this NASA STTR program, we propose to develop a novel
superlattice-based near infrared to midwave infrared avalanche
photodetector (APD) grown on InP substrates for single photon counting
applications at high operating temperatures on the order of 200K
accessible using thermoelectric coolers. This enables a detector with
broad spectral response spanning 0.9 to 4 ?m wavelength with reduced
cooling requirements, offering a reliable detector technology with small
size weight and power requirements that is ideal for future planetary
missions. The detector is based on Princeton Lightwave's
industry-leading planar-geometry single photon counting APD detector
platform designed for 1.55 ?m wavelengths, with incorporation of a novel
absorber region.
An orifice element is commonly used in liquid rocket engine test facilities either as a flow metering device, or to provide a large reduction in pressure over a very small distance in the piping system.  While the orifice as a device is largely effective in stepping down pressure, it is also susceptible to a wake-vortex type instability that generates pressure fluctuations that propagate downstream and interact with other elements of the test facility resulting in structural vibrations.  Furthermore in piping systems an unstable feedback loop can exist between the vortex shedding and acoustic perturbations from upstream components resulting in an amplification of the modes convecting downstream.  Such was the case in the Arianne 5 strap-on P230 engine in a static firing test where pressure oscillations of 0.5&#37; resulted in 5&#37; thrust oscillations. The innovation described in this proposal directly relates to a proprietary design of a step down orifice that inhibits the instability modes generally associated with the operation of a traditional orifice while meeting performance guidelines.  In the Phase I effort we will demonstrate the effectiveness of the new device through a combination of analysis and sub-scale testing in a cryogenic environment.
Small satellites require much lighter weight, smaller, and long life Attitude control components that can withstand stressing launch conditions and space vibration environments without compromising their performance. In particular, rate sensors that can provide high-resolution Line of Sight (LOS) stabilization, accurate inertial pointing and higher bandwidths are needed to support attitude and position determination from highly compact and very lightweight packages.
Intelligent Fiber Optic Systems Corporation (IFOS) proposes to prove the feasibility of innovations in acousto-optic sensor development for measurement of launch acoustics on space vehicle and ground structures. The proposed sensor platform provides an ultra-light-weight, ultra-high-speed, multi-channel, optical fiber sensor array system for acoustics measurements.
Aerodyne Research, Inc. and the University of Massachusetts at Amherst will collaborate to develop laser desorption ionization (LDI) mass spectrometric analysis of organic analytes of interest in planetary exploration, based on microchip laser illumination.
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 1 program on the materials optimization, structures optimization, 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. The ROSA technology will provide NASA/industry a near-term and low-risk solar array system that provides revolutionary performance in terms of high specific power (&gt;200-500 W/kg BOL at the wing level, PV-blanket dependent), affordability (&gt;25-50&#37; projected cost savings at the array level, PV-blanket dependent), ultra-lightweight, high deployed stiffness (10X better than current rigid panel arrays), high deployed strength (10X better than current rigid panel arrays), compact stowage volume (&gt;60-80 kW/m3 BOL, 10X times better than current rigid panel arrays), high deployment reliability and operation reliability, high radiation tolerance, high voltage operation capability (&gt;200 VDC), scalability (500W to 100's of kW), and LILT &amp; HIHT operation capability (LILT &amp;#150; Low Intensity Low Temperature, HIHT &amp;#150; High Intensity High Temperature).
We propose to develop a capability to provide integrated acceleration, vibration, and shock testing using a state-of-the-art centrifuge, allowing for the test of synergistic effects of these combined environments. By installing a shaker table on the centrifuge, the test setup can provide both sustained and dynamic-g loads as well as simultaneous vibration loads, in two independent axes.
The space environment poses significant challenges to spacecraft electronics in the form of electrostatic discharge (ESD) as a result of exposure to highly charged radiation belts.  The NASA Europa Jupiter System Mission environment, for example, exhibits radiation levels seven times greater than Earth's geostationary orbit.  In addition to the Jovian environment, highly charged environments can also exist at geosynchronous and medium Earth orbits owing to solar winds/storms and trapped radiation belts.  Such environments can wreak ESD havoc on unprotected critical spacecraft components inside the spacecraft bus.  While existing conformal coatings serve their purpose of insulating and protecting electronics from environmental effects, they do not exhibit ESD mitigation qualities.  No solution currently exists to provide both electronic environmental protection, optical transparency for component inspection, and charge dissipation characteristics in one coating system. To address this need, Luna, in partnership with The Aerospace Corporation, proposes to modify industry standard and space-qualified conformal coatings by dispersing transparent and conductive nanoparticles within them to impart electrical conductivity levels sufficient for charge dissipation and increased radiation hardening capability. The proposed coating system will provide the appropriate performance properties of both common conformal coating protection and radiation hardening through ESD mitigation.
NASA Stennis Space Center (SSC) is one of the largest consumers of
gaseous helium in the world through its engine testing operations.
Because helium is a nonrenewable resource, it is desirable to conserve
the gas when possible. For safety purposes, helium is used to purge an
engine following a test that utilizes cryogenic liquid hydrogen fuel
(e.g. a Space Shuttle Main Engine test).  This proposal is another
important step toward enabling helium conservation through real-time
measurement of the H2 concentration in the purge gas.  The STTR will
continue the characterization of a commercial H2 detector for use as a
real-time sensor for determining the concentration of H2 in the helium
purge gas.  The H2 concentration can be used as an indicator that the
liquid hydrogen has been purged from the engine, allowing the helium
purge to be of shorter duration, thereby conserving this resource.
Significant analysis of sensor capabilities as well as experimental
characterization of the sensor performance in a simulated test-stand
environment will be performed. A sensor configuration will be
recommended with the goal of identifying the best installation option
that avoids pumps, mechanical actuators, or the need to vent or pipe a
sample if possible.
Planetary Science Technology Program
Global Aerospace Corporation (GAC), and its research partner, Cal Poly San Luis Obispo (CPSLO), will develop an integrated Small Probe Reentry System (SPRS) for low Earth orbit (LEO) small satellite Earth reentry missions. The SPRS delivers the small probe to a targeted reentry, protects it from the harsh atmospheric reentry environment, slows it down so that it can land without damage to its payload, and announces its position for recovery.
An all-electric aircraft testbed is proposed to provide a dedicated development environment for the rigorous study and advancement of electrically powered aircraft.  The new testbed 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.  The testbed aircraft will allow various electrical propulsion system technologies to be tested to determine performance, reliability, safety, and cost.  These include various battery, fuel cell, super capacitor, and motor technologies.  Additionally, the new aircraft could be used to study energy-harvesting solutions including photovoltaics, vortex energy extraction, and piezoelectrics.  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 testbed aircraft able to systematically evaluate new and existing technologies, which will make these systems, safe, reliable, and cost effective.
Our basic approach is to use a photoelectrochemical cell operated under simulated Mars conditions.  The light source will be solar simulator with a wide spectrum of emitted light. On Mars wavelengths of light down to 190 nm reach the surface (compared to Earth where only 300 nm and above reaches the surface). The soil will be the JSC.Mars 1 stimulant which is known to contain 10&#37; TiO2 (in partial reduced forms) and is supposed to be a good analog for the surface soils on Mars. We will consider two possible sources of H2O: first water flowing as liquid from below the surface of the soil and second water deposited as condensate on the surface of the soil. Additional two types of photocatalysts will be evaluated for methane conversion efficiencies: off shelf low cost TiO2 (P25), and doped TiO2 nanostructures (nanotubes and nanowires) for broader solar wavelength absorptions.
New aircraft designs depend on an integrated active approach to flight control, flutter suppression and structural mode attenuation to meet desired handling quality performance and gust load alleviation. Tao Systems will team with Professor Gary Balas at the University of Minnesota to  (1) develop a robust controller that demonstrates improved aerostructural performance over the state-of-the-art by utilizing a novel aerodynamic load sensor, and (2) provide a robust linear parameter varying controller that (a) requires no ad hoc methods of gain-scheduling, (b) provides robustness guarantees  that more traditional methods do not offer, and (c) allows for explicit rate bounds enabling less conservative, higher performing controller designs. The benefits include improvement of aerodynamic and structural efficiency using robust aeroservoelastic control methods over a range of flight speeds, in the presence of significant turbulence.
The proposed project is crucial to enabling safe flight research on a rocket nozzle that is based on our recent innovation, which is to use the refrigerant capabilities of nitrous oxide (N2O) to provide cooling for an aerospike nozzle on hybrid rocket motor using N2O as the oxidizer. The phase change cooling as liquid N2O is flashed from a liquid into a vapor, limits to acceptable levels the erosion of both the nozzle throat and spike, thereby enabling reusable operation and/or long burn times. The N2O used for cooling will be reintroduced into the rocket motor and used to boost performance. Because of potentially the violent exothermic decomposition of N2O, a thorough understanding of N2O behavior is crucial to developing an aerospike nozzle and hybrid rocket motor that are sufficiently safe for flight testing, where cooling the aerospike is necessary to get the burn duration required for good flight tests to yield the illusive flight test data for aerospike nozzles. Our prior work seeking to develop a fundamental understanding of the behavior of N2O when it is used in applications has answered some important questions about the behavior of N2O, yielded significant advances in designing instrumented nozzles for N2O cooling experiments, and generated important advances in making accurate temperature measurements on the coolant flowing in these nozzles. However, our work in developing and validating analytical models for predicting heat transfer coefficients in N2O-cooling applications was only partially successful due to unanticipated levels of uncertainty from a variety of sources. By addressing the sources of the above-mentioned uncertainty using a combination of nozzle design, novel construction, analytical, FEA, and CFD modeling, along with experimental validation of all models, this work will yield the refined models of N2O behavior that are necessary for the future design of safe N2O-cooled aerospike nozzles.
As the aerospace industry continues to push for greater vehicle efficiency, performance, and longevity, properties of wing aeroelasticity and flight dynamics have become increasingly important. Both the study and the active control of wing dynamics require advanced sensing technology to inform the design process on the ground and provide feedback for aeroservoelastic systems in the sky.
We propose to develop a high-efficiency, triple-junction, epitaxial lift-off (ELO) solar cell by incorporating quantum dots (QDs) within the current-limiting subcell. We intend to leverage existing QD epitaxy processes developed by the Rochester Institute of Technology and combine this with MicroLink's expertise in multi-junction cell growth and ELO technology.
For supporting NASA's Robotics, Tele-Robotics and Autonomous Systems Roadmap, we are proposing the "Evolutionary Autonomous Health Monitoring System" (EAHMS) for planetary exploration, which will provide an integral flexible diagnostics and prognostics framework by advanced and novel methods for determining the operational condition in on-board sensors (odometry), actuators, and power systems. In EAHMS, high performance diagnostic techniques provide a foundation for tailoring robust and accurate
For long-term exploratory space travel, there will be a critical need for in-situ diagnosis and assessment of biological specimens from symptomatic astronauts, especially, disease pathogens (virus, bacterium, or fungus) and microbial contaminants. Hence, a real-time, non-culture-based microbial detection, identification and quantification system for on-flight monitoring and evaluation of pathogens from astronauts, or the space environment, is strongly desired. The success of such diagnostic tasks critically depends upon the degree of automation and reliability of such trace level detection. To meet this need, we propose to develop a novel miniaturized, point-of-care (POC) detector for reagent-free, no-culturing, in-situ diagnostics of disease pathogens. The envisioned device will be compact, lightweight, fully integrated and automated (requiring minimum human intervention), and highly cost-effective and power-efficient. In Phase I, we will develop a new type of electrochemical molecules and fabricate solid electrode-based probe for in-vitro demonstration of accurate and effective signal transduction of selective binding of pathogenic cells to the electrode as proof-of-principle. In Phase II, the electrode probe will be optimized to increase specificity, sensitivity, stability, and the response to regular biological samples. Finally, the sensor will be integrated with a compact handheld instrument for data collection, analysis and processing and interfacing with existing NASA space instrumentation for both terrestrial and microgravity environments evaluation.
Lynntech proposes a novel flow control methodology for airfoils undergoing dynamic stall. Dynamic stall refers to an aerodynamic phenomenon that is experienced by airfoils that undergo rapid changes in the flow angle of attack such as rotorcraft based airfoils, flapping wing technologies as well as fixed wing aircrafts undergoing sudden angle of attack changes. Dynamic stall is inherently an unsteady, non linear and complicated effect that can affect such flight parameters as lift, drag and airfoil stability. 
Lynntech, along with its STTR partner in Dr. Noel Clemens and Dr. Jayant Sirohi, at the University of Texas at Austin proposes to use novel pulsed plasma discharge based actuators for flow control on dynamically stalled airfoils. Lynntech has more than 20 years of experience with applied plasma physics and 10 years of experience with turbulent CFD modeling. Dr. Noel Clemens at the University of Texas Flow Imaging Research Laboratory in the Department of Aerospace Engineering, who has implemented and tested various types of plasma actuators for flow control. 
The proposed technology consists of pulsed plasma actuators which will induce high velocity airflow within the airfoil boundary layer, thus reattaching the flow. The proposed plasma actuator can achieve high Reynolds number (&gt;5e6) flow control compared to contemporary dielectric barrier discharge plasma actuators without relying  on corona discharge / hot plasma technology. Advantages of the system include low power consumption, ease of installation, increased flight stability, reduced drag and higher stall angles.
American GNC Corporation (AGNC) and Louisiana Tech University (LaTECH) are proposing a breakthrough technology consisting of an innovative system for facilitating the monitoring and management of NASA test facilities (such as rocket engine test stands) and widely distributed support systems (WDSS). This technology, termed the Intelligent Distributed and Ubiquitous Health Management System (IDU-HMS) consists of: (a) a fault aware wireless sensor network (WSN) for monitoring valves, vacuum lines,
Single multi-sensor teleoperated systems are not optimal for NASA exploratory missions because they limit the coverage area and scope of exploration and create a single point for mission failure. A better solution would use many robots cooperating to maximize exploration area and location accuracy while minimizing total system power and weight.
Fused deposition modeling (FDM) is an additive manufacturing technology that allows fabrication of complex three-dimensional geometries layer-by-layer. The goal of the present proposal is to extend FDM technology to create new polymer matrix composites (PMCs) comprising of polymers and inorganic matrices.
Development of new polyurethane (PU) insulation foams through a non-toxic environmentally friendly composite approach. Target FR foams will exhibit high heat flow resistance as well as lower density than conventional PU.
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.
The NASA Office of the Chief Technologist (OCT) has identified a "carbon-carbon nozzle (domestic source)" as a "Top Technical Challenge" in the 2011-2016 timeframe in the "Launch Propulsion Systems Roadmap" document. This program, by utilizing a demonstrably capable team with a deep history in the manufacture, testing, and analysis of C/C materials, will address this need by developing a Lyocell C/C composite system aimed at the need for a composite J2X nozzle extension.
Current approaches planned for space suit atmosphere revitalization (AR) are neither compatible with each other nor regenerable in space, and have a high life cycle operating cost associated with them. The proposed PCI innovation in collaboration with University of Hartford involves synthesizing improved sorbents on high surface area supports tailored for CO2, water and trace contaminant removal.
NASA plans to use intelligent planetary rovers to improve the productivity and safety of human explorers. A key challenge in using robots to support human exploration is orienting remote personnel about robot operations as latency and communication constraints make real-time monitoring impractical.
ProtoInnovations, LLC and Carnegie Mellon University have formed a partnership to commercially develop localization and mapping technologies for planetary rovers. Our first aim is to provide a reliable means of localization that is independent of infrastructure, such as GPS, and compatible with requirements of missions to planetary surfaces. Simultaneously solving for the precise location of the rover as it moves while building an accurate map of the environment is an optimization problem involving internal sensing, sensing of the surrounding environment, probabilistic optimization methods, efficient data structures, and a robust implementation. Our second aim is to merge simultaneous localization and mapping (SLAM) technologies with our existing Reliable Autonomous Surface Mobility (RASM) architecture for rover navigation. Our unique partnership brings together state-of-the-art technologies for SLAM with experience in delivering and supporting both autonomous systems and mobility platforms for NASA.

Our proposed project will create a SLAM framework that is capable of accurately localizing a rover throughout long, multi-kilometer traverses of barren terrain. Our approach is compatible with limited communication and computing resources expected for missions to planetary surfaces. Our technology is based on innovative representations of evidence grids, particle-filter algorithms that operate on range data rather than explicit features, and strategies for segmenting large evidence grids into manageable pieces. 

In this project we will evaluate the maturity of these algorithms, developed for research programs at Carnegie Mellon, and incorporate them into our RASM architecture, thus providing portable and reliable localization for a variety of vehicle platforms and sensors. Mission constraints will vary broadly, so our SLAM components will be able to merge readings from various suites of sensors that may be found on planetary rovers.
An accurate predictive capability of coupled fluid-structure interaction in propulsion system is crucial in the development of NASA's new Space Launch System (SLS). This STTR effort will develop a multi-disciplinary tool to improve CFD prediction capability in modeling coupled fluid structure interaction (FSI) phenomena for many SLS propulsion applications such as flexible inhibitors for SRMs.
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
The proposed project will develop a set of at least 100 passive wireless surface acoustic wave (SAW) RFID sensor-tags for near-simultaneous remote monitoring of groups of conventional sensors. Coded SAW sensor-tags have been demonstrated by ASR&amp;D under NNX09CE49P to be capable of providing a passive wireless interface to external sensors, including switches, thermistors, and strain gages, as well as external sensors that generate voltages.
Longhurst Engineering, PLC and Vanderbilt University propose the innovation of torque control of friction stir welding (FSW) as a replacement to force control of FSW. The value of the torque is significant because it indicates how far the tool is plunged into the work piece.
Protection of critical electronic systems in spacecraft and satellites is imperative for NASA's future missions to high-energy, outer-planet environments. The objective of this project is to develop flexible, transparent, and removable conformal coatings to protect delicate, mission-critical electronic components from electrostatic discharge damage. In collaboration with our partners, InnoSense LLC (ISL) proposes to develop a Transparent Conformal Conductive Coating that will meet the needs of NASA's space programs. The transparent conformal coatings will consist of a flexible and low-water-absorbing polymer matrix blended with conductive polymers. Phase I tasks focus on (1) preparing conductive polymers and conformal coating formulations, (2) developing coating and curing processes, and (3) testing conformal coatings with respect to adhesion, UV resistance, offgassing, resistivity, charge dissipation, ease of removal, and resistance to temperature cycling and vacuum.
We propose novel and real-time smart software tools to process spectroscopy data. Material abundance or compositional maps will be generated for rover guidance, sample selection, and other scientific missions. First, we propose a novel anomaly detector called clustered kernel Reed-Xiaoli (CKRX) algorithm.  This tool was developed by us, is fast, and can achieve very high anomaly detection rate in hyperspectral images from the Air Force. This is important in planetary missions because we may need to look for some anomalous regions in a scene. Second, if target material signatures are available, then we propose a fast matched signature identification algorithm called Adaptive Subspace Detector (ASD). We compared ASD with several other tools and found that ASD outperformed other methods. Third, if target material signatures are not available, then we propose a new technique called minimum volume constrained non-negative matrix factorization (MVCNMF) to perform unsupervised material identification. In a recent comparative study by using hyperspectral images from the Air Force, the MVCNMF performed better than some conventional unsupervised methods. Fourth, the above tools can be implemented in a parallel processing architecture, in which the computations are distributed to multiple cores. We have applied it to speech processing and genomic processing recently. Real-time performance is achievable.
The ability to quickly and reliably simulate high-speed flows over a wide range of geometrically complex configurations is critical to many of NASA's missions. Advances in CFD methods and parallel computing have provided NASA the core flow solvers to perform these simulations. However, the ease of use of these flow solvers and the reliability of the results obtained are a strong function of the technologies used to discretize the domain. Many applications involve solutions with highly anisotropic features: boundary layers, shear layers, wakes, shocks etc. Efficient resolution of those features motivates matching the mesh resolution/anisotropy to the solution's anisotropy but, in the more challenging applications, the location and strength of those features is difficult to precisely estimate prior to solution. Currently available meshing tools are not capable of producing and controlling the required initial meshes, nor adapting the mesh to match evolving anisotropic features. This project will combine Simmetrix Inc. expertise in the development of meshing components for flow simulations, and Rensselaer's Scientific Computation Research Center expertise in the development of adaptive mesh control technologies, to provide NASA the mesh generation and adaptation technologies needed. New techniques will be developed to create highly anisotropic semi-structured and unstructured meshes suitable for CFD simulations with high Reynolds number flow features (e.g., boundary layers, bow shocks, free shear layers, wakes, contact surfaces). Techniques to adapt these meshes based on mesh correction indicators will be developed to enable fully automated adaptive simulations. All procedures to be developed will work effectively in parallel on large-scale parallel computers and will support a wide range of flow solvers. The overall capabilities will be demonstrated through execution of fully automated parallel adaptive simulations on problems relevant to NASA.
This NASA Phase II STTR effort will develop domain-engineered magnesium oxide doped lithium niobate (MgO:LN) for LIDAR-based remote sensing and communication applications. Use of bulk and waveguide-based domain engineered MgO:LN will allow the manufacture of highly efficient and compact, wavelength conversion modules for second-harmonic generation (SHG), sum-frequency generation (SFG), and parametric down conversion (PDC).
Fault-Tolerant Control (FTC) is an emerging area of engineering and scientific research that integrates prognostics, health management concepts and intelligent control. Impact Technologies and the Georgia Institute of Technology, propose to build off of a strong foundation in fault-tolerant control (FTC) research performed with NASA in past years to mature the applicability of this technology and push the envelope on the capability and breadth of the technology itself. We are introducing for this purpose two novel concepts to expand the scope of fault tolerance and improve the safety and availability of such critical assets. Building upon the successes of Phase I, we will develop and apply to the hovercraft (a targeted testbed) a reconfigurable control strategy that relies on current prognostic information to maintain the platform's stable operation and complete its mission successfully. The second innovation to be introduced refers to a challenging problem encountered in complex systems such as aircraft platforms: A multitude of critical system components can not be monitored directly due to a lack of appropriate sensing modalities. We will introduce a Model Based Reasoning approach and frequency demodulation tools to resolve the ambiguity and "unmask" those fault variables that can not be observed directly.
Flight control, structural reliability, and efficiency depend critically on the ability to assess the time-accurate unsteady aerodynamic loads and moments for each lifting surface under nominal and adverse flow conditions. Tao Systems and California Institute of Technology propose to develop a flow control system that utilizes advanced sensors and a vorticity state estimator (VSE) to reach flow states unattainable without continuous control feedback. The flow control scheme enables manipulation of the vorticity state to achieve performance objectives, such as short take-off/landing through controlled aerodynamic lift at angles of attack near stall.
Electrodynamic tethers are optimally suited for use in Low-Earth-Orbit (LEO) to generate thrust or drag maneuver satellites. LEO region is polluted with space debris from the left over of rockets and abandoned satellites. It becomes important to clean them, i.e., de-orbit and ED tethers are promising for such applications. ED tethers are operating without propellants, so less polluting in our space and also cost-efficient. Tether powered satellites can operate in dual mode (thrust or power generation). Advanced PIC tools can perform self-consistent 2-D and 3-D tether simulations to study the plasma interactions and will improve the understanding of the self-induced magnetic field effects on the current collection ability of these ED tethers. These tools once validated using tether ribbon tape experiments can help NASA researchers to analyze various tether geometries in efforts to optimize tether design for space missions on a wide range of operating conditions.
In this Phase II project, we propose to develop, construct, and deliver to NASA a prototype single-sided computed tomography time-domain terahertz (single-sided CT TD-THz) scanner accessory. This accessory will be suitable to be mounted onto a non-destructive evaluation (NDE) imaging gantry for the single-sided inspection of spacecraft and launch vehicle composite structures.
The objective for the Phase II effort will be to develop a comprehensive, efficient, and flexible uncertainty quantification (UQ) framework implemented within a matured user-friendly software, which will enable the modeling of both inherent and epistemic uncertainties in spacecraft system models, have a general quantification of margins and uncertainties (QMU) capability for system certification and reliability assessment, and utilize advanced methods based on non-intrusive polynomial chaos (NIPC) for efficient and accurate propagation of mixed (inherent+epistemic) uncertainties as also demonstrated under the Phase I effort. In the proposed project, an adaptive uncertainty quantification methodology, which will successively utilize different NIPC methods depending on the size of the problem along with the non-linear global sensitivity information, will be implemented to address the computational expense of UQ in complex spacecraft system simulations with large number of uncertain variables. The developed UQ framework and QMU capability will be demonstrated on a large-scale spacecraft system model that is of interest to NASA. This proposed work will compliment M4 Engineering's expertise in developing simulation technologies that solve relevant demonstration applications. The researchers from MS&amp;T (RI) will guide the implementation of UQ and QMU methodologies and contribute to the proposed effort with their UQ expertise in aerospace simulations.
ACTA and Sandia National Laboratories propose to quantify and propagate substructure modeling uncertainty for reduced-order substructure models to higher levels of system assembly, thereby enabling predictive simulations of engineering designs with quantified margins and uncertainties for model-based flight qualification of complete spacecraft.  A critical part of this process is the accurate modeling of nonlinear components and interface structures, structures that connect major substructures, and the quantification of their uncertainties.  By developing uncertainty models for reduced order models of specific substructures, NASA will be able to quantify margins and uncertainties for structural systems outside the domain of model validation tests.
NASA is interested in advancing green technology research for achieving
sustainable and environmentally friendly energy sources for both
terrestrial and space applications. It has been reported that
thermo-electric power generation (TEPG) can contribute to electrical
power generation scavenged from waste heat sources. Significant
advantages to TE technology include: no moving parts, low-weight,
modularity, covertness, high power density, low amortized cost, and long
service life with no required maintenance. TEPG also has the potential
of enabling large-scale electric power generation. We propose to
continue are on-going research of PbTe single crystals and investigate
the FAST technique, developed by Penn State Univ., to produce bulk
nano-composites. We will assemble the material into TE devices and
optimize the high temperature electrical contacts for minimal
resistivity. We expect to standardize the processes to produce device
with efficiency up to 10&amp;#37; (we currently have efficiency of 4.4&amp;#37;) by the
end of Phase II.  The major goal of the proposed work is to establish
the feasibility that kilowatt levels of power can be produced in an
environmentally clean (pollution free) manner using TEPG.
Busek proposes to prove the feasibility of a Mg Hall effect thruster system that would open the door for In-Situ Resource Utilization (ISRU) based solar system exploration.  Elemental magnesium has favorable thermophysical properties and is very easy to ionize.  The estimated specific impulse for a high efficiency magnesium Hall thruster operating off of a standard 400 V power processing unit is 5000 s.  Efficiencies &gt;50&#37; will be possible.  Although the vapor pressure of Mg is relatively low, it is believed that spacecraft interactions can be managed through the implementation of a simple plume shield.  Moreover, magnesium is found abundantly in the regolith of Mars and the Moon, from which it can be readily extracted.

In Phase I, we will prove the concept's feasibility through four technical tasks.  In the first task, the overall architecture of a Mg Hall thruster system will be established and subsystem requirements will be identified.  In the second task, Busek will integrate an magnesium vapor propellant Hall thruster with a wire feed system.  In the third task, the integrated system will be tested in Busek facilities.  In the fourth task, the Applied Research Laboratory (ARL) at Penn State University will develop a powder feed system capable of fueling both medium and high power thrusters.  A fully integrated system sized for NASA needs will be developed and characterized in Phase II.
The Goal of this STTR is to develop a high speed, high power, waveguide based modulator (phase and amplitude) and investigate its use as a pulse slicer.  The key innovation in this effort is the use of potassium titanyl phosphate (KTP) waveguides making the high power, polarization based waveguide amplitude modulator possible.  Furthermore because it is fabricated in KTP, the waveguide component will withstand high optical power and have a significantly higher rf modulation figure-of-merit (FOM) relative to lithium niobate.
The high-intensity level acoustic load generated by large launch vehicle lift-off propulsion is of major concern for the integrity of the launch complex and the vehicle payloads. The currently practiced computational methods are unable to offer the reliability of both the noise generation mechanism and acoustic environment. In order to uniquely address both of these critical aspects, the proposed approach will unify the physics of noise production with propagation and structural interactions. This method will utilize hybrid LES/RANS modeling established in NASA production flow solvers (Loci-Chem and OVERFLOW) capable of realistic descriptions of flow-acoustic interactions. A non-dissipative acoustic Boundary Element Method (BEM) will be coupled with the well-resolved noise source for high-quality acoustic environment predictions, equipped with the Fast Multipole Method (FMM) for solution acceleration. In Phase I, merits of the proposed approach will be investigated for plume impingement problems. A high-performance simulation architecture, easy user interfaces and post-processing utilities will be developed for complex geometries and efficient large-scale simulations.  Phase II efforts will involve refinements and extensive evaluations for high-resolution noise source modeling, transition of mixed speed flow regimes, wave propagation through non-uniform flow, and supercomputing capabilities facilitating new insights into rocket exhaust acoustic loading and comprehensive noise suppression analysis.
In this STTR Phase I effort, Los Gatos Research (LGR) and Professor Scott Sanders (Mechanical Engineering Department, University of Wisconsin ? Madison) propose to develop a highly-accurate sensor for high-purity oxygen determination.  The analyzer, which is based on near-infrared tunable diode laser absorption spectrometry (TDLAS) and LGR's patented Off-Axis Integrated Cavity Output Spectrometry (Off-Axis ICOS), will be capable of rapidly quantifying high-purity oxygen (95 ? 100 &#37;) with very high accuracy (to better than 1 0.05 &#37;), minimal calibration, and no zero drift.  The analysis will be completely specific and exhibit no measurable cross-interferences from other background species (e.g. argon, nitrogen, water vapor, CO, CO2, or small organics).  Moreover, the analyzer will be low-power, battery-operable, require no consumables, and sufficiently compact and robust for adaptability to future space missions.   The high-purity oxygen sensor will help characterize NASA oxygen generators for breathing and propulsion applications.
This proposal describes the preliminary development of surface acoustic wave (SAW) based hypergolic fuel sensors for NASA application to distributed wireless leak detection systems. SAW devices are a platform technology for passive wireless sensing of numerous possible measurands.
Balcones Technologies, LLC proposes to adapt technologies developed by and resident in The University of Texas at Austin Center for Electromechanics (CEM) in the areas of superconducting Trapped Field Magnet (TFM) motors, magnetic bearings, terrestrial and space-based flywheel energy storage systems, and air-core generators to address STTR 2010-1 Subtopic T3.01, Technologies for Space Power and Propulsion.  In particular, our team will develop a concept design for high field intensity superconducting Trapped Field Magnetic Bearings (TFMB) for a space-based flywheel system, including magnetic field activation and cryogenic cooling subsystems.  The design will focus on exploiting approximately $47M of CEM technology to develop commercially viable superconducting magnetic bearings that significantly exceed the force density (developed force per unit of system mass) of today's magnetic bearings and will optimize the design for the space flywheel application rather than adapt terrestrial designs for space.

Relevant features of our anticipated solution include:
?	Much lower power usage than conventional non-superconducting magnetic bearings.
?	Much stiffer magnetic bearings than conventional non-superconducting magnetic bearings.
?	Much stiffer magnetic bearings than current superconducting magnetic bearing technology.
?	Capable of high rotational speeds.
?	Operation at magnetic fields of 2.5-3 Tesla to allow demonstration within a normal 24 month Phase II STTR, but with a design approach amenable to future systems at ~ 10 Tesla .
?	Air-core magnetic circuit design (e.g., does not employ iron to guide magnetic fields which limits magnetic fields to 2 Tesla or less and practically limits operational fluxes to ~ 1 Tesla).
?	TFM charging system to inject the magnetic field, most likely based on a system to cool the magnet while maintaining an applied charging field, but could also be a pulse charging system of a pre-cooled TFM.
Solid oxide fuel cells and electrolyzers are promising electrochemical devices for space and terrestrial applications due to their high power densities and clean operation.  Furthermore, proton-conducting oxides have the potential to allow lower operational temperatures and promote more reliable and longer-lived devices?both valuable attributes for space applications?however, practical devices are not yet realized because of insufficient proton mobility at moderate temperatures.  Phenom Technologies, Inc. has identified a new non-thermal technique to dramatically enhance the mobility of protons in solid oxides using resonant infrared irradiation to excite molecular O-H vibrations in the material.  In our earlier work, we have shown that this photo-enhanced hydrogen transport effect can increase the proton diffusion rate in solid oxides by nine orders of magnitude.  In this Phase I STTR proposal, we will build on our established research to complete a proof of concept study and lay the foundation for Phase II prototype development of a "photo-enhanced" solid oxide electrolyte for fuel cells and electrolyzers.  This study will address NASA's need for more reliable and efficient solid oxide electrochemical components for clean renewable energy systems.
The innovation proposed here is a framework for the incorporation of high performance, high fidelity computational fluid dynamics (CFD) techniques to enable accurate and robust simulation of unsteady turbulent, reacting or non-reacting flows involving real or ideal fluids with practically useful turnaround times. The emphasis will be on a major improvement in efficiency and scalability of Loci-STREAM which is a CFD code already in use at NASA.
Surface exploration of planetary environments with current robotic technologies relies heavily on human control and power-hungry active sensors to perform even the most elementary low-level functions. Ideally, a robot should be capable of autonomously exploring and interacting within an unknown environment without relying on human input or suboptimal sensors.
Infrared spectroscopy is an invaluable detection and measurement tool intensively used in Earth Science, Solar Physics and Astrophysics experiments pursued from satellite platforms. The geometrical characteristics and sensitivity of satellite infrared spectroscopy systems is often determined or limited by their optical elements. Improvements in optical components allow one to reduce the mass and increase the sensitivity of the system.  Here we propose a compact, high sensitivity sensor based on the integration of HgCdTe photodiode detection technology with micro-opto-electromechanical-systems (MOEMS) technology. This combines HgCdTe's high sensitivity with an inexpensive MOEMS lamellar grating interferometer (LGI) device. During Phase I we will perform the optical and mechanical design of the lamellar grating elements, identify suitable processes for fabrication, demonstrate etch processes compatible with the LGI design, and demonstrate prototype lamellar elements. During Phase II, we will further optimize the LGI components, minimize their size, weight and power, and integrate them into an operational LGI. A prototype LGI instrument will be deployed in an environment with controlled input of a variety of low-level test gases. We will develop and test detection-identification algorithms and build a characterization set-up to assess the LGI's sensitivity, selectivity and probability of detection.
Middle-wave infrared (MWIR, 3-5 ??m) photodetectors are of great importance in numerous NASA applications, including thermal remote sensing for carbon-based trace gases (CH4, CO2, and CO), heat capacity mapping for earth resource locating, environment and atmosphere monitoring, and IR spectroscopy. However, existing MWIR photodetectors are require a low operating temperature, below 77K to achieve high photodetectivity (D*).
Prime Research LC (PPLC) and Virginia Tech (VT) propose to develop an energy harvesting wireless strain node technology that utilizes single-crystal piezoelectric fiber-based energy harvesting, highly sensitive and low power piezoresistive strain gages, and ultra wide-band (UWB) ultra low power radio communication. Single crystal piezoelectric fibers promise to improve piezoelectric harvesting power density by a factor of 4 &amp;#150; 5 &amp;#61620; while the ultra wide-band radio (UWB) and piezoresist
Advancements in technology and contractions in budgets are driving constant increases in spacecraft "capability density." These factors are motivating the design of small spacecraft capable of generating and communicating large amounts of data, over great distances, at low cost.
NASA and many others often rely on delivery of cryogenic hydrogen to meet their facility needs. NASA's Stennis Space Center is one of the largest users of hydrogen, with the LH2 used as a fuel for cryogenic rocket engine testing.
Nanosatellites are receiving increased interest since they are proving reliable for surveillance, communication and other space missions. Also, the possibility of launching "constellations" of them offers unique capabilities for low-cost experimentation, sensing and communications in space.
Agiltron proposes to develop an extremely compact and high sensitivity uncooled near- and mid-infrared (NMIR) spectrometer engine for planetary compositional analysis and mapping. In this program, we will produce lead salt-based IR detector materials with single crystalline-like oriented thin film structures which will increase the majority charge carrier mobility by two orders of magnitude.
An opportunity to boost energy efficiency in homes and buildings exists through the design of functional radiative properties in glass and other building materials. Current surface materials ignore or take first-order approaches to complicated spectral behavior, leading to sub-optimal properties.
The goal of this proposed research is to advance the development of biological in situ resource utilization for NASA's space exploration programs.  We plan to build a foundation to use synthetic biology to engineer microorganisms to extract metals from naturally occurring extraterrestrial regolith. 
					
We propose to create a novel growth medium designed to mimic the lunar regolith ice discovered at the south pole of the moon by the LCROSS mission.  We will develop a bioleaching column for this simulant to purify metals for consumable production in space.  We will characterize known biomining organisms to leach this simulant.  Finally we will study the biochemical processes taking place in the leaching of the regolith to be able to improve the metabolism of these organisms in the future.

In addition, will produce a database of organisms involved in biomining on Earth and the geologies and substrates that they have been found on.  This database can be used as a tool to find undersampled mine sites that may contain novel organisms suitable for biomining in space.

We then plan to develop a conceptual bioreactor which is designed to extract metals from regolith in space.  We will perform a trade study of the mass, productivity, cost and energy requirements of such a bioreactor.

Later phases of the research will involve characterization of the important enzymes involved in biomining in key organisms, adding to the limited existing knowledge of these pathways and leading to creation of a synthetic biological system for efficiently engineering them, which we will use to optimize these organisms for extracting relevant substrates in relevant space-settlement-like conditions. This further research will also include growth on Mars-like simulant regoliths, as well as improvement of the bioreactor model in a series of increasingly durable and realistic prototypes that will undergo both physical and functional testing.
It is critically important that a physics based ADR SAAT prototype be developed that can be refined and used across the community to study and analyze various remote (non-contact) orbital debris stabilization concepts and architectures prior to investing significant commercial or public funding into technology development, technology and system level demonstrations, and development and deployment of an Orbital Debris Stabilization/ADR system. Under this STTR, PA&amp;S plans to develop a prototype Ac
A spacecraft thermal control system must keep the cabin (both air and its structure if manned) and electronic equipment within a narrow temperature range even though the environment may vary from very cold to warmer than room temperature. Since water is safe to use and an excellent coolant (other than its high freeze point and volumetric expansion during freeze), a water coolant loop often is used to transport heat to or from the spacecraft via heat exchangers to the heat sink systems that reje
The utility of airborne remote observation of hypersonic reentry vehicles was demonstrated by the NASA Hypersonic Thermodynamic Infrared Measurement (HYTHIRM) project. High spatial resolution infrared imagery was collected using available technology manned aircraft.
The proposed innovation is a heterogeneous multi-robot team developed as a platform for effective subsurface planetary exploration. State-of-art robotic exploration is based on single-robot systems with human controllers augmented by limited automation.
Firefly, in collaboration with Rochester Institute of Technology, proposes an STTR program for the development of a space solar cell having record efficiency exceeding 40&#37; (AM0) by the introduction of nanowires within the active region of the current limiting sub-cell. The introduction of these nanoscale features will enable realization of an intermediate band solar cell (IBSC), while simultaneously increasing the effective absorption volume that can otherwise limit short circuit current generated by thin quantized layers. The triple junction cell follows conventional designs comprised of bottom Ge cell (0.67eV), a current-limiting middle GaAs (1.43eV) cell, and a top InGaP (1.90eV) cell. The GaAs cell will be modified to contain InAs nanowires to enable an IBSC, which is predicted to demonstrate ~45&#37; efficiency under 1-sun AM0 conditions. The InAs nanowires will be implemented in-situ within the epitaxy environment which is a significant innovation relative to conventional semiconductor nanowire generation using ex-situ gold nanoparticles. Successful completion of the proposed work will result in ultra-high efficiency, radiation-tolerant space solar cells that are compatible with existing manufacturing processes. Significant cost savings are expected with higher efficiency cells which enables increased payload capability and longer mission durations.
Intelligent Fiber Optic Systems Corporation (IFOS) proposes an innovative fiber optic-based, multiplexable, highly ruggedized, integrated sensor system for real-time measurement and monitoring of temperature in an Ablative Thermal Protection System (TPS).  Such measurement will allow for an effective estimation of temperature gradient and subsequent calculation of heat flux. IFOS will initially develop such a system for thermal monitoring in Small Probe applications. However, the technology will readily be applicable to other NASA vehicle applications where TPS is employed. The IFOS fiber optic sensors will incorporate Fiber Bragg Gratings (FBGs).  These sensors are extremely light-weight, small, electromagnetically immune, and electrically passive.  Multiple sensing FBGs can be fabricated on a single fiber for simplified design and reduced cost.  The proposed fiber optic sensing technology is highly sensitive and accurate. It is also low-cost and lends itself to high-volume production.  In the Phase I, IFOS will perform a feasibility study of its proposed temperature measurement and monitoring system.
The challenges of designing, developing, and fielding man-rated propulsion systems continue to increase as NASA's mission moves forward with evolving solid propulsion requirements.  Recent developments in simulating solid rocket motor environments include Lagrangian particle tracking, particle combustion models, dynamic particle drag and breakup models, and two phase impingement phenomena.  These advances are demonstrating success in numerically simulating solid motor environments, but evolutionary innovations leading to more realistic simulations are required.  In particular, transient ignition phenomena, such as grain surface heating, initiation of surface reactions, and transition to steady burning, have not yet been addressed.  Consideration of these transient flow aspects is extremely important for analyzing ignition delay, pressure buildup, nonuniform grain recession, and overall combustion behavior.  Our research will combine existing two phase flow tools for solid motors with a grain heating and ignition model to produce software tools for simulating transient ignition phenomena and the subsequent flow development.  These products will ultimately provide NASA with the important capability to simultaneously analyze solid propellant ignition and combustion, heat transfer, and grain burnback within a unified framework.  We will demonstrate feasibility using a two phase solid propellant ignition model for a simple grain shape in the TRL range of 3-4.
The objective of this Phase I STTR program is to adapt NanoSonic's HybridSil&amp;#153; nanocomposite technology for the creation of next generation highly flexible, fire resistant foams capable of extended operational lifetimes within demanding aerospace platforms. Phase I optimized nanocomposite foams would have immediate utility within a broad spectrum NASA applications as non-halogenated fire proofing, insulative, de-icing, and energy absorptive materials with tailorable breathabilities.
The proposed innovation provides a way to design low flow coefficient inducers that have higher cavitation breakdown margin, larger blade angles, thicker more structurally robust blades, and better off-design flow stability than the current state-of-the-art designs.  The technology will increase the structural, stability, and suction margin of inducers designed in the currently acceptable flow coefficient range of about 0.06 to 0.1.  In addition, it will allow for stable and structurally robust designs at much lower flow coefficients than previously thought possible (down to at least 0.02) for the capability to operate in near zero net positive suction pressure inlet environments.  The innovation is based upon a synergistic coupling of Concepts NREC's patented cavitation control device with a new blade design approach that takes full advantage of the CCD's characteristics for optimal suction performance.  The technology significantly enhances the capability of rocket engine systems through increased thrust-to-weight, specific impulse, simplicity, operational safety, and turbopump life.  It will also reduce turbopump and propellant tank weight and system costs by eliminating boost pump systems and allowing for lighter lower pressure tanks.
In Phase 1, Intelligent Fiber Optic Systems (IFOS) successfully demonstrated a Fiber Bragg Grating (FBG) based integrated Structural Health Monitoring (SHM) sensor system capable of providing in-situ crack detection, location, damage quantification and validation of structural models. The system offers advanced features to perform non-contact, non-destructive dynamic testing of composite structures.
Firefly, in collaboration with Rochester Institute of Technology, proposes an STTR program for the development of a space solar cell having record efficiency exceeding 40&#37; (AM0) by the introduction of nanowires within the active region of the current limiting sub-cell. The introduction of these nanoscale features will enable realization of an intermediate band solar cell (IBSC), while simultaneously increasing the effective absorption volume that can otherwise limit short circuit current generat
The innovation of our Phase II STTR program is to develop and provide to NASA automatic mesh generation software for the simulation of fluid flows using Reynolds-Averaged Navier-Stokes codes. As a result of the successful Phase I work, these new tools are now capable of generating high-quality, highly-stretched (anisotropic) meshes in boundary layer regions and transition smoothly to inviscid flow regions, even in an adaptive context. The significance is that our method has the ability to generate a boundary layer mesh while keeping intact the previous adaptation procedures from non viscous simulations. This leads to a natural coupling between boundary layer mesh generation and anisotropic mesh adaptation. All of the Phase I objectives were met and all tasks were completed successfully. The Phase II project will include improvements in surface remeshing, coding for optimal speed and increased robustness of the solvers, adding a mesh optimization module, providing a link to general CAD packages, include unsteady coupling where the boundary layer mesh refinement evolves in time, conduct further validation and verification on NASA models by running flow cases with our solver, documenting the project, and delivering the new meshing software to NASA.
LongWave Photonics proposes a terahertz quantum-cascade laser based swept-source optical coherence tomography (THz SS-OCT) system for single-sided, 3D, nondestructive evaluation (NDE) of non-conductive materials.  The THz SS-OCT system uses a frequency tunable QCL array to generate an interferometric signal between a reference mirror, and a sample.  An algorithm is used to transform this signal into depth information of the interfaces within the sample.  Phase I demonstrated the feasibility of measuring the interfaces of a dielectric on metal sample.  In Phase II, we propose to demonstrate a complete scanning system for 3D imaging by upgrading the optics and mechanics.  Improvements in the power levels and frequency bandwidth of the QCL source are expected to greatly improve the depth resolution and signal to noise ratio of the system.  The milliwatt power levels of the QCL are expected to result in fast scan speeds.  Operation of the SS-OCT system is expected to be relatively simple as the QCL is an electrically pumped, solid state source of terahertz radiation, capable of operation in a compact, high reliability crycooler as demonstrated in Phase I.
The innovation proposed here is a high performance, high fidelity simulation capability to enable accurate, fast and robust simulation of unsteady turbulent, reacting flows involving cryogenic propellants (such as LOX/LH2 and LOX/LCH4). The key features of this proposed capability are: (a) Hybrid RANS-LES (HRLES) methodology, and (b) flamelet modeling for turbulent combustion incorporated in a proven existing solver called Loci-STREAM which has been developed by the proposing personnel under fu
Analogous to the CubeSat standardization of micro-satellites, the SPORE flight system architecture will utilize a modular design approach to provide low-cost on-orbit operation and recovery of small payloads.  The Phase 1 investigation will evaluate a scalable flight system architecture consisting of a service module for on-orbit operations and deorbit maneuvering, and an entry vehicle to perform entry, descent and landing (EDL).  The design space for the SPORE system architecture is shown in Figure 1.  Flight system designs capable of accommodating payload volumes ranging from 1-unit (1U) dimensions of 10x10x10 cm to 4U dimensions of 20x20x20 cm will be investigated.  The proposed system will be capable of flight operations and return from low-Earth orbit (LEO) and geosynchronous transfer orbit (GTO).  The SPORE design can be launched as a primary or secondary payload into LEO or GTO, or it can be deployed from the International Space Station (ISS).
HJ Science &amp; Technology, Inc. and the University of Texas at San Antonio propose a joint venture to demonstrate the feasibility of a mobile "lab-on-a-robot" platform capable of in-situ, high throughput, and simultaneous identification and characterization of universal classes of ions, molecules, and biomolecules for NASA planetary and small body surface chemistry studies.
&lt;p&gt;
	Design and prototype a lightweight, precision-deployable mast for the Ka-band Radar Interferometer (KaRIn) antennas in the Surface Water and Ocean Topography (SWOT) mission.&lt;br /&gt;
	Performance goals are:&lt;br /&gt;
	Azimuth pointing deployment precision:&amp;nbsp; &amp;lt; 0.11&amp;deg;&lt;br /&gt;
	Elevation stability:&amp;nbsp; &amp;lt; 16 milli-arcsec&lt;br /&gt;
	First mode frequency:&amp;nbsp; &amp;gt; 10 Hz&lt;br /&gt;
	Technologies including a precision deployable mast containing a multi-joint cable driven precision latch mechanism and a pointing adjustment mechanism.&lt;/p&gt;
&lt;p&gt;
	Advance the state of the art in continuous wave and pulsed IR distributed feedback (DFB) and optical parametric generation (OPG) lasers between 2.8 and 3.5 &amp;mu;m to measure key atmospheric chemical species including OH, H2O, H218O, HDO, CH4, 13CH4, CO2, 13CO2, CH2O, C2H6.&lt;br /&gt;
	Combine new lasers with integrated optics and electronics to enable the use of new single mode light sources aboard satellite and UAV platforms to support GACM and ASCENDS.&lt;/p&gt;
&lt;p&gt;
	Develop high electron mobility transistor (HEMT) amplifier based heterodyne radiometers to provide high sensitivity at millimeter and submillimeter wavelengths with high spectral resolution for molecular line detection.&lt;br /&gt;
	Performance goals are:&lt;br /&gt;
	Low system noise temperature:&lt;br /&gt;
	&amp;lt; 280K Single Sideband at 230 GHz&lt;br /&gt;
	&amp;lt; 650K Single Sideband at 640 GHz&lt;br /&gt;
	Wide spectral coverage:&lt;br /&gt;
	180-270 GHz (for tropospheric measurements)&lt;br /&gt;
	620-660 GHz (stratospheric measurements)&lt;br /&gt;
	Sideband separation:&amp;nbsp; &amp;gt; 15 dB&lt;br /&gt;
	Amplifier front-end operating temperature:&amp;nbsp; 20K&lt;/p&gt;
&lt;p&gt;
	Achieve scalability of a 1.26 &amp;micro;m fiber Raman amplifier (FRA) to 5W with an optical-to-optical efficiency of &amp;gt;50&#37;, that is compatible with ITT&amp;rsquo;s modulated CW Laser Absorption Spectrometer (LAS) in support of the ASCENDS mission.&lt;br /&gt;
	Advance the retrieval/software tools to demonstrate the retrieval of dry air mixing ratio of CO2 using simultaneous active O2 and CO2 integrated column measurements.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop and demonstrate a next-generation digitally calibrated, highly scalable, L-band Transmit/Receive (TR) module to enable a precision beamforming SweepSAR architecture for interferometric radar applications and phase-stable electronically steered arrays.&lt;br /&gt;
	0.01 dB amplitude, 0.06 degrees phase.&lt;br /&gt;
	Develop technologies to enable real-time on-board beamforming capability for use in phase-stable array antennas:&lt;br /&gt;
	High efficiency L-band TR module.&lt;br /&gt;
	Closed-loop transmit and receive calibration circuitry.&lt;br /&gt;
	On-board real-time digital calibration and beamforming.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Fabricate Si immersed gratings for IR (1150 &amp;ndash; 6500 nm) spectroscopy to support ground-based, airborne, and space-based infrared spectrometers.&lt;br /&gt;
	These devices offer substantial advantages in compactness, formatting, and efficiency over other dispersive devices and have 3.44 times the resolving power of a conventional front-surface device for a grating of a given size.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop a wideband (500 MHz) L-band phased-array antenna for airborne Synthetic Aperture Radar (SAR) applications based on a novel approach that will make possible meter-resolution and fully polarimetric measurements of permafrost and above ground biomass.&lt;br /&gt;
	The development will enable a new generation airborne Digital Beamforming Synthetic Aperture Radar (DBSAR-2) instrument that can significantly enhance the scientific measuring capability of existing SAR systems while providing critical data for carbon cycle studies.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	? Develop the technology for a compact, space-qualifiable laser transmitter for a lidar operating at 1.65 5 to enable Earth observation CH4 measurements.&lt;br /&gt;
	? Reduce the risk, cost, size, mass and volume of the CH4 lidar instrument by scaling the laser power of the existing laboratory breadboard.&lt;br /&gt;
	? Demonstrate and validate simultaneous, high sensitivity, methane and CO2 measurements using the proposed methane lidar and an operational CO2 lidar.&lt;/p&gt;
&lt;p&gt;
	Design and fabricate a space-qualifiable, fully conductively cooled, 2-micron pulsed laser breadboard meeting the projected 3-D Winds mission requirements.&lt;br /&gt;
	Utilize improvements in key technologies including high-power, long life space proven 804 nm pump diodes; derated diode operation, and heat pipe conductive cooling.&lt;/p&gt;
&lt;p&gt;
	Develop a HgCdTe avalanche photodiode (APD)&amp;nbsp; SWIR/IR linear mode photon counting (LMPC) array detector system in support of the LIST lidar.&lt;br /&gt;
	Provide a new type of SWIR/IR focal plane array with near zero read-out noise and fast frame rate for IR spectrometers and cameras for other Earth science decadal missions and scientific and commercial applications.&lt;/p&gt;
&lt;p&gt;
	Develop an etalon front end receiver (FIDDL) and combine it with the Optical Autocovariance Wind Lidar (OAWL) for an integrated direct detection (IDD) wind lidar.&lt;br /&gt;
	Demonstrate the IDD hybrid system measuring winds from both molecular and aerosol returns using a single lidar.&lt;br /&gt;
	The hybrid system will significantly reduce the size and cost of a 3D Winds mission (on the order of 20-30&#37; based on aperture size) compared to the current hybrid 2-laser approach.&lt;br /&gt;
	Performance goals are &amp;lt; 1 m/s wind estimate precision for the etalon sub-system.&lt;/p&gt;
&lt;p&gt;
	Develop a compact, efficient 2&amp;micro;m pulsed laser for a lidar instrument to make accurate, high-resolution atmospheric CO2 column measurements in support of the ASCENDS mission.&lt;br /&gt;
	Develop a pulsed 2&amp;micro;m laser that is based on a Thulium fiber-laser pumped Holmium (Ho) solid state laser in a Master Oscillator Power Amplifier (MOPA) configuration.&lt;br /&gt;
	Demonstrate 65mJ at 50Hz needed for the space&amp;nbsp; Integrated Path Differential Absorption (IPDA) instrument in a robust prototype format.&lt;/p&gt;
&lt;p&gt;The Biomedical Engineering and Research Laboratory is working with the NASA Life Support group and BCS Life Support to improve the safety of the environmental control units (ECUs) used in the self-contained atmospheric-protective ensemble (SCAPE) suits at Kennedy Space Center (KSC). ECUs are liquid-air-based backpacks that allow operators to work in hazardous environments for up to 2 hours. Though ECUs have been used at KSC with great success for over&amp;nbsp;30 years, some ECU deficiencies have required mitigation.&lt;/p&gt;&lt;p&gt;Because the breathing commodity is liquid, the liquid pickup in the dewar can come out of the fluid if the dewar is near the end of its service life and if the operator lies on his side. This can prevent air from flowing in the SCAPE suit. Furthermore, the ECUs have no liquid level sensors to indicate to the operator that the unit is running low on air. BCS Life Support has invented a novel liquid pickup system that will allow the ECU to operate safely in the horizontal position. The system has a liquid level sensor that will warn the operator when the commodity is at 25&#37;.&amp;nbsp;The overall objective for this project was to evaluate two candidate alternatives for the existing Propellant Handler&amp;rsquo;s Ensemble (PHE) escape ventilator.&lt;/p&gt;
&lt;p&gt;This design uses regular drinking water that is pumped through two filters to produce, in minutes, sterile, ultrapure water that meets the stringent quality standards of the United States Pharmacopeia for Water for Injection (Total Bacteria, Conductivity, Endotoxins, Total Organic Carbon). The device is 2.2 lbs (1kg) and 10L x 5W x 3H inches (25L x 13W x 7.5H cm) in its storage configuration. This handheld device produces one liter of medical-grade water in 21 minutes. Total production capacity for this innovation is expected to be in the hundreds of liters.&lt;/p&gt;&lt;p&gt;The device contains one battery powered electric mini-pump. Alternatively, a manually powered pump can be attached and used. Drinking water enters the device from a source water bag, flows through two filters, and final sterile production water exits into a sealed, medical-grade collection bag. The collection bag contains pre-placed crystalline salts to mix with product water to form isotonic intravenous medical solutions. Alternatively, a hypertonic salt solution can be injected into a filled bag. The filled collection bag is detached from the device and is ready for use or storage. The entire system can then be flushed, sealed, and radiation-sterilized.&lt;/p&gt;
&lt;p&gt;Controlling air traffic on all temporal and spatial scales &amp;ndash; from a single aircraft to the entire airspace &amp;ndash; can be formally stated as a dynamic, high-dimensional optimization problem with many objectives and constraints based on physics, economics, information, and other considerations. Especially in the future NAS, attempting to find the optimal solution to such problems as they arise during operations would often violate practical constraints such as computation time and/or communication resources. The issue is how to find the best solution subject to such constraints on the solution-finding algorithm. We propose to approach this as a multilevel optimization problem, where a complexity measure F maps the combination of s and an algorithm alpha (e.g., an algorithm that searches over a specified class of fine-grained traffic flows all having a given large-scale flow) to whether applying alpha to s would violate the practical constraints. Given F, the higher level optimization problem identifies the member of a set A of candidate algorithms that has best likely value of the objective functions, subject to provided practical constraints on the algorithm. A lower level optimizer then runs that algorithm and by construction is likely to do so within the given practical constraints. The technical approach will use mathematical programming, Probability Collectives (PC), and Machine Learning (ML), among other areas. The ultimate goal is a methodology and tools for use both in research and as a decision-making aid for all system participants, including aircraft pilots and automatic systems, air traffic controllers, and airlines.&lt;/p&gt;
&lt;p&gt;Partnering with National Institute of Occupational Safety and Health (NIOSH) to develop several cryogenically based life support technologies to be used in mine escape rescue scenarios. Technologies developed for mine rescue directly benefit future NASA rescue and ground operation missions. Projects Include: advanced liquid air self contained breathing apparatus (SCBA) packs, liquid air storage and fill stations, liquid oxygen rebreather technologies, liquid air based refuge chamber technologies.&lt;/p&gt;&lt;p&gt;Research under this project will explore cryogenic breathing air and oxygen technology used by NASA for application to mining breathing air supplies suitable for use in refuge alternatives. Specific objectives are to conduct a feasibility study for cryogenic air and oxygen application, to fabricate, test, and document operational prototype supply systems, and to adapt and evaluate systems for retrofit into, or for use in conjunction with, existing refuge chambers. Final demonstration of the system may occur in an operating underground coal mine or in NIOSH&amp;rsquo;s Safety Research Coal Mine.&lt;/p&gt;
&lt;p&gt;The goal for this project included developing the capability to store liquid air for long periods of time without commodity boiloff and oxygen enrichment using cryocoolers and condense the vapor in the dewar as it heat leaks in over time.&amp;nbsp;Seeing the commercial potential of this project, two companies donated a modified 300 L dewar and a cryocooler. Phase I testing demonstrated that the concept works. Phase II was a long-term test during which the mixture ratio was maintained within the sampling error for over 120 days, demonstrating the viability of long-term storage. The goal in Phase III was to determe if the&amp;nbsp;dewar fill level affects the cryocooler energy requirements.&lt;/p&gt;&lt;p&gt;Testing successfully demonstrated the ability to store liquid air over long periods (6+ months) without boiloff or oxygen enrichment. The laboratory test prototype is currently in use at an operational facility and is doing very well. &amp;nbsp;Full operational implementation of this technology at KSC is currently being considered. Implementation is expected to lead to significant operational cost savings over current operational methods.&lt;/p&gt;
&lt;p&gt;Using biologically-inspired neuromorphic optic flow algorithms is a novel approach in collision avoidance for UAS. Traditional computer vision algorithms rely on solving nonlinear partial differential equation systems to estimate optic flow which is a computationally expensive task. Neuromorphic algorithms instead make use of lessons learned in biology to solve these problems in a more efficient manner. An example is the fly&amp;#39;s motion detector, which can be modeled by a system that uses a set of locally calculated, parallel spatio-temporal correlations for a set of velocities determined by the input sampling rates and flying speeds. Correlation results are interpreted as likelihood for a motion direction and speed. Stages of obstacle detection and tracking can temporally and spatially integrate these likelihoods to increase the signal-to-noise ratio, and in turn the detection rate. In addition to its computational efficiency, the proposed neuromorphic solution is more stable and noise tolerant than solving a nonlinear optimization problem. Even if single computational nodes get corrupted due to functional or structural failures in the hardware, the performance of appropriately designed parallel, distributed neuromorphic algorithms degrades gracefully. Neuromorphic algorithms are commonly implemented using software running on general-purpose multicore/graphic processing unit systems. This approach, though flexible, can have significant overhead in terms of power, performance, and is not easily portable across platforms, therefore reducing its scope of applicability. In the second phase, we will port the neuromorphic algorithms to field programmable gate arrays (FPGAs) and application specific integrated chips (ASICs). This will allow us to meet demanding performance requirements needed in UAS such as fast processing, low weight, low power consumption, as well as robustness to hardware failure.&lt;/p&gt;
&lt;p&gt;Future human spaceflight missions will occur with crews and spacecraft at large distances, with long communication delays, to the Earth. The one-way light-time delay to the Moon is 1.3 seconds, which is sufficient to make some scenarios (e.g. for landing) difficult or impossible to conduct from Earth. One-way communication delays to human exploration destinations such as Near Earth Asteroids (NEA) at close approach range from seconds to minutes. The one-way light-time delay to Mars ranges from 3 minutes (at conjunction) to 22 minutes (at opposition). As the communication delays increase, the crews in the spacecraft must execute, and manage, much of the mission themselves. Throughout the course of a mission, as distances increase, NASA must continue to migrate operations functionality from the MCC flight control room to the vehicle for use by the crew. The role of the ground control teams and systems will evolve away from real-time support to more long range planning, diagnosis, analysis and prognostics support role. While the vehicle systems and crew must take on the role of daily schedule execution, planning, and systems management from onboard. Both ground and vehicle systems will require automation to maximize crew functionality, minimize unnecessary overhead, and reduce operating costs. This project is to understand the impacts of increasing communications time delays on operations and to develop technologies to mitigate the impacts.&lt;/p&gt;
&lt;p&gt;The objective of this project is to mature technologies and systems that will enable future Extravehicular Activity (EVA) systems. Advanced EVA systems have applicability to all future human spaceflight missions. Advanced EVA systems have applications to current operations on the International Space Station (ISS), to extended operations on ISS past 2020, future missions to Low Earth Orbit (LEO) such as satellite servicing, missions beyond LEO such as exploration of asteroids, and surface exploration missions to the Moon or Mars. An EVA system would be a significant element of any future human exploration mission and will enable suitport operations in a Deep Space Habitat or Multi-Mission Space Exploration Vehicle (MMSEV). The Human Exploration Framework Team (HEFT) ranked EVA systems as one of the top five needed areas of future development for human space flight. The goal is to produce real cost, performance, and reliability data through building and testing high fidelity systems, culminating in a flight demonstration on ISS of an exploration Extravehicular Mobility Unit (EMU). The current plan leading to this flight demonstration consists of subsystem demonstrations of increasing fidelity. These demonstrations would produce hardware and systems that could then be combined into a complete EVA system which would be used in human thermal-vacuum chamber tests and finally in a flight demonstration.&lt;/p&gt;
&lt;p&gt;The Nonlinear adaptive filters (NAF) can learn deterministic gyro errors and cancel the error&amp;rsquo;s effect from attitude estimates. By completely canceling deterministic gyro errors, NAFs improve sensor performance. The project includes: Simulation of NAF (and comparison to state-of-art); Mathematical analysis to optimize NAF tuning; Development of high-fidelity gyro models, especially modeling thermal effects. Milestones include Simulation Development and Thermal Vacuum Testing with several CubeSat-grade gyros.&lt;/p&gt;
&lt;p&gt;The objectives of the project is the development of single emitter and multiple emitter injectors for doped kerosene; to develop a fundamental understanding of droplet transport, evaporation, and mixing in the complex swirling flow fields required for meso-scale flame stabilization; and the system integration of meso-scale thrust chamber with electrospray fuel injection system. A single emitter electrospray configuration will be developed and the performance benchmarked using Phase Doppler Particle Analysis to determine the droplet size distribution as a function of flow rate. The nature of droplet transport and evaporation at the meso-scale will be studied using non-intrusive laser based techniques. The electrospray injector will be integrated into the existing heat regenerating thrust chamber and fired with kerosene/H2O2.&lt;/p&gt;
&lt;p&gt;Develop an Atom Interferometry-based gravity wave detector (vs Optical Interferometry). Characterize a high power laser. Use Goddard Space Flight Center Mission Design Lab to study a single flyer with boom&amp;nbsp; and developed cost estimate. Also funded a study at Stanford on Large Momentum Beam Splitters applications for Detection of Gravity Waves using Atom Interferometry.&lt;/p&gt;
&lt;p&gt;Integration of graphene as the top metal on GaN Schottky. This will replace platinum, which is 50&#37; transparent at the desired wavelength, with graphene, which has higher mobility and much higher transparency (&amp;gt;90&#37;). Develop a fabrication process for GaN Schottky and a chemical vapor deposition process for large area graphene. Develop a process to cleanly integrate single or multilayer graphene on GaN devices and pattern them. Develop a characterization scheme to determine the Schottky barrier height of graphene and device QE.&lt;/p&gt;
&lt;p&gt;This project involves modulating a commercial, distributed feedback, laser with a pseudo random code. It involves the optimization of laser pulse width versus the pumping of the fiber laser to extract the maximum amount of energy before encountering damaging nonlinear effects in the fiber amplifier.&amp;nbsp; It also explores the impact of nonlinearities in the noise on measurement precision.&lt;/p&gt;
&lt;p&gt;Incorporate PF into GSFC&amp;rsquo;s Orbit Determination Toolbox (ODTBX). Augment PF with ODTBX&amp;rsquo; unique ability to partition error sources into subspaces for analysis. Utilize multi-core server to facilitate fast simulation of large particle populations.&lt;/p&gt;
&lt;p&gt;The project is to build a grazing incidence mirror for hard X-rays (E&amp;gt;20 keV) using a &amp;ldquo;scotch-tape&amp;rdquo; design, in which a thin plastic tape with a specific thickness profile and a multilayer reflective coating is tightly wound into a roll. Key challenges are (a) to find a suitably smooth tape substrate (this has been done), (b) to wind a large number of tape shells onto the smooth metal centerpiece without introducing and accumulating shape irregularities, and (c) to give the tape the variable thickness profile in order to achieve the desired optical figure. Our immediate goal is to demonstrate the idea feasibility by building a crude conical X-ray concentrator. If successful, we will aim at building and flying a mirror prototype on a balloon and then proposing for an Explorer mission or MOO. The ultimate goal is a telescope with 1 m^2 effective area at E=30 keV.&lt;/p&gt;
&lt;p&gt;To characterize the IR optical properties of the metal-coated hollow waveguide ensemble; configure the Hollow Waveguide FTS (HWFTS) chip in such a way that we maximize signal-to-noise; carry out full radiometric testing of this implementation and acquire spectra of standard gas cells.&lt;/p&gt;
&lt;p&gt;Lobster X-Ray Imaging technology gives high sensitivity and source localization.&lt;/p&gt;&lt;p&gt;The project consist of the following:&lt;/p&gt;&lt;p&gt;Demonstrate angular resolution and sensitivity. Successful lab demonstration of ISS leak checking, using nitrogen, electron beam, and Lobster x-ray optic.&lt;/p&gt;
&lt;p&gt;The University of Maryland is proposing to use a dielectric barrier discharge (DBD) as a means to dissociate N2O. DBD uses alternating high voltage differences between two electrodes to create strong electric fields. One or both of the electrodes is covered in a dielectric, and a gap in between allows gas to pass through. Nitrous Oxide sent through the gap between the electrodes has its free electrons accelerated by the large E-field, and in the process the electrons collide with N2O molecules.&lt;/p&gt;
&lt;p&gt;
	The ion source investigation consisted of coupling the low-temperature plasma discharge source to a mass spectrometer. The goal of this investigation is to provide insight into the ion yield and degree of fragmentation of the low-temperature plasma source relative to conventional electron-impact ion sources, as well as providing insight into technical requirements relating to gas usage, and vacuum requirements. Answering these questions will also address the larger question: is a plasma discharge ion source feasible for planetary exploration? The ablation study with the low-temperature plasma consisted of prolonged exposures of metal surfaces to the low-temperature plasma discharge and analyzing surface modifications with scanning electron microscopy. The intent of this study is to identify whether a plasma source can be used to ablate material from a surface and provide depth profiling of that surface when used in conjunction with a mass spectrometer. Sterilization of a surface with plasmas can proceed through passivation where contaminants are simply desorbed from the surface or through deactivation where biological contaminants on a surface are altered or destroyed following exposure to the plasma. This sterilization study with the low-temperature plasma probe focused on deactivation and involved exposure of Bacillus subtilis samples to the low-temperature plasma discharge to ascertain its effectiveness in deactivating these spores.&lt;/p&gt;
&lt;p&gt;
	The TOAST instrument is an open-loop processor of GPS navigation signals. The electronics fits on a single 10 cm square card with RF components and digital components on opposite sides. A dime-sized programmable chip (FPGA) acts as a signal processor for the GPS signals of up to 10 satellites. This FPGA is under the control of a very low-power Linux CPU which handles all of the tracking models for very weak GPS signals transecting the atmosphere. Unlike typical GPS receivers, TOAST tracks without tight phase-locked loop tracking of the received carrier phase. For any given GPS satellite to be observed, TOAST generates a precise 3rd order range and phase model and only updates the FPGA every 1 - 10 seconds. This allows the processor to be loosely coupled with the signal processing to the point where, given sufficient ground to space bandwidth, TOAST can be controlled by a ground-based CPU. However, in this implementation, a Linux CPU will accompany the RF and FPGA logic to provide real-time data.&lt;/p&gt;
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	&lt;span style="font-family: Calibri; "&gt;The objectives of this study are to adapt an existing JPL dewar and electronics for use with the STA device for observation at Palomar using an existing array (expected to have delta doped detectors produced with the MBE RTD), characterize and calibrate the performance of the array and the camera system in the laboratory (iterate), deploy to Palomar for a test run (first light check), and optimize devices and dewar configuration based on feedback.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: Calibri; "&gt;The objectives of this workshop are to engage the engineering community at JPL that is knowledgeable in this technology in guiding/developing/critiquing&amp;nbsp; its application in the context of an end-end functional system, expand the repertoire of engineering applications for this technology, further define the engineering functionality of the &amp;ldquo;reference mission&amp;rdquo; platform generated at the Science/Mission Workshop, discuss the mission architecture trades regarding the balance of functionality on the &amp;ldquo;support spacecraft&amp;rdquo; vs the printed platform, discuss trades within the system design of the printed platform, and to determine engineering functionality and requirements.&lt;/span&gt;&lt;/p&gt;
&lt;p&gt;
	Our task is evaluating a specialized detector for guidance, navigation and control (GNC) applications. The detector being evaluated is a 15 microsecond Latency Asynchronous Temporal Contrast Vision Sensor, referred to as a spiking sensor. It detects change in intensity on the detector at for very high rate applications. Each pixel on the detector operates independently, and detects intensity changes on the pixel. When the change in intensity exceeds a threshold and an event is generated. The events are reported from the detector as an asynchronous stream of digital pixel addresses and time tag (to an accuracy ~10 microseconds). This results in a highly reduced set of data returned from detector. Hence, only points of interest, not image frame data is output, which reduces data volume &amp;gt; 100x. The device is very low power (~25mW). Since the detection of the events is done on the detector, not in a processor, the requirements on processing are reduced. Because the events are asynchronous, the timing is tied to the event, not a frame rate, such as with imagers. For GNC characterization, we performed testing on laboratory targets that included a star simulator and Mars terrain targets, as well as field testing on star patterns, planets, and International Space station (as a beacon test) passes. During the testing, we gained understanding of the details of detector biases and operations, and developed processing algorithms for clustering and noise rejection on collected data. The current detector design has high dark current and low (9&#37;) QE; devices are in design that will give the technology a 100x SNR improvement by changes in manufacturing processes (silcon process), and front side vs backside illumination. The projection for GNC of the future device is part of this task (to be completed at end of May 2012).&lt;/p&gt;
&lt;p&gt;
	Our approach is based on high-Q optical WGM resonators made with a nonlinear crystal. Such resonators have been demonstrated to dramatically enhance nonlinear optical processes involving optical, microwave and THz frequencies. Difference frequency polarization is generated from two optical beams via second order nonlinearity of lithium niobate (LN). Efficient difference frequency generation (DFG) requires three features. The optical beams should be near the surface due to large THz absorption coefficient of lithium niobate. The cross section of the optical beams must be smaller than THz wavelength to minimize far field phase mismatch of the THz beam. In addition, the optical beam intensities must be high for the conversion process to be efficient. The LN WGM resonators provide the highest figures of merit on all three requirements and are expected to outperform the Fabry-Perot resonator-based nonlinear optical THz generation. The required phase matching of the process is achieved with a structure represented either by the periodically poled domains or by a metal structure integrated with a resonator. The capability to produce micrometer-precision arbitrary domains in ferroelectric crystal chips is present at JPL. With collaboration at UCSB/ITST we fabricated metal structures on LN chip. These chips were then used at JPL to produce WGM resonators with an integrated metal phase matching structure. Intrinsic Q of these resonators was preserved at 10 million levels which is an important milestone. We then carried out an experiment aimed at simultaneous excitation of two whispering gallery modes inside the resonator. The outputs of two DFB lasers emitting at 1560 nm and 1548 nm (1.5 THz difference frequency) are combined and are coupled to the resonator with a prism coupler. Coupling efficiency exceeded 40 &#37;. We achieved two-wavelength pumping of the resonator and high optical Q.&lt;/p&gt;
&lt;p&gt;
	&lt;span style="font-family: Calibri; "&gt;A new navigation technique known as LiAISON (Linked Autonomous Interplanetary Satellite Orbit Navigation) may be used to propel the benefits of GPS to new orbits, including GEO, lunar, L1, and L2 orbits.&lt;/span&gt;&lt;/p&gt;
&lt;p&gt;
	We had two objectives in this task: 1. Develop effective single low-mass, low-power piezoelectric drive that can actuate rotary-hammer samplers through walls. 2. Determine design sensitivities and investigate Acoustic Mechanical Feed-throughs (AMF) using acoustic mode conversion with emphasis on extension to rotary. In our earlier studies, we were able to excite rotation from longitudinal vibrations but, without sufficient analytical foundations, it has been a challenge to get consistent results. Therefore, we focused our efforts on the modeling, analysis and optimization of configurations that effectively convert longitudinal forces to torque and rotation. The task consisted of conceiving drive configurations and optimizing them thru finite element and harmonic analysis, as well as producing and demonstrating the physical mechanism. The analytical task provided tools and data to select highly efficient mechanisms that use piezoelectric materials to generate elastic waves that wirelessly transmit power through a metallic wall. We produced a resonant breadboard system that converts high frequency micron-size displacements to macroscopic rotary and linear motions. The developed mechanism uses the converse piezoelectric effect as a means of generating elastic waves, which is transmitted in the form of elastic waves, was used to excite rotation through a wall and establish a basis for a systematic capability to design wireless actuation, manipulation, and deployment thru walls. Efforts were made to optimize the location of the nodal plane of the transducer and difficulties were encountered since the nodal location of the transducer is not necessarily a plane. Through our analytical studies, we were able to produce Acoustic Mechanical Feed-throughs (AMF) capability that consistently and efficiently induces rotation. We established sufficient data and analysis to allow submittal of a credible proposal for further development of the concept.&lt;/p&gt;
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	An ultra-compact superconducting on-chip-spectrometer has the potential to revolutionize far-IR through millimeter-wave observational astronomy and astrophysics, allowing for the first time wide-field mm- and sub-mm spectral surveys and efficient follow up observations of known sources. Our ultimate plan is to use planar lithography to fabricate superconductin g transmission line filters to sort incident radiation by frequency to an array of direct detectors such as MKIDs. However, for this task, we are only focusing on the antenna array element and coupling structures which will couple energy from the telescope to the spectrometer chip. We will design and fabricate a 2x2 array of multi-flare-angle smooth walled horn array to demonstrate the feasibility of this concept for the spectrometer-on-a-chip as well as other focal plane arrays in the submillimeter-wave frequency band. The 2x2 horn array antennas will be fabricated using a tool which can make hundreds of arrays of horn antennas without much difficulty. This is the key innovation of this approach. The horn array will be designed for the 190-320 GHz frequency band. We will also design and fabricate a 2x2 array of circular to rectangular transition block which will be used to test the performance of the horn array. Fig. 1 shows the design concept and that fabrication tool that will enable fabrication of antenna arrays with hundreds of pixels.&lt;/p&gt;
&lt;p&gt;Background. NASA missions undergo wide variation in communications link conditions. Over the course of months, the range changes dramatically from launch, to cruise, to say, Mars orbit, but link conditions change on much shorter time scales, as well. For example, a typical track of MRO tracked by the Deep-Space Network might start at antenna elevation 11&amp;deg;, rise to 72&amp;deg;, and then fall to 8&amp;deg; over a twelve hour period. Recent and near-future NASA missions have their data rates limited by dynamic effects such as weather (e.g., MRO Ka-band links), solar scintillation (e.g. Solar Probe), on-board interference (e.g., MRO CRISM interference), launch plumes, and other effects. A 2005 Mars Technology Program study reported that up to 50&#37; more data can be returned on a typical Mars-lander to Mars-orbiter link when adaptive data rates are used on the link. Our task is to extend the concept of adaptive data rates to variable and adaptive coded modulation, in which the dynamic power and bandwidth resources can be much more effectively utilized. A 2010 study by ESA determined that in one practical scenario, a VCM system could more than double the total data volume returned. Our task is to make effective use of the CCSDS standard coded-modulations, thereby allowing us to operate close to the unconstrained capacity limit, regardless of link conditions. To do this, we will develop a physical-layer design that allows the transmitter to switch between coded modulations on a codeword-to-codeword basis, a mechanism to inform the receiver which coded modulation is being used, and the receiver tracking structures necessary to identify the coded-modulation and demodulate and decode the data appropriately.&lt;/p&gt;
&lt;p&gt;Metal patches were developed for the Juno Microwave radiometer instrument at P-band and L-band. The absence of dielectric in the metal patch design obviated issues with static discharge in the Jupiter orbital environment. However, metal patches readily scale to operation at other frequencies, and have excellent loss performance at W-band. Moreover, metal patches can be fabricated accurately using photo-lithographically defined microfabrication techniques that are dielectric free. The metal patch antenna elements that will be developed in this work are intended for use in an array-fed reflector system that is scanned in azimuth through the use of phase shifters in transmit and receive MMICs. This technology will support W-band cloud radar for the Aerosol/Cloud/Ecosystem (ACE) decadal survey mission, as well as other millimeter-wave applications. The focus of this work is to develop the antenna elements and associated feed networks; active electronics will be developed separately. The work will result in the design, fabrication, and testing of a 2x2 element array, termed a unit cell. A much larger feed array will be formed as the linear concatenation of these unit cells in subsequent development work. The unit cell (illustrated below) developed in this work incorporates all of the salient features that are critical to constructing larger scanning arrays, including the microfabricated feed network and the capability to predict scan performance. As a key part of the verification approach, a waveguide adapter fixture to measure network performance and element patterns of the unit cell device.&lt;/p&gt;
&lt;p&gt;
	The readout technique for &amp;ldquo;tilt locking&amp;rdquo; has been widely adopted in a range of scientific areas from quantum optics to spectroscopy since first being demonstrated in 1999 [1,2], but it has not been applied to high-performance laser frequency stabilization. Common laser stabilization systems transfer the length stability of an optical reference cavity to the laser frequency (or wavelength) using the standard RF interrogation technique (Pound-Drever Hall (PDH) locking), which employs electro-optic phase modulation of the carrier and RF demodulation as shown in Figure A below. In tilt locking, the reference signal relies instead on interference between overlapping spatial modes on reflection from the cavity, realized simply by intentionally tilting the laser beam and reading out a DC signal level difference between two halves of a two-element photodiode. The use of this DC signal allows the elimination of the phase modulator, RF signal generator and mixer electronics, as shown in Figure B. In addition, the DC operation largely reduces the susceptibility to a commonly limiting noise source: parasitic etalons. To demonstrate tilt-locking as a viable laser frequency stabilization technique we will construct a tilt-locking system comprising a laser, an ultra-stable optical reference cavity in vacuum, along with associated optics and electronics. [1] D. A. Shaddock et al. Opt Lett 24 1499 (1999) [2] B. J. J. Slagmolen, et al. IEEE J. Q. E., 38, 11, (2002)&lt;/p&gt;
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&lt;p style="margin: 0px; font-family: Calibri; "&gt;
	We shall develop a MEMS shutter that is expected to have 2-3 g mass and consumeThis research will demonstrate fabrication of a low mass (~2-3 grams), low power (&amp;lt;1 milliWatts), MEMS shutter. This technology will enable new in-situ and remote sensing imaging spectrometer instruments that were previously not feasible due to the mass, power, and reliability issues related to mechanical shutters or the calibration challenges posed by instruments without active dark frame measurement capability.&lt;/p&gt;
&lt;p&gt;This study will employ a three phased approach: SAR image formation and calibration. DBSAR polarimetric and interferometric data analysis. PolInSAR algorithm development, validation and extension.&lt;/p&gt;
&lt;p&gt;Measurements of energetic neutral atoms (ENAs) are a new tool to improve our understanding of energy release and particle acceleration in solar eruptive events. &amp;nbsp;Due to limitations of past observations, even the most basic questions remain unanswered about the acceleration of solar energetic particles (SEPs) by shocks driven by coronal mass ejections (CMEs). &amp;nbsp;ENAs provide the only way to observe SEPs where they are accelerated. &amp;nbsp;The one observation of solar ENAs to date had low sensitivity, a high energy threshold, and no imaging information.&lt;/p&gt;&lt;p&gt;The Solar Energetic Neutral-atom Imaging Coronagraph (SENIC) instrument concept is designed to observe ENAs from &amp;lt;~20 keV to a few hundred keV with a spectral resolution as good as 1 keV and image them from 2 R_sun to 40 R_sun with a spatial resolution of 0.1 R_sun. &amp;nbsp;Since ENAs cannot be imaged with focusing optics, this concept uses an indirect imaging technique similar to the one successfully used on RHESSI. &amp;nbsp;Thus, the SENIC instrument concept&amp;nbsp;combines large detector area, a low energy threshold, and high angular resolution.&lt;/p&gt;
&lt;p&gt;The Cleaning Lenses and Mirrored Surfaces with Electrons tasks include: Development of Fractal Wand Geometries; Vacuum Chamber testing&amp;nbsp;of Fractal Wand Prototypes; and selection of best prototype.&lt;/p&gt;
&lt;p&gt;This technology will be a quantum advance in cardiac monitoring and will be applicable in numerous situations such as for&amp;nbsp;immediate assessment and monitoring of patients in life-threatening emergencies, during environmental stressors, and in performance of hazardous occupational tasks. For NASA these benefits will apply to both flight and ground personnel. For the military this device can be used during actual combat to alert medical personnel when a service member is wounded and to monitor his/her condition even before help is provided thus lowering medical evaluation times. This can also be used to aid medical personnel allowing them to prioritize triage and evacuation in multiple casualty contingencies.&amp;nbsp;&lt;/p&gt;&lt;p&gt;The goal for this project is to design, develop and advance technology for a near-instantaneous, non-invasive radio frequency-based method for measuring heart and lung function without invasive probes, cuffs, electrodes and without patient contact.&lt;/p&gt;
&lt;p&gt;This project created a pilot version of the software tool work control system to run on a tablet by modifying the existing template and beginning an initial investigation into the processes needed to make the mobile software tool work well with the existing database. A tablet and the mobile software was used in conjunction with software currently owned by Stennis. From an Information Technology (IT) security standpoint, proper implementation strategies (e.g. Secured Wi-Fi, 3G cellular networks, and docking stations) were considered for field use of the system. A representative from IT security helped facilitate discussions for proper implementation strategies with support from developers to assess feasibilities of such strategies.&lt;/p&gt;&lt;p&gt;Primary project objectives included the following:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Create a pilot version of the work control system to run on an tablet by modifying an existing template&lt;/li&gt;&lt;li&gt;Begin an initial investigation into the processes needed to make the control system work well with the existing database.&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;From an IT security standpoint, consider proper implementation strategies (e.g. Secured Wi-Fi, 3G cellular networks, and docking stations) for field use of such a system.&lt;/p&gt;
&lt;p&gt;We have developed carbon nanotube formulations primarily geared towards enhanced stray light control on a variety of instruments.&amp;nbsp; IRAD has supported development of this technology to make it 10 to 100 times blacker than alternate surface treatments from the Near UV to Far Infrared and a large variety of substrates suitable for space flight instrumentation.&amp;nbsp;&amp;nbsp; In addition, we have performed the first growth on catalyst applied to substrates using Atomic Layer Deposition (ALD).&amp;nbsp; Catalyst is normally deposited using thermal or e-beam evaporation which allows for coating flat surfaces.&amp;nbsp; Many baffles are dimensional, curved or complex, requiring conformal deposition.&amp;nbsp; The development of a conformal nanotube process is enabling to many applications.&amp;nbsp; We have demonstrated ALD of iron catalyst out of house and hope to achieve an in-house capability.&amp;nbsp; Ellipsometry performed on the part verified sub nanometer uniformity of catalyst across a test part .&amp;nbsp; The compact coronagraph baffle is larger and more complex which will pose a significant challenge in maintaining uniformity over a larger third dimension.&amp;nbsp;&amp;nbsp; In addition, we must solve the problem of managing feedstock gas flow in our nanotube furnace during chemical vapor deposition (CVD).&amp;nbsp; We have seen significant shadowing and non uniformity of growth due to laminar flow at substrate edges.&amp;nbsp; Modeling of the gas flow has begun and will be useful in solving this problem.&amp;nbsp; In addition we are performing our occulter growth using a reflector to direct feedstock gas to the shadowed side of the mask.&amp;nbsp; Our goal will be to address these challenges and deliver a solar chronographic mask that is applicable to other scientific observations.&lt;/p&gt;
&lt;p&gt;
	Pulse tube coolers at high temperature have offered increased efficiency and reliability over older cooler technology. At lower temperatures (&lt;/p&gt;
&lt;p&gt;This development is a collaborative effort between California Institute of Technology (Caltech) and the Jet Propulsion Laboratory (JPL). The fabrication is done using complementary facilities at the Kavli Nanoscience Institute (KNI) of Caltech, and the Microdevices Laboratory (MDL) at JPL. There are two parallel processes being developed. One involves the deformable mirror it self. The other involves process development of ultra-low thermal exopansion bi-metallic reflective layer that provides thermal stability to the mirrors using a mechanical grid. The mirror fabrication process involves forming micron-thick layers of PVDF with the required electrode patterns. Two approaches are being developed. Both approaches begin by depositing stack of piezoelectric films and electrodes over a Silicon wafer substrate. In the first approach, the silicon wafer is removed by plasma-based reactive ion etching (RIE)followed by a non-plasma dry etching with Xenon Difluoride (XeF2). In the second approach, the actuator film stack is immersed in a liquid such as deionized water. The adhesion between the actuator film stack and the substrate is relatively weak. Simply by seeping liquid, the actuator film stack is gently released from the substrate. The bi-metallic mesh structure fabrication is being pursued using deposition of dissimilar metals in lithographed patterns followed by sacrificial release processes. This process is now being transferred to a more robust approach that employs Silicon-on-Insulator (SOI) based fabrication processes. A stack that is produced when both of the above-mentioned structures are integrated will be a deformable mirror that is expected to have high tolerance against suface errors from temperature variations while in space.&lt;/p&gt;
&lt;p&gt;
	Renewable energy sources, including wind and solar, can supply a significant amount of electrical energy globally, but their potential has not been fully exploited yet, due to their intermittent nature, which requires safe, cost-effective, and reliable electrical energy-storage systems. Such storage systems will also be critical to improve the robustness and efficiency of the electrical distribution grid by reducing power surges and balancing the load over time. Electrochemical energy-storage devices, i.e., batteries and fuel cells, are promising because of their scalability and versatility, but most fuel cells cannot be reversed electrically (i.e., charged) efficiently. Consequently, batteries, especially flow batteries, wherein the energy density can be increased independently of power density, remain as the preferred option for large-scale energy storage. Several types of flow batteries, i.e., including true redox systems, (ionic solutions comprising vanadium salts or iron-chromium salts), reversible fuel cells with gaseous reactants, and hybrid flow batteries (e.g., metallic anodes as in Zn-Br, or Zn-air), are being developed. The Vanadium Redox Battery is perhaps the most developed flow battery, but still has several deficiencies, such as: i) Low energy densities, (~ 25 Wh/kg, and 20-30 Wh/liter, which is about 1/5th of conventional Li-ion batteries), ii) Low efficiency of 60&#37;, and iii) Non-ecomomic cost (~ 6-20 times the target of $100/kWh, mainly due to high cost of Vanadium reactants and Nafion membranes. To mitigate these issues, new chemically-stable redox couples, with high cell voltage (possible only in non-aqueous electrolytes) are desired and being proposed here to improve energy and power densities.&lt;/p&gt;
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	&amp;nbsp;&lt;/p&gt;
&lt;p style="margin: 0px; font-family: Calibri; "&gt;
	NASA has plans to fly stratospheric ULDBs for missions of 100 days or more in the next few years. As these balloons circumnavigate the globe multiple times, the risk of complete data loss in the case of adverse wind patterns or balloon failure will begin to outweigh the benefits of continued data acquisition. This could be mitigated if the complete data could be transferred from the balloon periodically throughout the mission. For missions with high data rates (such as a wide field telescope), downloading the data via ground stations used for balloons may be prohibitively slow and unable to match the data rate. Other methods, such as using the Tracking and Data Relay Satellite System (TDRSS) or line of sight communications with multiple ground stations have in the past proven to be prohibitively expensive. We are developing AIRS (Automated Information Retrieval System), a lightweight glider capable of descending from 30km balloon altitude, autonomously compensating for the jet stream to land in a predetermined GPS coordinate. AIRS carries a solid-state drive capable of withstanding much more than the mild G forces encountered on landing. A prototype has been built and tested at low flight altitudes successfully. Production costs of AIRS are anticipated to be about $1000 for parts and labor. In a one-day workshop we will explore various methods of retrieving balloon data in flight. We will compare the costs and risks of TDRSS, multiple line of sight ground stations, and AIRS. Collaborative efforts, and funding possibilities, to explore these concepts further will be discussed. The outcome will be an economical way to buy down a mission risk on ambitious future balloon missions. We will write a report on our findings and coordinate this with continued development of AIRS, which we plan to flight test (using a different funding source).&lt;/p&gt;
&lt;p&gt;
	What causes the Sun to vary? The Sun gives off magnetic fields, bulk plasma (the solar wind) and energetic particles moving up to nearly the speed of light, and all of these vary spatially and temporally. The three dimensional structure of solar wind turbulence, coronal mass ejections (CME) and magnetic clouds can only be understood with concurrent, multipoint measurements. Rapid advancements in CubeSat technology and the NASA OCT funding of Interplanetary CubeSats has opened the possibility of developing a flotilla of tiny spacecraft carrying magnetometers or simple plasma instruments to conduct these investigations. CubeSats are already demonstrating their cost effectiveness in Earth orbit. Heliophysics is a particularly fruitful field for extension of CubeSats to interplanetary constellations because many scientific investigations can only be accomplished with concurrent, spatially distributed measurements and the fields and particles instrumentation may fit within CubeSat volume constraints. While many CubeSat subsystems developed for Earth orbit are directly applicable to interplanetary mission, many subsystems will have to be totally redesigned to meet the requirements of deep space missions. This workshop will identify the scientific investigations enabled by a flotilla of small instruments in Earth-trailing and Earth-leading orbits. It will outline a mission concept and the technology challenges of the instruments and spacecraft systems necessary to conduct these investigations. This new approach, a flotilla of simple instruments, could help NASA develop a new approach to heliophysics research.&lt;/p&gt;
&lt;p&gt;The project focuses on key physico-chemical process technologies for Atmosphere Revitalization Systems (ARS) that increase reliability, capability, and consumable mass recovery as well as reduce requirements for power, volume, heat rejection, and crew involvement. For the Environmental Monitoring Systems (EMS) effort, the project is developing and demonstrating onboard analysis capabilities which will replace the documented need to return air and water samples to earth for ground analysis. This effort is addressing these challenges by adopting a new architecture that is based on the modular integration of multiple sensing modalities, employing a hybrid combination of simple, rugged technologies and, where needed, highly capable complex approaches, to completely address monitoring needs of the future. It incorporates Microelectromechanical Systems (MEMS) technologies to enable significant miniaturization over current systems, and selects elements offering both low resources and high reliability operation for affordability. The project is developing, demonstrating and/or testing leading process technology candidates and system architectures that will meet or exceed current requirements and fill capability gaps or significantly improve the efficiency, safety, and reliability over the State-of-Art (SOA). The project&amp;rsquo;s main goal is to demonstrate test articles (at various technology readiness&amp;nbsp;levels) in a ground test facility under relevant flight conditions.&lt;/p&gt;
&lt;p&gt;
	The proposed workshop is innovative in that it explores the use of additive manufacturing for the fabrication of hardware. Currently, all additive manufacturing techniques are in the early stages of development, both commercially and at other NASA centers. This technology, which includes processes like LENS, e-beam welding, and ultra-sonic additive manufacturing, aims to reduce the need for machining metal parts from large billets by creating net or near-net shapes using only the metal required for the final part. In 2012, JPL R&amp;amp;TD is funding the development of a novel steel-Invar alloy that is included in this proposal as the weld connection between a steel bench and an Invar optical mount. By tuning the composition of the gradient alloy to the prototype hardware, the thermal expansion between the two can be predicted and controlled. This will eliminate the need for brazing or fastening hardware, reduce the stresses associated with thermal-cyclic fatigue, and improve reliability. The fabrication of such a gradient alloy by traditional metallurgical techniques is not possible. The LENS technique offers the additional ability to fabricate net and near-net shape components from the gradient alloy, limiting the need for machining, by laser depositing the constituent metals at independently controlled rates via the LENS system&amp;rsquo;s computer-controlled multi-nozzle feature. The resulting part is fully dense, has a gradient transition from one alloy to another, and is tough (free of cracks and brittle intermetallic phases). The workshop is a natural evolution advancement from the current project because it will utilize the new material in optical packaging and other applications that are plagued with design challenges.&lt;/p&gt;
&lt;p&gt;
	System validation addresses the question &amp;ldquo;Will the system do the right thing?&amp;rdquo; When system capability includes autonomy, or more specifically, onboard mission planning and possibly closed-loop control, the question becomes more pointed. As NASA deploys space systems deeper into remote environments where the operating conditions are at least partly unknown (planetary surfaces, vicinity of primitive bodies), the ability to predict the fine details of the operating context becomes more challenging, and by extension, also the ability to predict how the system will behave under those operating conditions. On the other hand, grappling with operational uncertainty is in fact a motivation for pursuing onboard autonomy. The workshop will explore system validation in the context of future NASA mission scenarios that are enabled by autonomy concepts. The workshop will address the following and related questions: &amp;bull; Are extant validation techniques and methodologies adequate or extensible to future mission scenarios and system autonomy concepts? &amp;bull; Is the concept of a system behavior envelope (an enforceable boundary on system behavior, independent of operating context) viable, both from an engineering safety and a mission success viewpoint? &amp;bull; Is it useful and perhaps necessary to view system validation as an activity that continues into operations (Phase E)? The workshop will generate the following products: &amp;bull; An evaluation of whether future autonomous systems validation can be addressed by extensions to existing validation approaches or requires new validation concepts &amp;bull; A set of prioritized research questions relating to autonomous systems validation, and addressable with a small investment &amp;bull; A set of potential technology investments coupled to the research questions&lt;/p&gt;
&lt;p&gt;
	A number of low noise amplifier technologies exist at a variety of maturity levels and with a variety of strengths and limitations. The most mature amplifier technologies are semiconducting amplifier (InP HEMT or SiGe). The InP HEMTS have the lowest noise above several GHz, and are available commercially. However, more advanced InP HEMT ICs are only available to those with specialized knowledge and contacts with industry. By contrast the SiGe circuits have lower noise below two GHz and can be manufactured as complex mixed signal circuits integrating low-noise bipolar amplifiers with CMOS. Like InP, simple commercial SiGe amplifiers are readily available, but the more complex ICs requires a designer and the use of a commercial fabrication line. One benefit of this workshop will be introducing cryogenic technologists to these specialized designers of InP and SiGe ICs, in order to form new partnerships. Along with these semi-commercial technologies there are several new amplifier concepts still in the research phase including superconducting parametric amplifiers and RF/Microwave SQUID amplifiers. These amplifier technologies offer the possibility of quantum limited noise at frequencies as high as 300 GHz, but since they are research topics themselves they are not generally available. Again by bringing the researches working on these less developed technologies together with end-users we hope to create opportunities for collaboration. In general, the use of low-noise and quantum limited amplifiers can improve the sensitivity of many instruments and enable new ones. Some of these amplifier technologies are already being used in detector systems, but many are new or may be of benefit to additional NASA projects. This workshop will allow cryogenic instrument builders and amplifier experts learn about these technologies and find new opportunities for collaboration.&lt;/p&gt;
&lt;p&gt;
	The workshop will have three main objectives. The first will be to inventory the signatures and measurements that are desirable to make using submillimeter active systems. The second will be to derive the minimum requirements that would make such measurements competitive relative to the present state of knowledge. The third and final one will be to compare what is needed relative to the presently available capability to determine where immediate opportunities are, where short term investment could generate opportunities and areas where breakthroughs are still necessary before suitable systems could be built. There is a great deal of expertise distributed between various groups doing different kinds of research that does not generally lead to a discussion of possibilities outside the research area. The workshop will bring these diverse groups together with the intention of exploring the entire parameters space of scientific and technical possibility. Some potential applications include characterization of aerosols and particulates in atmospheres, dust in the solar system, molecules in atmospheres or exospheres, materials characterization, non-invasive inspection and remote surface characterization. The workshop will collect potential advocates and align them with those developing technology to illuminate areas where technological advances would lead to systems and to areas with systems leading to new science could be proposed using existing technology.&lt;/p&gt;
&lt;p&gt;
	&lt;span style="font-family: Calibri; "&gt;Individual talks by JPL and Caltech experts on graphene to present the different ambits of application in which graphene is currently being used on campus, roundtable among the participants to identify graphene&amp;rsquo;s potential applications and impact for future NASA missions: atomic-scale detectors, high-frequency sources, efficient thermal dissipation, expandable structures, etc., discuss the viability and a possible roadmap to establish a high-quality graphene CVD production process.&lt;/span&gt;&lt;/p&gt;
&lt;p&gt;
	Current electronic packaging designs used in our most recent spacecraft are comprised of technologies from the 1980&amp;rsquo;s and 1990&amp;rsquo;s. The current approach to electronic packaging design and selection uses well known design solutions because they are considered low risk and have space flight heritage; typically a ruggedized VME (Versatile Mechanical Euro) packaging architectures. Semiconductor features of this vintage utilize features that are measured in microns. As semiconductors have advanced, features are now measured in nanometers. We can use the example of the iPhone; with our current electronics design approaches the iPhone would be the size of a breadbox. These modern phones and devices such as laptop computers incorporate hundreds of new packaging technologies, some of which are appropriate for spaceflight and some that are not robust enough. The challenge is to identify the most useful technologies that are likely to survive rigorous spacecraft testing. With the exception of some earth-orbiting missions, virtually all other missions have unique environmental survival requirements. The primary objective of the Workshop will be to identify industry established state-of-the-art packaging technologies that can be leveraged without technology development with a focus on miniaturization. This will include active and passive components, substrates, connectors etc. Reliability and reworkability will be considered but will be a secondary objective in order to allow creativity. There will be a review of current JPL electronic packaging subsystems that can be exploited by reverse engineering the existing design. Also, new in-process JPL designs will be considered for redesign.&lt;/p&gt;
&lt;p&gt;The Cubesat Microfluidic Electrospray Propulsion (MEP) system module prototype will be designed, built and tested to demonstrate that a four MEP thruster system can be integrated into a single module on a cubesat electronic board. The MEP thruster is shown in Figure 1. It is an electrospray thruster with microfabricated components, a highly integrated capillary force driven feed system and indium propellant that is stored as a solid metal in the thruster head. It has no valves or pressurized reservoirs. Four of these thrusters will plug into one side of the cubesat board with the Power processing Unit (PPU) on the opposite side. The PPU will consist of COTS components. It will be designed to operate four 100 micronewton MEP thrusters. Existing lower thrust prototype MEP thrusters will be demonstrated in the module. The performance of the system will be characterized and control of the module will be demonstrated in a vacuum environment.&lt;/p&gt;
Micro-Instrument Accommodation Survey Project
X-ray measurements are critical for the understanding of cycles of matter and energy in the Universe, for understanding the nature of dark matter and dark energy, and for probing gravity in the extreme limit of matter accretion onto a black hole. We propose a program to mature the current x-ray microcalorimeter technology, while developing transformational technology that will enable megapixel arrays.

X-ray calorimeters based on superconducting transition-edge sensors achieve the highest energy resolution of any non-dispersive detector technology. The performance of single x-ray calorimeter pixels has reached that required for many possible future missions such as IXO, RAM, and Generation-X, but further optimization is still useful. In the last years, we have made progress in developing techniques to control and engineer the properties of the superconducting transition. We propose to continue this single-pixel optimization, and to improve both the practical and theoretical understanding of the correlation between alpha, beta, and noise to identify favorable regions of parameter space for different instruments.

A greater challenge is the development of mature TES x-ray calorimeter arrays with a very large number of pixels. Advances in the last several years have been significant. We have developed modestly large (256 pixel) x-ray calorimeter arrays with time-division SQUID multiplexing, and demonstrated Walsh code-division SQUID multiplexing, which has the potential to allow scaling to much larger arrays. Here we propose to extend this work, and also to introduce a new code-division SQUID multiplexing circuit with extremely compact, low-power elements. Using this approach, it is possible for the first time to fit all of the detector biasing and multiplexing elements underneath an x-ray absorber, allowing in-focal-plane multiplexing. This approach eliminates the requirement to bring leads from each pixel out of the focal plane, while reducing the power dissipati
&lt;p&gt;Electrical Impendance Tomography (EIT) utilizes a series of electrodes in a circumferential band-like device feeding these signals to a portable computer that generates images similar to a Computerized Tomography (CT) scan using a mathematical algorithm.The development and validatation of this new technoligy could provide reliable portable imaging of the head and chest cavity through the use of EIT. Impedance has been used to gain knowledge of cardiac function for several decades but not used as a scanning technique.&amp;nbsp;&amp;nbsp;&lt;/p&gt;&lt;p&gt;Still early in development, Electrical Impedance Tomography Technology (EITT) is designed to provide images allowing doctors to monitor a patient&amp;#39;s airflow or blood flow. While tools such as X-ray, magnetic resonance imaging (MRI) and ultrasound are well known, they don&amp;#39;t work well in a space environment due to radiation, user training, size and power usage considerations. These same limitations exist in remote locations on Earth.&lt;/p&gt;&lt;p&gt;The EITT device is a belt of electrodes worn around the portion of the body to be imaged. Once placed on a patient, it sends its observations to a computer, which then converts that signal to a still image or even a stream of live data. This information can be sent from space to the ground, or from remote locations anywhere in the world.&lt;/p&gt;
&lt;p&gt;Water comprises the majority of the daily mass requirements for crewed space missions. Used&amp;nbsp;for drinking, food prep, or hygiene, water is one of the most critical life support elements.&amp;nbsp;Reliable water recovery is paramount for long term space exploration either on the&amp;nbsp;International Space Station (ISS) or&amp;nbsp;beyond Earth&amp;rsquo;s gravity well. Advances in water recovery have allowed longer mission durations&amp;nbsp;and decreased launch costs. In order to visit or even habituate extraterrestrial bodies (Mars,&amp;nbsp;Europa) further advances in water recovery are needed.&lt;/p&gt;&lt;p&gt;Current environmental control and life support systems on the ISS are focused on air and water recovery. Wastewater is pretreated with chromic acid and then distilled. The pretreatment turns about 10&#37; to 30&#37; of the wastewater into unusable brine and makes further water recovery difficult.&amp;nbsp;In addition, no chemicals are retrieved for reuse from the brine. If the wastewater were treated in bioreactors and then distilled or filtered, chemical pretreatment would not be needed and the remaining brine could serve as a resource for chemical and further water recovery.&lt;/p&gt;&lt;p&gt;Development and application of brine tolerant ion-exchange resins could provide more efficient methods for retrieving elements and pure water from salt water, and provide feed stocks for commercial processes that generate bleach, HCl, and Na/KOH (e.g., Chlor-alkalai Process).&amp;nbsp;If proven feasible, the combined benefits would reduce consumables and further close the water loop for future space exploration. and generate consumable chemicals, such as HCl, NaOH , KOH and sodium hypochlorite (bleach).&amp;nbsp;&lt;/p&gt;
&lt;p&gt;For this project, several different augmentation techniques for locating ground articles from distance through an augmented live view were investigated. &amp;nbsp;Article photo-recognition, printed AR target on articles recognition, and geotagging augmented reality techniques were tested for accurate AR tracking, location, and ease of development. Also, an innovative use of combined virtual reality (VR) panorama elements along with properly placed AR elements in the virtual scene was tested for accuracy and ergonomic field viewing via the smart device. Test cases were run at SSC with: (1) common above and underground facilities; and (2) at a long barren sandy test site, with various application/techniques to determine feasibility of potential use for extra-planetary AR location/identification. Tests were first run at close range and then, if those runs were successful, they were additionally run at a distance.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Current methods for monitoring the water used on the ISS rely heavily on ground analysis of archival samples. Air monitors presently on board the ISS could be used for trace analysis of the water samples. Electrospray ionization (ESI) is a powerful and widely used ionization technique for analysis of bio-molecules in solution and provides a potential means for introducing water into the current monitors. Ions are formed in liquid droplets and these droplets behave differently depending on the composition of the liquid. A ground study is important to characterize the spray produced from different liquid compositions in an ESI source as a first step to proposing an ESI flight experiment. This study will serve as the baseline for the flight experiment, where the effect of microgravity on electrospray is unknown. Different liquid compositions will be used in an attempt to affect the surface tension and conductivity, and, therefore, the power requirements to form an electrospray. Solutions mimicking the ISS water samples will be tested to determine if the sprays produced require different parameters from those produced using different dopants. The intended product of this project will be a report detailing the effects of solution composition, needle size, and solution flow rate using the ESI source. These results will provide a baseline for an on-orbit ESI experiment, which might eventually lead to a new ionization source for water sample analysis. A successful completion of this project will lead to a proposal aimed at studying ESI as a station detailed test objective. As ESI is currently used in ground-based studies of biomolecules, further testing of this technique for on-orbit medical monitoring may be pursued.&lt;/p&gt;
&lt;p&gt;The research team took a fully collaborative approach with&amp;nbsp; NASA, the University of Central Florida, Embry Riddle Aeronautical University, and&amp;nbsp;a&amp;nbsp; global research commercial partner on the development and application of novel materials. Information gained in this study will be leveraged to propose future funding to advance the technology readiness level (TRL) for extreme conditions applications.&lt;/p&gt;&lt;p&gt;The three materials research tasks and associated partners&amp;nbsp;that were explored during this project are summarized as follows:&lt;/p&gt;&lt;ol style="list-style-type:upper-alpha"&gt;&lt;li&gt;Two-way Shape Memory Alloys systems with University of&amp;nbsp;Central Florida and&amp;nbsp; NASA Glenn Research Center (GRC)&lt;/li&gt;&lt;li&gt;Gradient Cellular solids with Embry Riddle Aeronautical University&lt;/li&gt;&lt;li&gt;Tunable composites/laminates&amp;nbsp; with NASA-GRC&lt;/li&gt;&lt;/ol&gt;
&lt;p&gt;To improve instruments functionality in a harsh rocket propulsion test environment, this project developed an intelligent strain gauge.&amp;nbsp; The initial design for this project was a novel foil strain gauge with the capability to measure strain and temperature (Type 1). &amp;nbsp;The novel foil strain gauge pattern features the integration of a silicon-diode temperature sensor and a self-heating element. The silicon-diode sensor provides the gauge temperature for performing real-time temperature compensation algorithms. The silicon-diode temperature sensor was used in the initial gauge pattern due to its enhanced abilities, but after refinement, resistive temperature element was then embedded into a second gauge pattern (Type 2). Then, the debond detection function was tested by monitoring the temperature of the gauge while the gauge was heated and cooled. The temperature signature (rate of heating/cooling) from the gauge was analyzed for both bonded and debonded gauges. Finally, a small control circuit was created with the capability to self-execute a bond integrity check, and perform real-time temperature compensation was also added. By combining the control circuit with the special gauge the smart gauge was converted into a fully functioning intelligent sensor system.&lt;/p&gt;
CIF Yagi &amp; Radio Science Project
&lt;p&gt;During the period of this project three different possible DC transformer concepts were proposed, theoretically modeled, and then experimentally tested with the intent of demonstrating a true dc transformer; i.e. an electrical device into which a given DC voltage and current can be applied and which will generate a different voltage and current, effectively changing the impedance of a power supply.&lt;/p&gt;&lt;p&gt;A component level DC transformer is described in which no alternating currents or voltages are present. It operates by combining features of a homopolar motor and a homopolar generator, both DC devices, such that the output voltage of a DC power supply can be stepped up (or down) with a corresponding step down (or up) in current.&lt;/p&gt;&lt;p&gt;Based on demonstrated technology, this DC transformer should be scalable to low megawatt levels, but it is more suited to high current than high voltage applications. Significant development would be required before it could achieve the kilovolt levels needed for DC power transmission.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The proposed effort will explore the feasibility and effectiveness of utilizing an electrically driven thermal shield for use as part of rocket plume deflectors. To accomplish this, a small scale prototype deflector cover will be designed and tested. The overall reduction in thermal conduction will then be observed using high speed thermal imagining. The goal is to achieve a ten percent reduction; however, any thermal reduction would be considered a valuable success. The fundamental principles from a small scale system could then be used to economically scaled up for deployment within full-size rocket propulsion system.&lt;/p&gt;
&lt;p&gt;The innovation will allow waste heat to be harvested for use on aircraft jet engines, hypersonic vehicles, automobiles and other areas where waste heat is available. It will also provide a portable solution for laboratories that require a small power supply. The compact power supply can also be used on Mars and other planets to use solar energy to power plasma actuators for dust removal or for thrust corrections. 1. Combining Thermoelectric cells with plasma generation for self powered system proof of concept. 2. Optimization of the high-voltage generator towards a higher efficiency and its compacter size. 3. Addition of load current measurement circuitry for characterization and analysis of D.B.D. devices including power measurement. 4. Creation of compact circuit to power a plasma actuator using a thermoelectric generator (that can also be powered using solar cells.)&lt;/p&gt;
&lt;p&gt;Martian atmospheric gases are a very important resource for surface missions on the red planet. However, their utilization for the production of hydrocarbons, oxygen, and water into&amp;nbsp;in situ resource utilization (ISRU)&amp;nbsp;systems requires that they be separated from their original mixture. Trace gases must be extracted to provide pure carbon dioxide (CO&lt;sub&gt;2&lt;/sub&gt;) to processing reactors. In addition, other Martian gases, such as nitrogen and argon, occur in concentrations high enough to be useful as buffer gas and should be captured as well. To achieve these goals, highly efficient gas separation processes will be required. These gas separation techniques are also required across various areas within the ISRU project to support various consumable production processes.&lt;/p&gt;&lt;p&gt;&amp;ldquo;Living off the land&amp;rdquo; with resources indigenous to a planetary body such as Mars, or ISRU, requires mission-enabling capabilities that will be a necessary part of further exploration of the solar system. It is vital to demonstrate the practicality of these technologies for future Martian missions. Current work, focusing on developing a first-generation Mars ISRU demonstration lander for atmospheric and soil processing operations, is being performed as a multicenter NASA effort. Work on the Mars Atmosphere and Regolith COllector/PrOcessor for Lander Operations (MARCO POLO) project&amp;nbsp;is aimed at using Martian resources to produce methane, oxygen, and hydrogen for use as rocket propellant and fuel cell consumables.&lt;/p&gt;
&lt;p&gt;An application was developed that could enforce two-factor authentication for NASA access to the Propulsion Test Streaming Video System.&amp;nbsp; To gain access to the Propulsion Test Streaming Video System, all user requests are submitted through the NASA Account Management System (NAMS).&amp;nbsp; The assigned approver of these requests is the respective Project Manager for each of the engine test projects.&amp;nbsp; Then, for authentication purposes, a user is required to use either a NASA issued SmartCard or RSA token to gain access to the website.&amp;nbsp; Upon authentication, the user enters the website page. The page displays hyperlinks to each engine test video streams that the user has been granted access to.&amp;nbsp; The user can then selects the chosen video stream for live viewing from their end-user device/location.&amp;nbsp; For commercial customers, the video stream is sent directly from the video encoder to the customer&amp;rsquo;s corporate streaming server for distribution within the customer&amp;rsquo;s facility.&lt;/p&gt;&lt;p&gt;The architecture of the Propulsion Test Streaming Video System was redesigned in order to provide a service capable of supporting two-factor authentication.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Cloud computing security penetration testing and anomaly detection defense studies were conducted to assess the adequacy of cloud computing security.&amp;nbsp; Since cloud computing involves data distributed over wide areas and multiple devices being shared by unrelated users, the security challenges become increasingly complex.&amp;nbsp; Additionally, with the advent of cyber warfare as a threat, protecting data from theft or alteration does not in itself neutralize the threat, as the adversary also seeks to disrupt critical infrastructure and services such as penetration into data center server networks, and automated security access control.&amp;nbsp; It has therefore become increasingly important to complement security capabilities with advances in automated intelligence (AI) to recognize the plans of multiple agent threats (software or human) based on the observation of their activities. Therefore, for this project, an autonomous micro-modular mobile data center was used as a test/demonstration platform to study cloud computing security.&lt;/p&gt;
&lt;p&gt;The objective of the proposal work is to investigate the highly innovative conceptual design of an optical communication selective frequency transmitter terminal that enables the selection of multiple high-frequency microwave bands (L, S, X, Ku, Ka, V, W Bands ranging from 1 GHz to 100 GHz), while still maintaining the high-data-rate transmission of more than several tens of Giga bits per second. The primary technical objective to be achieved will be a demonstration of a functional optical selective frequency transmitter terminal for multiple microwave frequencies, specifically the X and Ka frequency bands, which are presently used for NASA space communications. We will show the feasibility of transmitting multiple high-frequency bands with the wavelength-division-multiplexing (WDM) technique over a fiber optical network by utilizing a wideband electro-optic modulator and tunable laser semiconductor diode. An important technical merit of this concept, which is based on a WDM technique, is the fact that it does not need complex protocols to handle data and can thereby greatly simplify the structure of the transmitter. This configuration of a WDM system at the transmitter end only requires a few components such as a multiplexing module, electro-optic modulator, control electronics terminal, tunable laser, and telescope. At the receiver end, the terminal has an optical filter (de-multiplexer) to select the transmitted frequency. After the filter, the optical signal is converted to an electrical signal by a photodiode and amplified by a pre-amplifier.&lt;/p&gt;
&lt;p&gt;During the last 10 years, mis&amp;shy;sions to the moon have revealed locations where ice water could be located beneath the surface. The moon is not flat, but has permanently shadowed craters at the north and south poles that hold ice water and volatiles.&amp;nbsp;&lt;span style="line-height:1.6em"&gt;The Shackleton crater at the south pole of the Moon is a very compelling target. Researchers think that up to 22 percent of the surface content could be water ice.&lt;/span&gt;&lt;/p&gt;&lt;p&gt;Extreme access will be required on these missions into the permanently shadowed regions of the moon&lt;span style="line-height:1.6em"&gt;. There are hundreds of small craters at the moon&amp;rsquo;s North Pole, and there is data that shows they might contain&amp;nbsp;up to 600 million metric tons of water ice. S&lt;/span&gt;pace mining re&amp;shy;quires access, resource excava&amp;shy;tion, extraction, and then some level of processing.&lt;/p&gt;
&lt;p&gt;The project involved the development and testing of a new alumina-silicate based multi-purpose, cost-effective, &amp;lsquo;green&amp;rsquo; cementitious binder (geopolymer) capable of acting as a high performance refractory material with both a low ablation rate and a high early mechanical strength. This work was built upon previous research undertaken by the research team in the areas of geopolymer binders. Full scale and laboratory controlled tests were performed to compare geopolymer performance to currently available commercial products (e.g. Sentinel, Greencast). Geopolymer&amp;rsquo;s thermal shock resistance properties were tested on eleven different fly ash stockpiles specimens from around the world. The geopolymer specimens were subjected to ASTM C-1100 (Standard Test Method for Ribbon Thermal Shock Testing of Refractory Materials). Samples were subjected to incremental 5-5-5-15-30 second flame exposure durations and to a 15 or 30 accumulated exposure, depending on the sample performance (e.g., if the plume became detached). Field test durations were limited to prevent excessive erosion of the test panels and subsequent plume detachment. Laboratory testing also demonstrated that geopolymer could withstand thermal shock and exposure to flame. Additionally, a computational model was created to determine the optimal chemical ratios for geopolymer to be exposed to elevated temperatures. Additionally, due to their excellent adhesion to pre-existing surfaces geopolymer binders were proven to be good candidates for use in repair of existing structures upon which they were applied and retrofitted; this was demonstrated and observed via tests conducted on repaired tested panels. Overall, the demonstration testing program revealed that the geopolymer products had equal or superior performance compared to commercial refractories currently used by NASA.&lt;/p&gt;
&lt;p&gt;The objective of this study was to identify and estimate the cost of one or more approaches of utilizing waste hydrogen for power generation. To simplify the scope of the problem, this study was limited to the boiloff source of the run tank at one test stand which consistently produces 500 gallons of hydrogen gas every day. This study used the results of several previous studies that also examined different ways of allaying the waste hydrogen problem. Using literature from these previous efforts as a starting point, a market review was conducted to find potential systems of hydrogen-fueled energy generation that are currently available. Candidate systems were considered based upon their compatibility with requirements dictated by the test stand and related infrastructure. These requirements were developed from technical data and drawings and supplemented with knowledge gained during a site visit to the test stand.&lt;/p&gt;&lt;p&gt;The market review revealed only a single viable option: a hydrogen-fueled 4.9-L reciprocating engine and generator set.&lt;/p&gt;&lt;p&gt;A high-level design of the supporting infrastructure was carried out in order to conduct a reasonably accurate cost analysis once a prime mover and generator system was selected. Gas and water piping systems were developed, electrical equipment needs were identified, and a general site layout determined. Cost estimates were then made for materials, equipment, installation labor, maintenance and prime contractor expenses.&lt;/p&gt;&lt;p&gt;With the performance of the power generation system, capital and variable expenditures known, life cycle cost analysis metrics were calculated. Impacts of the developed system on the environment were also assessed.&lt;/p&gt;
&lt;p&gt;This project was a small proof-of-concept case study, generating SysML model information as a side effect of safety analysis. A&amp;nbsp;prototype FMEA Assistant was used to semi-automate safety analysis that identifies failure modes and causes, using a library with standard SysML-compatible terminology to classify components associated with failure modes&amp;nbsp;and to&amp;nbsp;automatically identify candidate functions, infrastructure and failure modes. FMEA analysts select from standard functions and failures to systematically narrow down failure mode selection&amp;nbsp;(presented in automatically created pick lists). Standard terminology from an existing Aerospace Ontology&amp;nbsp;is used to&amp;nbsp;classify components and automatically identify candidate functions and failure modes. With automatically created pick lists, analysts can easily and correctly select standard functions and failures for a SysML architecture&amp;nbsp;model as a side effect of using FMEA Assistant.&amp;nbsp;&lt;/p&gt;&lt;p&gt;A white paper reports on a concept&amp;nbsp;for using&amp;nbsp;SysML profiles for safety analysis, to&amp;nbsp;standardize&amp;nbsp;FMEA-related terminology&amp;nbsp;for reuse in several types of safety analysis (hazard analyses, fault trees, reliability block diagrams).&lt;/p&gt;&lt;p&gt;See related project:&amp;nbsp;&amp;nbsp;Failure Modes and Effects Analysis (FMEA) Simulation Tool&lt;/p&gt;
&lt;p&gt;In practice, cleaning and disinfection of surfaces involves a considerable amount of effort, high consumption of energy and chemical detergents, and consequently high costs.&lt;/p&gt;&lt;p&gt;Current methods to sterilize assembled flight hardware elements include dry heat processing, gamma irradiation and hydrogen peroxide vapor processes.&amp;nbsp; Items such as sensors, battery and valve seals, and optical coatings will generally not survive these processes.&amp;nbsp; Because of these issues, NASA is concerned that planetary protection sterilization requirements may make future missions exceedingly costly.&amp;nbsp; Properly illuminated photocatalytic materials have been shown to kill microbes and decontaminate surfaces.&lt;/p&gt;&lt;p&gt;This project assessed the viability of using commercially available photocatalytic coatings as an&amp;nbsp;alternative method of sterilizing previously non-sterilizable flight hardware.&amp;nbsp;&lt;/p&gt;&lt;p&gt;Hygienic photocatalyst coatings are formulated with light activated TiO2 which assists in the deactivation of bio-contamination sources like bacteria, viruses, and Volatile Organic Compounds (VOC&amp;#39;s), as well as tough odors. In recent years, photocatalyst coatings have demonstrated successful reduction of transmittable diseases like Bird Flu and Severe Acute Respiratory Syndrome (SARS) infections in high risk areas. Many hospitals and buildings in Asia and Europe have been photocatalytically coated to increase the surface protection of these properties.&lt;/p&gt;&lt;p&gt;For this project, an experiment for testing the effects of commercially available TiO2 solutions in controlling the growth of bacteria, as an antibacterial activity test, was implemented.&amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
Phase-Induced Amplitude Apodization (PIAA) is a high performance coronagraphic technique well suited for direct imaging and
spectroscopic characterization of potentially habitable Earth-like planets from space. It delivers high contrast images by performing a
lossless geometric remapping of the telescope beam with two aspheric mirrors, and simultaneously offers nearly full throughput, full
angular resolution of the telescope, small inner working angle, high contrast and low chromatism. While the early PIAA systems
(which are currently undergoing testing at several facilities) were designed to deliver high contrast at 2 l/D, newer hybrid designs can
theoretically deliver on a point source a 1e-10 contrast down to 0.64 l/D inner working angle with full throughput, approaching limits
imposed by fundamental principles. PIAA coronagraph designs offer nearly optimal coronagraphic solutions for a wide range of
telescope size and astrophysical goals, from debris disks and giant planet imaging with a small size (
&lt;p&gt;It is critical that safety factors be maximized with respect to long duration, extraterrestrial space flight. Any significant improvement in radiation protection will be critical in ensuring the safety of crew and hardware on such missions. The project goal was to study novel concepts for radiation shielding materials that can be used for long-duration space missions. As part of this project we investigated the use of thin films for the evaluation of a containment system that could retain liquid hydrogen and provide the necessary hydrogen density for effective shielding.&lt;/p&gt;&lt;p&gt;The technical challenge of this project was to identify or design/develop a polymeric/composite material, laminate system that can contain a large quantity of liquid hydrogen in deep space for Galactic Cosmic Radiation (GCR) shielding. This material/system must be strong enough to handle the pressure generated by this cryogenic material, yet maintain some degree of elasticity, even at liquid hydrogen temperatures (typically 20&amp;nbsp;K). It must be thin enough to minimize secondary particles from GCR, yet not allow the hydrogen to diffuse through it.&lt;/p&gt;&lt;p&gt;Finally, it would be desirable to have high emissivity at long wavelengths so that radiative cooling can occur. Specific architectural&amp;nbsp;designs and thermal controls of hydrogen contaminant system were not addressed in this project.&amp;nbsp; This project also aligns with joint activities currently being worked with other NASA centers and the integration of technologies that are considered necessary for future exploration.&lt;/p&gt;
&lt;p&gt;An economic development tool, for use at SSC, was developed to generate portfolios coupling standard descriptors about potential sites with maps and location specific information. The generated portfolios include pre-created maps, dynamic map products, acreages, demographic reporting of the surrounding area, areas within a specified transportation distance, distance to utilities and other critical infrastructure, soil/regolith types, and proximity to dangerous condition areas, that could potentially be used for infrastructure layout and development for decision making. The wizard-based tool allows personnel working with potential tenants to step through these descriptive areas to edit or verify the populated information before generating the portfolio.&amp;nbsp; The first step involves using query tools to find property or space within a specified size constraint. Once the user has selected all the desired site information, and entered and/or verified the categorized information, the final portfolio document can be created.&amp;nbsp; &amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	The near future of spacecraft will likely be more autonomous, require more processing power, and may include the use of multicore processors or next generation FPGAs. These high thermal density devices can create local hotspots which can hinder device performance and reduce reliability. Highly oriented mats of carbon nanotubes (CNTs) with their extremely high thermal conductivity (k ~ 2500 W/m-K for individual multi-walled CNTs) have the potential to improve the performance and reliability of these devices by functioning as a thermal superhighway, maximizing heat transfer away from the source. Successful implementation of CNTs as a thermal interface material (TIM) would be a significant improvement over the status quo as current quality TIMs are in the form of metal or ceramic filled polymers and greases with thermal conductivities ranging from 0.5 to 2 W/m-K. Implementation of CNT TIMs has been limited due to insufficient thermal and mechanical coupling of the CNTs to secondary and tertiary (i.e. non-growth) surfaces. The investigators have proposed a method to improve the thermal and mechanical coupling of CNTs to these surfaces. In this study the investigators will examine theoretical CNT-substrate interfaces for sources of thermal resistance (phonon scattering) and effective coupling for a variety of metallic substrates. Phonon (quantized lattice vibrations) propagation and dispersion at the interface will be investigated using atomistic and quantum mechanical models and the theoretical potential of heat transfer across the examined interfaces evaluated for potential future work.&lt;/p&gt;
&lt;p&gt;A major challenge for the CPAS (The parachute system for the Orion/MPCV vehicle) program is to estimate the jerk load during parachute deployment. Accurate determination of this jerk load would enable proper selection and sizing of not just the parachute cords but the entire parachute attach structure on the vehicle. At present, this is estimated using analytical methods based on fluid mechanics principles. Current sensors that may be attached to the parachute cords tend to be very heavy, occupy too much volume and potentially interfere with the parachute deployment process. Instrumenting 60+ parachute cords with these large sensors would thus not be viable. The proposed sensor will alleviate these issues. The CPAS project manager did express the desire for such a device.&lt;/p&gt;
&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;One of NASA&amp;#39;s strategic goals is to extend and sustain human activities across the solar system. With time delays and potentially sparse communications back to Earth, astronauts may have to perform life-saving surgery without support from the Earth based flight control team. Medical crew training is a complex and labor-intensive process. Due to the large and diverse set of possible medical conditions, crew medical training focuses on the most likely medical scenarios that may occur in the current mission profiles, with less emphasis on rarer, or unforeseen health related events. The need for good training and the access to large amounts of documentation areconditions making the use of Augmented Reality (AR) techniques most promising. Also, the use of medical AR for crew training could enhance effectiveness, and expand the repertoire of available on-mission aids while minimizing resource utilization saving time, money and potentially improving outcomes.&lt;/p&gt;
&lt;p&gt;The Morpheus VTB/ALHAT project plans to free fly a reusable Morpheus VTB with the integrated ALHAT system starting from a slant range of approximately 500 m to the landing target at the KSC Shuttle Landing Field (SLF), ascending to about 250 m and descending to a safe landing site, and demonstrating an autonomous closed loop landing. This flight will demonstrate real-time hazard detection and hazard avoidance followed by a divert maneuver to the determined safe landing aim point and a safe, controlled landing within a hazard field. This demonstration flight will be a culmination of a series of earlier test flights, starting with improvements to the LOx-Methane propulsion system, GPS navigation, integrated reaction control system, and incrementally increasing in complexity by incorporating ALHAT sensor data.&amp;nbsp; The project aims to yield not just technologies, but technologies integrated as capabilities which could then be easily adapted to human spaceflight mission architectures.&lt;/p&gt;
&lt;p&gt;This proposed work is fabricate &amp;ldquo;button&amp;rdquo; with cathodes of 2-3 different ceria-based compositions. The cells will be tested in a mixed gas CO2&amp;ndash;H2O-H2 atmosphere perform both impedance and polarization measurement to characterize the performance.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The idea of vibrational locomotion is based on vibrational-fluidization in ISRU reactor systems, which has proven very effective for regolith mixing. The vibrating device would essentially vibro-fluidize the local regolith surrounding it, reducing the local bulk density. With proper design (size, shape, weight) the device could gradually sink into the regolith. Vibration is also used in industrial digging applications as a supplement to a constant forward force. The vibration helps to reduce friction between the soil and the digging tool. Including a percussive motion to the proposed device would produce such a downward force and mimic industrial techniques.&lt;/p&gt;
&lt;p&gt;Build and test in a relevant environment a Mars propellant production plant of an appropriate scale for an initial demonstration on Mars. It will produce sufficient propellants for a small science hopper vehicle to hop 2 km every 30 days. Specific objectives include: &amp;bull; Validate the performance of specific components included in the design from ref. 2 &amp;bull; Acquire data for a range of operating conditions for the CO2 acquisition devices to enable design improvements &amp;bull; Develop realistic estimates of the mass and volume of the &amp;lsquo;other&amp;rsquo; components (valves, plumbing, wiring, etc.)&lt;/p&gt;
&lt;p&gt;Develop a well understood process for manufacturing visible quality SCSi mirrors. Areas of research include stress relief, figure, finish, and light weighting techniques.&lt;/p&gt;
&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;The idea is to develop a graphene/polyethylene layer that can be laminated to other thin films as is commonly done in the food packaging industry.&amp;nbsp; A typical food packaging film has more than five layers of materials that confer altogether the desired physical and mechanical properties of the package.&amp;nbsp; The proposal encompasses the feasibility study of graphene/polyethylene films for use in lightweight and safe food packaging.&lt;/p&gt;&lt;p&gt;The focus of this project is the construction, characterization, and demonstration of a flexible, impermeable membrane for use in any application where gases are required to be contained or excluded, such as food and drug packaging, or inflatable modules and habitats.&amp;nbsp; Graphene is essentially single-layer graphite, and can be thought of as an unrolled nanotube.&amp;nbsp; Graphene has shown promise to be impermeable to all gases.&amp;nbsp; It has been observed that as little as a single atomic layer of graphene is impenetrable by gases, including helium [J. S. Bunch et al., Nano Lett., 8, 2458 (2008)].&amp;nbsp; This property can be exploited to fabricate impermeable membranes.&amp;nbsp; Graphene will be embedded within polymer films for fabrication of these impermeable membranes.&amp;nbsp; &amp;nbsp;&amp;nbsp; &amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The overall goal of the project is to demonstrate cost efficient cryogenic operations on a relevant scale that can be projected onto future Spaceport architectures and extraterrestrial surface operations. This goal will be demonstrated by completing the primary test objectives below: GODU Integrated Refrigeration and Storage (IRAS) &amp;bull; Demonstrate zero loss storage and transfer of LH2 at a large scale. &amp;bull; Demonstrate hydrogen densification in storage tank and loading of flight tank &amp;bull; Demonstrate in situ hydrogen liquefaction using helium refrigeration GODU Autonomous Control of Cryogenic Propellant Load &amp;bull; Demonstrate autonomous control of a sub-scale vehicle loading operation &amp;bull; Demonstrate recognition of common system faults and anomalies and recover without human intervention &amp;bull; Evaluate tools and techniques in real world application to advance health management and autonomous control technologies for future applications &amp;bull; Demonstrate scalability and extensibility by replicating autonomous control of the 6,000 gallon LOX simulator system to the 33,000 gallon LH2 system &amp;bull; Develop and demonstrate helium conservation instrumentation and processes &amp;bull; Provide potential hardware in the loop demonstration capability for AES Automated Mission Operations project or other analog test environment for remote operations in 2014&lt;/p&gt;
Future UV/Optical telescopes will require increasingly large apertures to answer the questions raised by HST, JWST, Planck and Hershel, and to complement the = 30-m ground-based telescopes that will be coming on line in the next decade. Apertures in space in a 10m-class scale will be needed to serve this goal. For diffraction limited performance, technologies are therefore required that provide a high degree of thermal and dynamic stability, and wave front sensing and control.
&lt;p&gt;Demonstrate efficacy of a novel growth technique for planar waveguides (PWG) Enable PWG laser technology with improved performance, efficiency and manufacturability. Manufacture a planar waveguide more like a fiber, instead of building it piece-by-piece. Build an optimized PWG amplifier prototype using this technique Evaluate its performance Demonstrate potential of new technique Collaborators: NP Photonics, Inc.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;This first part of this effort &lt;/strong&gt;investigated the iron-nickel binary system with varying nickel content over a range of CTE from 0.6ppm/&amp;deg;C to 10.0ppm/&amp;deg;C.&amp;nbsp; Figure 1 shows a comparison of calculated values of room temperature CTE for binary Fe-f(Ni) alloys based on the two gamma state ferromagnetic model for the face-centered cubic Fe-Ni austenite matrix, with one-hundred year old data from the experimental work of Guillaume.&amp;nbsp; Both the calculation and the early experimental data indicate that the CTE of Fe-Ni binary alloys vary continuously with nickel content in a smooth and predictable manner.&lt;/p&gt;&lt;p&gt;&lt;strong&gt;The second part of this &lt;/strong&gt;&lt;strong&gt;effort&lt;/strong&gt; determined experimentally the functional relationship between Ni content and CTE for the binary Fe-Ni system.&amp;nbsp; This was achieved by manufacturing a series of test alloys using high-precision melt metallurgical techniques.&amp;nbsp; The test alloys were heat treated by the Goddard Space Flight Center&amp;rsquo;s (GSFC) Materials Engineering Branch (MEB) and CTE coupons were machined by GSFC&amp;rsquo;s Advanced Manufacturing Branch.&amp;nbsp; Microstrain was measured as a function of temperature from 300K to 23K using the MEB interferometer.&amp;nbsp; Figure 2 shows an example of a secant CTE calculated from these microstrain measurements over the temperature range 10&amp;deg;C to 30&amp;deg;C.&lt;/p&gt;
&lt;p&gt;
	&lt;strong&gt;Methodology used to answer science question:&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;
	The investigators propose to upgrade the successfully flown EUNIS EUV spectrograph, increasing its signal-to-noise ratio and replacing its 30-37 nm channel with a 52.4-63.0 nm channel to cover transition region lines.&amp;nbsp; They plan to fly the upgraded suborbital experiment, and analyze the results from this and the two previous EUNIS flights.&lt;/p&gt;
&lt;p&gt;There are several key parameters that will be studied through simulation, including 1) controlling spatial and spectral crosstalk on the detector, determining the proper spectral resolution and bandpass to meet both science and speckle removal constraints, 3) characterizing the instrument throughput and the required source brightness at the ExEP HCIT, 4) designing a compact system that will fit above the ExEP HCIT bench, and 5) investigating calibration techniques for the data cube properties. We will 1) design a specialized lenslet array for high contrast imaging that reduces scattered light and 2) design a compact IFS that will fit within the HCIT vacuum chamber&lt;/p&gt;
&lt;p&gt;While In-Situ Resource Utilization (ISRU) studies for Mars return have emphasized methane fuel, only modest work has been done to develop the methane-powered rocket engine. Developing a process that generates liquid hydrocarbons that are compatible with current engine designs is more economical than developing a methane production process, along with developing and certifying new engines that use methane. Fisher-Tropsch (FT) is a commercial-scale technology that currently produces liquid fuels from syngas (CO &amp;amp; H2). FT could easily produce kerosene-type products, like RP-1, therefore eliminating the need for new engines. Front-end systems that produce syngas can be interfaced with the FT reactor thus integrating ISRU with closed-loop Environmental Control and Life Support Systems (ECLSS). Development Approach: Demonstrate the feasibility of deploying the FT technology to produce RP-1 (kerosene) for a Mars return scenario and for a deep-space/lunar habitat mission. The first scenario will demonstrate integrating FT with gas-phase collection of CO2 and conversion to syngas. The second case will integrate FT with gasification to convert solid waste to syngas. Process development and equipment sizing will follow established methods used for sizing ECLSS technologies. Anticipated Outcomes: A detailed feasibility analysis along with process economics for both scenarios. The process model will specify sizing parameters for the system and the results will discuss FT with respect to other proposed ISRU technologies in order to provide a detailed perspective on process economics.&lt;/p&gt;
&lt;p&gt;Key NCPS project objectives are to conduct preliminary design, fabrication, and test of representative fuel samples and partial length fuel elements for the two primary NTP fuel forms identified by NASA and DOE &amp;ndash; NERVA carbide &amp;ldquo;graphite composite&amp;rdquo; and ceramic-metallic (Cermet) fuels; further define NTP system concept designs that can meet the mission requirements of Mars DRA 5.0 and serve as a basis for the above two primary fuel elements/types for both a smaller demonstration sized engine and the larger Mars Crewed Vehicle sized engine (25 klbf); and using the results of the above fuel development and testing as well as other heritage NTP data, develop fuel downselection criteria and recommendations to support a fuel&amp;nbsp;type downselection in early FY 2015.&lt;/p&gt;
As the teams supporting NASA missions become increasingly diverse and dispersed new means of sharing data and experiences among team members are required. Collaboration must occur across teams in different geographic locations, different time zones and, in the case of missions on the distant horizon, different generations. Each of these teams has different expertise and uses different tools to meet their goals, yet they must all somehow come together to achieve a single vision. Distributed Visualization strives to unify teams and technologies by providing a common mechanism for sharing and integrating pertinent data.  To accomplish this task, algorithms, software, data formats, data systems, and process are examined to identify and implement those which will best enable the sharing and integration of simulation-based information across temporal and spatial boundaries.

To date, demonstrated work in Distributed Visualization has dealt with physics-based simulations and utilized a variety of graphics engines and toolkits. In addition to the application of these technologies, significant effort has been expended to define data elements, identify process commonality among simulation teams, establish interfaces, and evolve data standards. This approach has resulted in a tool agnostic capability that relies on simple inputs and requires virtually no knowledge of how the data was generated, which allows collaboration without sharing source algorithms and system properties.  Validation has been performed using simulation results from Glenn, JPL, JSC, KSC and Langley, generated in everything from Dassault?s Delmia to Google Sketchup.
Research areas for further enhancement include: use of data from other types of simulators (ex. Computational Fluid Dynamics, Discrete Event Simulation, Distributed Simulation), local storage vs. centralized storage, system latency and other network-induced challenges, and human-computer interaction.
&lt;p&gt;
	N/A&lt;/p&gt;
&lt;p&gt;Find numerical solutions to the non-linear partial differential equations describing our amplifier transmission lines. Optimize periodic choke structure to block shock formation while maximizing parametric gain. Measure the microwave properties of our transmission lines at cryogenic temperatures.&lt;/p&gt;
&lt;p&gt;Develop scalable graphene-based bolometer technology. Use low pressure chemical vapor deposition (LPCVD) technique to grow large area graphene. Develop a process to make saturable absorber with single layer, as well as multilayer graphene. Test and characterize graphene samples with in-house developed laser transmitter.&lt;/p&gt;
&lt;p&gt;
	N/A&lt;/p&gt;
&lt;p&gt;
	&lt;strong&gt;&lt;u&gt;Methodology&lt;/u&gt;&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;
	The approach is highly focused and well conceived.&amp;nbsp; Two rocket payloads will be launched under day and night conditions to study the mass and height distributions, and charging of the MSPs. These will be launched in the Fall period to study the characteristics of the MSPs without the complications introduced by the presence of NLCs and other phenomena containing ice droplets.&amp;nbsp; The campaign has been selected for And&amp;oslash;ya Rocket Range&amp;nbsp; (ARR) in Norway because of the nearby ALOMAR Observatory, which is composed of several critical lidars and radars for support of this mission.&amp;nbsp; The program is a follow-on to an earlier program conducted from ARR in 2007.&amp;nbsp; In this case, the prime instrument is the MASS or aerosol mass analyzer, which has been improved to increase the mass range of particles observed in the earlier mission. It is accompanied by Faraday rotation radio propagation experiment to measure electron density, a positive ion probe pair, a payload potential measurement, UV and photoelectric measurements and dust detectors.&lt;/p&gt;
&lt;p&gt;
	N/A&lt;/p&gt;
&lt;p&gt;
	The approach is to measure ExB drifts (through electric field observations) in conjunction with E and F region turbulence observations.&lt;/p&gt;
&lt;p&gt;
	This will be accomplished via a twin rocket launch from Kwajalein. The two rockets would have apogees of 200 and 350 km so measurements will be made simultaneously in the E and F-region. and will be instrumented to determine&lt;/p&gt;
&lt;ul&gt;
	&lt;li&gt;
		DC and AC electric fields&lt;/li&gt;
	&lt;li&gt;
		the plasma density and its structures,&lt;/li&gt;
	&lt;li&gt;
		the spectral properties of ionospheric E and F region irregularities.&lt;/li&gt;
&lt;/ul&gt;
&lt;p&gt;
	The rocket measurements will be complemented by a comprehensive array of ground-based instruments including interferometric coherent scatter radar observations and GPS and ionosonde data. Neutral winds will be determined from chemical release trails.&lt;/p&gt;
&lt;p&gt;Low return loss package design Improve amplifier mismatch at the package and chip interface Multi-branch MKID design to increase readout frequencies Silicon membrane of 1.45 or 5 micron-thick strong enough to support membrane size of 18x18 mm2 Automated software for large array measurement and computation.&lt;/p&gt;
&lt;p&gt;This IRAD proposal investigates and proposes different small, efficient, low cost, reliable, and robust antenna design concepts with stable electrical and radiation characteristics in harsh space environments for cube/small satellites. Objective 1: Investigate what type of novel antennas have been considered, designed and implemented on previous CubeSat/Small Satellites. Objective 2: Perform some analytical and numerical analysis work to come up with a design skeleton. Objective 3: Running simulations to further optimize proposed antenna designs as well as investigate performance in the presence of physical small satellite structures. Objective 4: Designing a novel CubeSat/Small satellite antenna baseline.&lt;/p&gt;
&lt;p&gt;Future missions will need compact, efficient refrigeration systems for science as well as other uses. NASA should take advantage of the latest state-of-the-art technology on Earth and leverage that for use in space. Space Shuttle had vapor compression refrigerator-freezers, but they required servicing after every mission due to their design to avoid micro-gravity issues. Space Station has thermoelectric refrigerator-freezers which avoid micro-gravity issues, but are not energy efficient. There is no currently acceptable vapor compression refrigerator-freezer (the mainstay of refrigeration on Earth) for use in space. Utilizing a very small, oil-free compressor that has just come onto the market, we will build a proof-of-concept micro-gravity compatible vapor compression refrigerator-freezer that can be used to store medical and other science samples at temperatures from +5C to -20C. Space Station thermoelectric refrigerator-freezers have had some in-flight issues.&amp;nbsp; Thus, this proposal addresses the challenge of Space Health and Medicine.&lt;/p&gt;
&lt;p&gt;Thermal modeling and Test plan to be carried out and developed by Goddard Space Flight Center. This project will be done in collaboration with partners at MIT and Draper Laboratory Basic Thermal Model, Oct. 1, 2011; Final Thermal Model, Mar. 1, 2012; Draft Test Plan, Mar. 1, 2012; Final Test Plan, July 1, 2012.&lt;/p&gt;
&lt;p&gt;The goals of this project are to 1) develop modular power design concepts for human exploration flight vehicles (longer-term) and assess, develop,&amp;nbsp;and/or improve power system designs&amp;nbsp;for AES/HEOMD ground/flight demonstrations (nearer-term) ; 2) demonstrate the modular power design concepts, by participating in annual ground demonstrations, infusing power technologies developed by the Space Technology Program Game Changing Development (GCD) Space Power Systems (SPS) project,&amp;nbsp;Small Business Innovative Research (SBIR), and other government agencies as practicable; and 3) demonstrate and verify the operation of the modular power systems in a relevant, end-to-end ground test environment. The AMPs project will pursue rapid hardware development cycles for such exploration systems. Also, the AMPs project will determine a family of common power modules, delivering at least one system each year and repeating the requirements, design, build, test, learn process each year.&lt;/p&gt;
&lt;p&gt;Using analytical methods to conceptualization L-band antenna structures that offer potentials of wideband operation. Perform extensive computer simulations on these antenna structures for their RF performances. Select optimum design for final fabrication and testing.&lt;/p&gt;
&lt;p align="LEFT"&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	&lt;font size="3"&gt;Near-simultaneously deployed chemical tracer trails over an extended horizontal range will be used to obtain measurements of the turbulent structure function and (the pair) relative velocity distribution over a range of spatial scales covering a full decade. &lt;/font&gt;&lt;/p&gt;
&lt;p&gt;
	&lt;font size="3"&gt;Trimethyl aluminum trails (TMA) released in the mesosphere and lower thermosphere have been used to trace the neutral motions over 500 times since 1958. Such releases are a simple and reliable method for obtaining horizontal velocities with good accuracy and height resolution. Deriving the diffusion characteristics is more difficult but two detailed studies of the expansion rates have been carried out. Analyses from the earlier experiments show enhanced or anomalous diffusion rates in a 10 to 15 km altitude range above the turbopause. (MAJOR)&lt;/font&gt;&lt;/p&gt;
&lt;p&gt;
	&lt;font size="3"&gt;Even if only partially successful, this study is expected to contribute significantly to our understanding of turbulent motions in the atmosphere as turbulence at small scales is currently poorly understood. (MINOR)&lt;/font&gt;&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;We will demonstrate a full, end-to-end, lobster-eye optic instrument at GSFC. The STORM prototype is fully self-contained, including integrated pre-amps, HV power supplies, and C&amp;amp;DH. The workplan includes integrating the optics panels into the optics holder, developing the C&amp;amp;DH code on the integrated FPGA, deploying the instrument in GSFC&amp;rsquo;s 100m and/or 500m x-ray beamlines and measuring end-to-end performance including image quality and throughput as a function of x-ray energy.&lt;/p&gt;
We propose to develop and optimize 0.5 cm thick Cadmium Zinc Telluride (CZT) detectors with very small pixel pitches, i.e. 350 micron and 600 micron. The proposed innovative R&amp;D program is highly relevant for the EXIST  (Energetic X-ray Imaging Survey Telescope) mission, the leading candidate for NASA's black hole finder probe. The new EXIST reference design from the recent Advanced Mission Concept Study uses CZT detectors with a pixel pitch of 600 micron. The proposed work focuses on the optimization of the design of the pixel patterns (pad and gap widths), steering grids, guard rings, and bias rings. For the different designs, the detection efficiencies, energy resolutions, charge sharing properties, and minimum achievable energy thresholds will be evaluated. Dedicated measurements with collimated X-ray beams will be performed to evaluate the accuracy with which the depth of the interaction can be reconstructed based on different methods. Measurements with polarized X-ray beams will be used to put estimates of the X-ray polarization sensitivity of EXIST on a solid footing. Last but not least, the experimental results will be used to fine-tune a 3-D model of the detector response. The proposed R&amp;D is exciting and new in that very thick detectors with very small pixel pitches will be studied for the first time in detail. Effects like charge carrier diffusion and charge carrier repulsion are relatively more important for such detectors than for thinner detectors and/or detectors with larger pixel pitches.
&lt;p&gt;
	Results of PIDDP have contributed to the development of flight hardware flown on, or selected for, many of NASA&amp;rsquo;s planetary missions. The instrument technology selected through PIDDP addresses specific scientific objectives of likely future science missions. Instrument definition and development studies take place at several stages, including feasibility studies, conceptual design, laboratory breadboarding, brassboarding, and testing of critical components and complete instruments. The technology readiness level (TRL) that PIDDP supports is TRL 1-6. For immature or particularly complex new instruments, proposers initially may choose to only define or develop the most risky components. When the proposed effort is for a component only, the proposed effort describes one or more likely scenarios for possible follow-on instrument development. Scientific objectives of the instruments, proposed follow-on instruments, and future candidate missions are discussed in the proposal for each selected activity. It is the responsibility of the proposer to demonstrate how their proposed instruments address significant scientific questions relevant to stated NASA goals and not for NASA to attempt to infer this.&lt;/p&gt;
&lt;p&gt;We plan to develop a blackbody coated with Carbon nanotube materials that will able to operate in the temperature ranges need to calibrate a thermal infrared sensor for Earth Science missions. The carbon based nanotube material, developed through the NASA GSFC IRAD, will be evaluated as a surface treatment for onboard blackbody calibrators (OBCs). The aforementioned material can reduce stray light that can be introduced into an instrument from an OBC and effect the integrity of the data at is be collected. Also, a sufficiently uniform coating will simplify the geometry of the target, which reduces development time, manufacturing time, and cost of the OBC. Silicon has been determined to be an acceptable growth medium for the carbon nanotube coating. We will evaluate the effect of the paint/substrate layer thickness will have on the thermal gradient to see if we get the desired emissivity. Also, we want to verify that the thermal mass is sufficient to hold a stable thermal temperature. Once the OBC system is defined, a ray trace study will be conducted to assess the emissivity off the blackbody and the irradiance. The final product, an OBC performance model, could eventually be used as a tool to size a blackbody calibrator for future missions, such as a thermal imager for a future Landsat mission, the Visible Infrared Imager Radiometer Suite (VIIRS) instrument on the next generation Joint Polar Satellite System (JPSS) and the thermal infrared instrument that has been proposed for Hyperspectral Infrared Imager (HyspIRI).&lt;/p&gt;
&lt;p&gt;If successful, the project will produce a prototype embedded hypervisor system that consists of a of a LEON3 processor board, a real time Core Flight Executive Virtual Machine, and a Science Data processing Virtual Machine. The system will be benchmarked against the standard embedded software running on the LEON3 in order to evaluate the performance impact of the embedded hypervisor. Detailed steps include: 1. Research and Purchase Hardware and Software 2. Define Software Development Environment 3. Setup Lab and Software Development Evironment 4. Establish Configuration Management System 5. Prototype Virtualization Environment 6. Integrate Hypervisor Software 7. Design/Document Virtual Machine Deployment and Communication Software 8. Develop Virtual Machine deployment and Communication Software 9. Develop/port linux data processing software 10. Design and develop tests 11. Run tests 12. Document Results and plan follow on work.&lt;/p&gt;
&lt;p&gt;The effort will focus on P-Band and L-band polarimetric radar architectures that employ advanced and innovative techniques to increase the science value of the measurements while achieving it at a lower cost.&lt;/p&gt;
The focus of MMAMA is on providing high-fidelity scientific investigations, scientific input, and science operations constraints in the context of planetary field campaigns. Funding provided in this program element is intended to enable researchers to conduct scientific investigations and integrate their instruments, projects, and/or protocols into field activities designed to help NASA plan for future exploration of the Moon, Mars, and other planetary bodies with both robots and humans. The MMAMA R&amp;A Lead estimates that approximately two-thirds of the effort funded through MMAMA is technology-related.  

Through this research program element, investigators are selected to carry out specific scientific research analogous to investigations anticipated for missions to asteroids, the Moon, and/or Mars. Areas of specific interest to the Science Mission Directorate (SMD) include, but are not limited to:
1. Understanding and optimizing human and robotic performance to maximize scientific return;
2. Defining science requirements for human missions, including requirements for mobility, navigation, communications, in situ analysis, surface laboratory functionality, crew scheduling, and sample acquisition, handling, documentation, and curation;
3. Developing surface science scenarios for use in architecture planning and science payload manifesting; and
4. Illuminating areas of critical importance for robotic precursor missions, including robotic operations of/with human-oriented systems during periods when humans may not yet be present.
5. Field testing of robotic, teleoperated, and human-operated instruments.

Although this is primarily a Planetary Sciences call, proposals in other areas of SMD research such as Heliophysics, Astrophysics, and Earth Science are considered, to the extent that they reflect NASA?s strategic scientific goals at asteroids, the Moon, and/or Mars.
PPR supports research to improve NASA's understanding of the potential for both forward and backward contamination, how to minimize it, and to set standards in these areas for spacecraft preparation and operating procedures. Improvements in technologies and methods for evaluating the potential for life in returned samples are supported. 

The PPR R&amp;A Lead estimates that approximately 40&#37; of the effort funded through PPR is technology related, particularly in the following areas:
? The development or adaptation of modern molecular analytical methods to rapidly detect, classify, and/or enumerate the widest possible spectrum of Earth microbes carried by spacecraft (on surfaces and/or in bulk materials, especially at low densities) before, during, and after assembly and launch processing. Of particular interest are methods capable of identifying microbes with high potential for surviving spacecraft flight or planetary environmental conditions (e.g., anaerobes, psychrophiles, radiation-resistant organisms); and
? New or improved methods, technologies, and procedures for spacecraft sterilization that are compatible with spacecraft materials and assemblies.

PPR's research areas derive directly from recent National Research Council (NRC) recommendations on planetary protection for solar system exploration missions (see http://planetaryprotection.nasa.gov/documents/ for online reports and a list of publications).
&lt;p&gt;The objective is to develop a 2-Dimensional Far Infra-Red Magnesium Diboride Array (2D FIR MDA) to use in NASA&amp;rsquo;s future planetary exploration instruments. The array will have better signal-to-noise (S/N), almost two orders of magnitude higher sensitivity and better spatial resolution than the FIR detectors (thermopiles) currently on CIRS/Cassini. Each pixel in the array is of the composite detector type with the thermal sensor made out of HTS MgB2 thin film meander.&lt;/p&gt;&lt;p&gt;We will establish the D* and time constant of our MgB2 bolometer pixel with accuracy and confidence.&lt;/p&gt;
Activities advance the development of scientific instruments or instrument components to the point where the instruments could credibly be proposed in response to future flight opportunity announcements, including instruments that could be accommodated on or in small satellites (under 50kg total spacecraft mass), or as small payloads in support of future science activities associated with missions of human exploration (proposals to build and fly hardware on a specific mission opportunity are not a part of this program element and the development of instruments for use in future field campaigns is under ASTEP).

The scientific goals and objectives of NASA?s Astrobiology program are described in the Astrobiology Roadmap that is available on the Astrobiology web site at http://astrobiology.arc.nasa.gov/roadmap. Instrumentation and astrobiology mission concepts developed from research supported through this ASTID program element are meant to address two fundamental questions in Astrobiology, namely, ?How does life begin and evolve?? and ?Does life exist elsewhere in the Universe?? Objectives that could be addressed by new spacecraft instrumentation and astrobiology small payload missions include, for example:
? To determine whether the atmosphere of the early Earth, hydrothermal systems, or exogenous matter were significant sources of organic matter;
? To search for evidence of ancient climates, extinct life, and potential habitats for extant life on Mars;
? To determine the presence of chemical precursors and potential habitats for life in the outer Solar System; and
? To determine if compounds of biological significance are present beyond our Solar System.
&lt;p&gt;Task includes: Thermal/mechanical design study&lt;/p&gt;
&lt;p&gt;Graphene thin films will be fabricated using Low Pressure Chemical Vapor Deposition (LPCVD), Films will be selected and doped to reduce sheet resistance. The films will be patterned with electrical contacts in an array format. Optical transparency and electrical conductivity of the films will be characterized.&lt;/p&gt;
&lt;p&gt;Development of a cost-effective, robust, tunable, miniaturized, ruggedized, and flight tested swept laser for in-flight structural health monitoring. The objective of this effort is to research and develop a NASA flight certified tunable swept laser system that is comparable to the performance of currently-deployed swept lasers but are lower cost, lighter weight, lower volume, and are flight-ruggedized for vehicle health monitoring applications.&lt;/p&gt;
&lt;p&gt;We will perform lab bench evaluations using Analog Devices Lyric Labs evaluation hardware as well as the&amp;nbsp;NASA/GSFC Radiation Effects and Analysis Group field-programmable gate array (FPGA)-based low-cost digital tester. &amp;nbsp;The evaluation hardware will be used to inform spaceflight hardware design decisions. &amp;nbsp;The Analog Devices Lyric Labs&amp;nbsp;probability processing technologies are fabricated in commonly-available commerical complementary metal oxide semiconductor (CMOS) processes. &amp;nbsp;Part of this project will also be to interface with other technology developers and scientists, both inside and outside of NASA/GSFC. &amp;nbsp;Analog probability processing is enough of a paradigm shift that the end-user applications may not be known &lt;em&gt;a priori&lt;/em&gt;&amp;nbsp;and may either be based on insertion into pre-exisiting functions or development of new capabilities that could not be realized with existing hardware. &amp;nbsp;The probability processing hardware utilized for this project is the property of&amp;nbsp;Analog Devices Lyric Labs and was developed under a Defense Advanced Research Projects Agency (DARPA)&amp;nbsp;contract. &amp;nbsp;There is currently follow-on work at DARPA under the&amp;nbsp;Unconventional Processing of Signals for Intelligent Data Exploitation (UPSIDE) program.&lt;/p&gt;
"Summary:



The Laser Interferometer Space Antenna (LISA) mission is under consideration by NASA and ESA as a joint mission to study gravitational wave signals from a number of types of astrophysical sources at frequencies below 1 Hertz.  These include mergers of massive black hole binaries out to redshifts of 10 or more and inspirals of stellar mass black holes into galactic center black holes at redshifts out to about 1.  Extremely sensitive tests of the predictions of general relativity will be tested under highly relativistic conditions by the measurements.



Two dual-cylinder resonant cavities for laser stabilization which are suitable for hard-mounting in spacecraft have been designed and constructed under previous NASA support.  Evaluation and testing of these cavities now is being started under NASA Award NNX09AD11G.  The cavities have been designed to have substantially reduced sensitivity to vibrations and to temperature variations at frequencies above 1 millihertz.  The relative frequencies for the two cavities in their separate small vacuum chambers will tested under a range of different conditions.  In addition, a search will be made for occasional small glitches in the phase of lasers locked to the two cavities, which could cause temporary disturbances in the LISA measurements if they occurred too frequently.



It now has become clear that the desired range of measurements on the cavities can't be completed by the end of the present funding period.  Thus funding is requested under this proposal for two additional semesters of support for a graduate student in order to complete the desired measurements. The category under which this proposal is being submitted is Supporting Technology."
&lt;p&gt;The existing HDWLT (pictured) contoured composite structure design, its analyses and manufacturing tools, will be used to validate key analyses inputs through structure manufacturing, collecting relevant test data and assessing the performance parameters.&lt;/p&gt;
"Since the summer of 2000 we have successfully deployed a high resolution x-ray microcalorimeter spectrometer, based on the spaceflight XRS instrument, at the Electron Beam Ion Trap (EBIT) facility at the Lawrence Livermore National Laboratory. Over the last decade, this highly successful partnership has made fundamental measurements in laboratory astrophysics including the measurements of the absolute cross sections of all the Fe L shell transitions from Fe XVII to Fe XXIV, line ratios in Fe and Ni L shell transitions, measurements of Fe K shell emission over a wide range of electron energies, and direct measurements of charge exchange emission from highly ionized Fe, O, N, and most recently L shell S, using a variety of donor gases. This work has resulted in the publication of over 30 peer-reviewed articles with many more either submitted or in preparation. The newest addition to the facility, the ECS microcalorimeter spectrometer, developed under this program, has performed flawlessly as a facility-class instrument since 2007.



We propose here to continue our highly successful partnership and deploy new technology to resolve lines in the important 1/4 keV band that encompasses the M-shell iron emission and the L shell emission, including charge exchange, of many of the lower-Z elements, such as Si, S, Mg, Ne, Ca, and Ar. We thus propose completing a new spectrometer that will bring substantially improved performance to the laboratory astrophysics program at EBIT and will enable fundamentally new measurements. Thus, in addition to maintaining the current spectrometers, which will begin this work, a significant component of this proposal is the completion of a new spectrometer leveraged off of the substantial progress in high-resolution x-ray detectors developed for the International X-ray Observatory mission. The spectrometer will be composed of a detector system with unparalleled spectral resolution: 2 eV resolution across the 0.05-10 keV band. This will allow
&lt;p&gt;
	N/A&lt;/p&gt;
&lt;p&gt;
	We propose to observe the solar upper transition region and lower corona in Ne VII 46.5 nm with the Multi-Order Solar EUV Spectrograph (MOSES) rocket payload. The solar plasma in this temperature range, about 500,000 K, has not been imaged at rapid cadence since Skylab (Feldman, 1987). The unique observational capabilities of MOSES, demonstrated already in He II 30.4 nm, enable simultaneous imaging and measurement of line widths and doppler shifts over a large (20&amp;rsquo; x 10&amp;rsquo;) field of view, with typical active region exposure times of 10 s. These observations will reveal the 3D dynamics of outflows and reconnection events in active regions, quiet Sun, and coronal holes. The primary objectives of this one-year proposal are (1) instrument calibration, (2) launch of the rocket in summer of 2012, and (3) data analysis, including exploration of new techniques to recover more spectral information from the MOSES data. Prior NASA funding has enabled data analysis and publication of results from the first flight, upgrades to the payload, and increased reliability of our ground support equipment. Procurement of optics to observe the Ne VII 46.5 nm line is in process. With the help of additional funding from Montana Space Grant Consortium, we have also developed an EUV calibration facility optimized for testing the MOSES payload.&lt;/p&gt;
&lt;p&gt;
	N/A&lt;/p&gt;
&lt;p&gt;
	The Earth&amp;rsquo;s ionosphere is home to a number of phenomena that are regularly observed but still unpredictable; obvious examples include equatorial spread F, tidal ion layers, and sporadic E. The fundamental connection between these disparate events is that all three are strongly influenced by coupling between ionized and neutral particles. Most of what we know about these phenomena comes from plasma diagnostics &amp;ndash; we can accurately measure electric fields, plasma density, and plasma temperatures in the ionosphere using &lt;em&gt;in-situ &lt;/em&gt;probes, ground-based radars, and optical remote sensing techniques. Our ability to measure the neutral temperatures, densities, and motions at ionospheric altitudes is significantly less mature. We therefore propose to develop a low-power transducer system that will enable accurate measurements of neutral pressure and winds when assimilated into existing instrumentation systems. The low power aspect of this transducer concept is particularly important, since it is compatible with very small satellite platforms such as CubeSats. When deployed on constellations of small satellites in different orbit planes, instruments built around the small sensors we develop will be capable of providing simultaneous global measurements of neutral pressures and winds. These measurements will produce marked improvements in our predictive models, and bring us one step closer to forecasting the diverse phenomena that arise due to ion-neutral interactions in the upper atmosphere.&lt;/p&gt;
&lt;p&gt;
	NASA&amp;rsquo;s Mars Exploration Program (MEP) calls for a series of highly ambitious missions over the next decade and beyond. The overall goals of the MEP must be achieved with relatively low mission risk and within tightly constrained cost resources. The current overarching scientific goals of the MEP are: life, climate, geology, and preparation for human exploration. These have a common, measurable link: water. For Mars (like Earth), water is central to the planet&amp;rsquo;s history; it is also the primary reason for interest in it as a potentially habitable world. No new proposals are being solicited or funded in FY 2012 under this project line. Proposals for Mars instrument technology development are now included in PIDDP and no new awards will be provided under the Mars Instrument Development Program (MIDP).&lt;/p&gt;
Radioisotope Power Systems (RPS) is a multicenter, multiagency (with the Department of Energy (DOE)) program whose purpose is to manage the Science Mission Directorate?s investments in radioisotope power systems and their deployment to future missions. The majority of these missions are a result of planning arising from the Planetary Science Division.

RPS is responsible for acquisition and development of thermal energy conversion technologies and related system technologies and with the DOE, acquisition and development of flight radioisotope power systems for future mission uses. In addition, the RPS Program is responsible for maintaining a capability to acquire future systems through strategic investment in unique competencies that may be needed by future missions.

One element of RPS is Radioisotope Power Systems Technology Development. The goal of the radioisotope power systems? technology portfolio is to advance performance of RPS through new and novel innovations being developed and transitioned to flight systems. Historically, this has been achieved through an increase of energy conversion efficiency. The mission users benefit from such a gain in performance because an increase in the specific power (power per unit mass) reduces the spacecraft mass. This reduction can also enable a larger instrument suite. The effort to improve efficiency has taken on renewed significance with the increased constraint posed by a limited supply of Pu-238. Current investments include improving efficiency of thermoelectrics through novel materials selections, the Stirling conversion process, and supported systems development on materials and electronics.
"We propose to continue our detector development program in X-ray astronomy. Under our current grant we are developing a new

type of active pixel detector. The current funding allows us to carry this design through CDR, but will not cover fabrication of the detectors. Here we propose to build and test these innovative detectors, which could potentially be employed in future missions such as IXO, Xenia, Gen-X, and SMEX/MIDEX-class missions. This proposal supports NASA's goals of technical advancement of technologies suitable for future missions and training of graduate students."
We propose the development of a physical-vapor-deposition coating technique to correct residual figure errors in grazing-incidence optics. The process involves selectively depositing a filler material to smooth out the low-to-mid-spatial-frequency errors that typically dominate the performance of x-ray optics. We have demonstrated proof-of-concept on small (few-cm scale) full-shell optics intended for medical imaging. We propose here to scale the process up to larger mirrors applicable to astronomy. Simulations indicate that given adequate metrology, substantial improvements in angular resolution are possible through application of the technique. The process is applicable to full shell or segmented optics, either mounted or unmounted, and can in principal also be used to figure short reflectors. Examples of programs that could benefit from this technique include the large mission IXO and smaller explorer-class missions such as WFXT.
&lt;p&gt;ROCSTAR is an in situ instrument suite that can accomplish rapid mineral and molecular identification without sample preparation for in situ planetary exploration; inform the investigation with regard to trace element geochemical deviation from end member stioichiometry; operation as a spectroscopic imager for chemical mapping. It includes dual wavelength Raman spectroscopy, 380 - 2500 nm reflectance spectroscopy, visual imagery and thermal measurements.&lt;/p&gt;
&lt;p&gt;Configure LIBS system to view samples in the Venus chamber Confirm STP results for LIBS in Venus Chamber configuration Conduct high temperature/high pressure experiments on Columbia River Basalt.&lt;/p&gt;
AMMOS Technology tasks include:
 - Enhance mission planning and sequence generation tools with constraint based automated planning and scheduling techniques to enable greater levels of ground automation.
 - Demonstration of automated mission planning for tactical surface operations
 - Developing a multi-objective optimization tool for use in science planning for complex observatory scheduling.
 - An automated method to diagnose spacecraft systems from telemetry, generating models from standard test data and system documentation only
 - Develop Level 2 data product creation framework for producing atmospheric profiles.  The framework will be multimission and will allow subsequent missions to leverage on the implementations of previous missions
 - Automatic analysis discovers near-invisible signals and rapidly drafts maps of surface materials
Develop Orbital stability analysis algorithms, mean element orbit control/sizing algorithms
 - Develop flexible, reactive, multimission b??smartb? executive for AutoNav/AutoGNC
 - Develop algorithms to optimize the time of finite burns within a multi-body gravity field.
 - Develop tools and a handbook to quickly survey and generate low-energy transfers between the Earth and Moon, including transfers to low lunar orbits and three-body orbits.
 - Develop a strategy using an optimal sequence of flybys and observations to do rapid characterization (shape, gravity, and environment) of small bodies (including binaries) without entering orbit or placing the S/C into an unstable state
"We propose to develop a revolutionary x-ray camera for astrophysical imaging spectroscopy. High-resolution x-ray spectroscopy is a powerful tool for studying the evolving universe. Emission line ratios (e.g. within the He-like triplet) provide density and temperature diagnostics. Emission and absorption line energies identify ions and determine their velocities, and the shape of the lines can be used to study turbulence or the relativistic effects of a supermassive black hole. The grating spectrometers on the XMM and Chandra satellites demonstrated the power of high-resolution x-ray spectroscopy for astrophysics, but there remains a need for instrumentation that can provide higher spectral resolution with high throughput in the Fe-K band and that can enable spatial/spectral investigations of extended sources, such as supernova remnants and galaxy clusters. The instrumentation needed is a broad-band imaging spectrometer - basically an x-ray camera that can precisely resolve x-ray energies and fluxes over a large field-of-view.



 While we do not claim that in 3 years we will have developed such detectors, we advocate developing the technology that has the greatest potential for achieving this. Theoretically, magnetically-coupled microcalorimeters are best equipped to achieve sub-eV energy resolution in very large formats. We propose to build upon the work carried out by our group on metallic magnetic calorimeters (MMC) in the antecedent program. The great promise of MMCs for sub-eV energy resolution has been recognized for years. During our current research program, an accident in detector fabrication produced devices that derived their sensitivity from a different operating principle - the temperature dependence of a superconduc
Technologies include, but are not limited to, electric and advanced chemical propulsion, propellantless propulsion such as aerocapture and solar sails, sample return ascent vehicles, and Earth return systems. 

ISP will enable access to more challenging and interesting science destinations, including enabling sample return missions. ISP continues to advance several propulsion technologies in support of future Flagship, Discovery, Mars, and New Frontiers missions. The ISP portfolio continues to invest in high-priority technology areas such as the electric propulsion and aerocapture/Earth entry, descent, and landing technologies identified in the Solar System Exploration Roadmap, the 2010 SMD Science Plan, and the 2011 Planetary Decadal Survey.  The ISP project is highly responsive to the Decadal Survey.

The ISP project will complete the 7kW NASA's Evolutionary Xenon Thruster (NEXT) Power Processing Unit (PPU) repair in 2012, and will complete NEXT PPU characterization and integration testing and long duration validation testing of the NEXT thruster in 2013. ISP is completing the electric propulsion 4kW High Voltage Hall Accelerator (HiVHAC) thruster development task, is assessing commercial Hall systems, and will start long duration testing of the HIVHAC thruster in 2012. The Hall system power processing unit (PPU) and other subsystem technology development starts development in FY 2012.  High Voltage Hall Accelerator (HiVHAC) thruster technology is applicable to Earth return vehicles (ERV), transfer stages, and low-cost electric propulsion systems for Discovery-class missions. In FY 2012 ISP will continue development of NDI techniques and a detailed design for a lightweight propellant tank applicable to the Skycrane. ISP will continue completing Earth Entry Vehicle (EEV ) heat shield micro-meteoroid/orbital debris characteristics studies, a preliminary design of a multi-mission Earth entry vehicle (MMEEV) concept and continuing MMEEV technology development.
We propose to continue our program of emission line astronomy featuring three areas of emphasis: 1) The distribution and nature of high redshift emission line galaxies, using the Lyman alpha and other rest-frame UV lines; and the study of planetary systems in formation in the first 10 Myrs, with the interplay of circumstellar disks and jets; and spectral differencing of transiting planets. 2) We are extending the capability of our Goddard Fabry-Perot Imager by incorporating a Coronagraphic Integral Field Spectrograph (CIFS), and will continue our observations with the improved instrument. We request support for completing the commissioning of the instrument, and for its maintenance and operation. The CIFS, which has been delivered to the Apache Point Observatory's 3.5-m telescope, consists of a custom microlens array and magnifier section, a grating wheel assembly, and a photon-counting electron-multiplying CCD (EMCCD), within the optical train of the Fabry-Perot. The instrument is switchable between Fabry-Perot and IFS modes. It provides observational support to interpret data from the HST, Spitzer, Chandra, Herschel and soon JWST space observatories with capabilities not available on them, and will be used to develop technology for future NASA flight programs such as WFIRST, and NWO, THEIA, ATLAST and other planet-finding missions. In this period we propose to extend the wavelength coverage of the CIFS, by extending the format of the EMCCD.
"We propose to develop high contrast coronagraphic techniques for segmented telescopes, providing an integrated solution for wavefront control and starlight suppression on complex aperture geometries. Developing this technology will enable direct imaging of exoplanets from space with significant cost savings relative to monolithic mirrors. 



Searching for nearby habitable worlds with direct imaging is one of the top scientific priorities established by the Astro2010 Decadal Survey. Achieving this ambitious goal will require 1010 contrast on a telescope large enough to provide angular resolution and sensitivity to planets around a significant sample of nearby stars. Lightweight segmented mirror technology allows larger diameter optics to fit in any given launch vehicle as compared to monolithic mirrors, making it a compelling option for future space telescopes. But until recently, it was believed that internal coronagraphs were incapable of yielding very high contrast on segmented telescopes.



Recent developments now show that there is in fact a clear path to high contrast coronagraphy on segmented apertures. The key advances are (1) the demonstration of precision wavefront shaping with amplitude control using multiple deformable mirrors, and (2) improvements in coronagraph mask design that dramatically reduce transmission of segment-gap-scattered light.



We propose a plan that will mature these technologies for coronagraphy with on-axis segmented mirror telescopes to TRL 4 by mid-decade with the following elements:

1.	Numerical studies for coronagraph optimization and wavefront shaping to yield high-contrast point spread function dark zones.

2.	Precision segment phasing concepts and algorithms that will improve the state of the art by one order of magnitude, and will be applicable to any segmented telescope.

3.	A system-level demonstration integrating segment precision phasing, wavefront control and shaping, together with advanced coronagraphy. 



Success
&lt;p&gt;
	&lt;span style="font-size: 12px;"&gt;&lt;span style="font-family: times new roman,times,serif;"&gt;&lt;font color="#000000"&gt;&lt;span style="mso-fareast-font-family: Calibri; mso-fareast-theme-font: minor-latin; mso-bidi-font-family: TimesNewRomanPSMT; mso-ansi-language: EN-US; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;"&gt;Launch a single rocket from Andoya Rocket Range into an active cusp event. Observe electric and magnetic fields, HF waves, electron and ion distributions and wave-particle correlations between electric wave fields and downgoing electrons. Ground all sky camera data from Svalbard will be used to provide context, along with CUTLASS radar data. &lt;/span&gt;&lt;/font&gt;&lt;/span&gt;&lt;/span&gt;&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	&lt;strong&gt;Methodology &lt;/strong&gt;The methodology is based on making comparisons between downward electron flux, DC electric fields, electromagnetic waves, and auroral morphology. The proposed project will launch a rocket from Poker Flat over Fort Yukon to an apogee of 200-300 km when arc or arcs are present that has optical shear-flows present. Data from downgoing electron fluxes over a large energy range, electron density (Langmuir probe), electric and magnetic fields from the in-situ rocket payload and images from all-sky and narrow field cameras at Poker Flat and Fort Yukon will be produced and analyzed. All instrumentation is selected so that high temporal resolution can be achieved. &amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	The methodology developed under this grant is primarily an effort to develop new sub-payload technologies and an inexpensive method of testing them. The three technical goals are: (1) to improve and test the existing spring sub-payload ejection system and rocket propelled ejection system, (2) to test the performance of ampule-deployed radar chaff (rather than TMA) to track high altitude winds, and (3) to develop and test sensor and telemetry packages to monitor the attitude stability and position of deployed sub-payloads.&amp;nbsp; The proposed effort will also demonstrate very low cost, low altitude rockets as an inexpensive flight test of payloads prior to expensive sounding rocket deployments. The payloads tested on 5 to 7 low-cost rockets will be (1) foil chaff designed for radar tracking of mesospheric winds, (2) plasma instruments composed of GPS monitors, magnetometers, and accelerometers, and (3) android phones for the investigation of off-the-shell instrumentation and telemetry.&amp;nbsp; Finally, a campaign of 2 to 4 sounding rocket deployments on &amp;lsquo;as-available&amp;rsquo; flights from Poker Flats will be used to test spring ejection without spin up, spring ejection with spin up for sub-payload attitude control, and rocket ejection&lt;/p&gt;
Tasks supported by LARS include those that seek to develop new analytical instrumentation or combinations of analytical instruments, or new components of analytical instruments, leading to significant improvements in the precision, resolution, or sensitivity of measurements compared to the existing state of the art. Also supported is the development of new analytical techniques for existing instrumentation that push the limits of current technology, for example, by the elimination of analytical interferences or contamination problems. Work that addresses the needs of current or selected missions have the highest priority.

LARS supports the development of laboratory instrumentation and advanced analytical techniques, as well as the scientific analysis and analytical work on recently returned planetary samples.  Based on analysis of active awards in FY12, the LARS R&amp;A Lead estimates that $2.8M out of $8.1M, or 34&#37; of LARS funds, will be spent on technology, developing new laboratory instrumentation and laboratory sample handling and preparation technologies.  The amount of funding for technology in future years will depend upon the outcome of future ROSES solicitations, peer reviews, and selections.
&lt;p&gt;The laboratory Infrared Microscope that will be built will measure components for remote sensing instrumentation and measure geological samples that would represent samples collected during field campaigns and remote sensing missions. Infrared Microscopy will assure NASA provides quality components and instruments for future remote sensing missions and insure integrity of the instrumentation built. The quality control of instrument components reduces risk and this can be incorporated into a spaceflight mission proposal as a pathway to mitigate risk.&lt;/p&gt;
&lt;p&gt;Fabricate the microchannels using DDL facilities. Develop a process for in situ polymerization inside the microchannels and optimize the chemistry Perform separation of organic molecules to demonstrate device capability.&lt;/p&gt;
&lt;p&gt;Ensemble Detection is both a measurement technique and analysis tool. Like a prism that separates light into spectral bands, an ensemble detector mixes a signal with noise references that span a range of noise powers that produce multiple realizations that comprise an ensemble data set. The resulting ensemble data set represents a comprehensive stochastic description of the signal that is admissible to statistical analysis not otherwise possible with a single realization. Ensemble data sets provide time-varying probability distribution functions from which time varying statistics can be derived. The linear relationship between the reference mean and standard deviation provides a way to discriminate changes in the process mean from changes in the spread of the process&amp;rsquo; probability distribution. Why is this important? Distinguishing between a mean state change and natural variability is a problem that spans multiple scientific disciplines. One important application is discriminating between climate change and natural variability of extreme weather events.&lt;/p&gt;
&lt;p&gt;Mature the design and fabricate the Flare Initiation Doppler Imager (FIDI) instrument to demonstrate low-spacecraft-resource EUV technology (most notably, back-illuminated CMOS) from a 3U CubeSat platform, using a recently-developed EUV Doppler imaging technique (see upper right panel).&lt;/p&gt;
&lt;p&gt;Task 1: rad test AD7746 component for failure dosage for use in GEO Task 2: Algorithm for determining absolute plate spacing of the TIGO Fabry-Perot plates, incorporating reference light into TIGO design Task 3: Demonstrate DLOI technology under development, feasible design for future SBIR.&lt;/p&gt;
&lt;p&gt;Objectives a) Development, evaluation and demonstration of a dynamically reconfigurable optical fiber sensing network that is interrogated using the optical frequency domain reflectometry (OFDR) technique. Such a system will substantially reduce the susceptibility of optical fiber sensing systems to failure in the event of fiber breakage. b) Development and demonstration of a distributed, self-organized approach to configuration control of an optical fiber sensing network that is interrogated using the optical frequency domain reflectometry (OFDR) technique. c) Demonstrate fiber optic distributed strain and temperature sensing on a small-scale heat shield carrier structure. d) Development and demonstration of a method for determining optimal sensor placements with the aim of maintaining adequate accuracy of impact and damage location. e) Development and demonstration of acoustic detection and thermal evaluation of impact damage to a thermal protection system (TPS) attached to the carrier structure of goal c) above. Products Electronically-reconfigurable optical fiber sensor network. Self-organizing distributed system for optimal routing of light in network. Demonstration prototype for health monitoring of a TPS structure.&lt;/p&gt;
"We propose a four-year program for the fabrication and characterization of high dynamic range, low background photon counting detectors that will support the next generation of UV/optical astronomy missions.  These devices will serve as  

technology pathfinders for large format detectors ideal for space-flight applications.  Advanced UV/optical detector systems are essential for addressing NASA's strategic science goals highlighted in the recent Decadal Survey, including a census of the atmospheric properties of extrasolar planets and constraining the physics of reionization in the distant universe.  This program will address these goals through the development and testing of imaging High Event rate ReadOut Integrated Circuits (HEROICs), where independent pixel logic allows sustained count rates of order 1 kHz per pixel when coupled with a microchannel plate detector.  In addition to directly addressing NASA's strategic science goals, this technology will extend the lifetime of UV detectors by operating at a lower gain and enabling a boot-strapping of primary standard stars to fainter magnitudes, both of which address calibration challenges for future high-sensitivity UV instruments.  The proposed program will raise the technology readiness level of these devices from TRL 2 to TRL 4, while developing an architecture that will be compatible with flight applications in NASA's suborbital program.  This technology would then be well-placed for use as a primary science detector on future UV/optical Explorer-class missions and ultimately large strategic missions such as ATLAST."
We propose to develop the next generation MicroShutter Array (MSA) as a multi-object field selector for missions anticipated in the next two decades. For many applications, this field selector improves instrument efficiency proportionally to the number of shutters opened simultaneously. We have successfully developed and built the JWST microshutter array system, which increases the observing efficiency of the Near Infrared Spectrometer by two orders of magnitude. As a result of this development, there is a significant scientific demand for these devices for space-based and ground based applications. The availability of large format microshutters can significantly increase the scientific reach of spectroscopic survey instrument such as WFIRST and future missions such as ATLAST. The basic design of the JWST MSA cannot be extended to such a large scales due to the design limitations set by the required magnetic actuation. We have recently demonstrated shutter operation using DC plus AC resonant pumping. The breakthrough demonstrates that we are able to eliminate bulky permanent magnets used for JWST MSA actuation, thus opening an avenue to create a very large focal plane field selector that can be built at much lower cost. in this program, we will fabricate electrostatically actuated microshutter arrays and demonstrate their performance for use as UV, visible, and infrared field selectors.
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&lt;p&gt;The main objective was to design and manufacture a multi-channel high resolution analog-digital converter for digitizing a CCD image signal. The tasks included schematic capture, simulation, layout and verification leading to a GDSII foundry ready database. The chip was sent for manufacture in August 2012 and silicon was received in October 2012.&lt;/p&gt;
&lt;p&gt;One objective is to make structural and compositional changes to the largest electrical resistance element of the cell, the electrolyte. And the second objective is to expand on development of anode structures and chemistries. A third objective to be addressed is the low catalytic activity of those chemistries resistant to coking. Development involves use of material science, electrochemistry, and materials processing expertise resident at GRC and the ceramic powder processing expertise. The proposed effort will include (1) Develop fabrication methods to decrease electrolyte thickness &amp;gt; 2x, which will reduce cell resistance by at least 2x and decrease localized IR2 heating thus positively impacting anode life; (2) Change electrolyte chemistry to new co-doped Sc2O3 stabilized zirconias (3x increase in oxygen/charge conduction) or to alternative co-doped Yb2O3 stabilized zirconias (2x increase), which will result in a proportionate increase in power; (3) Increase electrode scaffold porosity and shorten its height to increase liquid tin loading, decrease electrical path, and further decrease weight and volume; (4) Explore liquid tin dopants/alloys with potential to improve wetting behavior and increase fuel catalysis without carbon formation. Test impact of a second metal as an under layer immediately adjacent to the electrolyte. Second metal will be selected for its wetting properties.&lt;/p&gt;
&lt;p&gt;Since the majority of the potential ADR targets are large (&amp;gt;meters) upper stages and payloads between 800 and 1100 km altitude, they are relatively bright, with visual magnitudes ranging from 5 to 7. Small telescopes are sufficient to collect their light curve data. However, due to the potential high tumble motion of the targets, a CCD camera with a frame rate up to 30/sec is needed. Identify an existing group with the necessary facility, equipment, experience, and capability for light curve observations of potential ADR targets in the low Earth orbit (LEO) region. Collect light curve data of at least 100 major ADR targets, including SL-8 Cosmos 3M second stages (2.4 m diameter by 6 m length; 1400 kg dry mass) and SL-16 Zenit second stages (4 m diameter by 12 m length; 8900 kg dry mass). Process raw data, obtain light curves, and analyze the data. Outcomes: A 4-month contract with the Air Force Academy was established in 2011. The Air Force Academy used one of their 16&amp;rdquo; telescopes equipped with a fast Andor CCD camera for the observations. A total of 126 targets were observed during the 4-month period (ended in February 2012). About half of the targets had multiple passes. All raw data were processed, and summary spreadsheets for individual targets were prepared and delivered by the Air Force Academy. Two abstracts on the observations and the implications for the tumble motions of the ADR targets for the 2012 International Astronautical Congress were submitted and accepted for presentation.&lt;/p&gt;
&lt;p&gt;The Cryogenic Propellant Storage and Transfer project will demonstrate the capability to safely and efficiently store, transfer and measure cryogenic propellants, including liquefied and super-cooled fuels and oxidizers. These advances will lead to development of next-generation space transportation systems capable of managing large propellant volumes over long time periods necessary for deep space travel.&amp;nbsp; NASA&amp;rsquo;s Human Exploration and Operations Mission Directorate is a primary customer and new opportunities will follow for the agency&amp;rsquo;s industry partners.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;&lt;strong&gt;CPST: Key Mission Facts&lt;/strong&gt;&lt;/p&gt;&lt;p&gt;- The Cryogenic Propellant Storage &amp;amp; Transfer mission will demonstrate technologies required for the development of in-space cryogenic systems to support exploration beyond low-Earth orbit.&lt;br /&gt;- The mission will support multiple human architecture elements&lt;br /&gt;- It is designed to demonstrate long-duration, storage and transfer of cryogenic propellants.&lt;br /&gt;- It will demonstrate an accurate and reliable gauging system for tracking stored propellant.&lt;/p&gt;
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	Build and test a full size (4x2 meter aperture) breadboard antenna for SMLS.&lt;/p&gt;
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		Demonstrate critical azimuth scanning capability of a 4m SMLS antenna and its performance under thermal load environments.&lt;/li&gt;
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&lt;p&gt;The goal of this project was to advance microencapsulation from the standard spherical microcapsule to a non-spherical, high-aspect ratio (HAR), elongated microcapsule. This was to be accomplished by developing reproducible methods of synthesizing or fabricating robust, non-spherical, HAR microcapsules. An additional goal of this project was to develop the techniques to the point where scale-up of these methods could be examined.&amp;nbsp; Additionally, this project investigated ways to apply the microencapsulation techniques developed as part of this project to self-healing formulations.&lt;/p&gt;&lt;p&gt;This project had three primary objectives, all of which have been addressed:&lt;br /&gt;&amp;bull; Assess the state-of-the-art for&amp;nbsp; microcapsules and self-healing systems;&lt;br /&gt;&amp;bull; Evaluate reproducible methods of synthesizing or fabricating robust, nonspherical microcapsules and develop new technology where applicable;&lt;br /&gt;&amp;bull; Evaluate the use of nonspherical&amp;nbsp; microcapsules in self-healing applications such as wire insulation&lt;/p&gt;
&lt;p&gt;The goal of the Protein Colloidal Aggregation project is to understand the underlying&amp;nbsp;cause of several major diseases, including&amp;nbsp;Alzheimer&amp;rsquo;s, Parkinson&amp;rsquo;s, and chronic&amp;nbsp;traumatic encephalopathy. These diseases&amp;nbsp;all occur when protein molecules undergo&amp;nbsp;a peculiar and irreversible process in which&amp;nbsp;they aggregate to form tiny fibers of a unique&amp;nbsp;material called amyloid, which the body&amp;nbsp;cannot remove.&amp;nbsp;Despite enormous investment in research,&amp;nbsp;the fundamental physiochemical mechanism of&amp;nbsp;these diseases remains poorly understood.&amp;nbsp;&lt;/p&gt;&lt;p&gt;Based on initial studies using atomic force microscopy (AFM), we theorized that the aggregation of proteins in these diseases is driven instead by colloidal interactions, the same forces that govern the behavior&amp;nbsp;of nanoscale particles in the colloidal suspensions we encounter every day, such as paint, milk, and clouds.&lt;/p&gt;&lt;p&gt;Our theory is being validated by the evidence. For many years, NASA has been heavily involved in research into the structure of proteins and their assembly into crystals, and in studying the colloidal interactions and aggregation of nanoscale particles. To date, however, NASA&amp;rsquo;s colloid research has involved&amp;nbsp;only nonbiological materials.&amp;nbsp;But now we&amp;nbsp;are bridging these two fields by studying the colloidal aggregation of proteins.&lt;/p&gt;
&lt;p&gt;This study was aimed at the further development of&amp;nbsp;visible light responsive&amp;nbsp;catalysts by investigating new methods. &amp;nbsp;A library of catalysts was developed and screened for gas and aqueous phase applications.&amp;nbsp;This project focused on the development of novel photocatalysts, using multiple preparation methods, to be utilized in air and/or water purification reactors. Developed catalyst samples were tested for both applications and underwent vigorous physical characterization.&lt;/p&gt;&lt;p&gt;Top-performing samples were also compared to commercially available visible light responsive (VLR) catalysts.&amp;nbsp;While photocatalysis is a well-developed technology for both air and water purification, most processes use bare titanium dioxide as the catalyst, which requires UV light for activation. By altering the wavelength of light needed for activation, solar radiation or highly-efficient LEDs can be better utilized while eliminating hazardous Hg-containing fluorescent lamps.&lt;/p&gt;
&lt;p&gt;When the project began, our intention&amp;nbsp;was to develop a more accurate model of&amp;nbsp;the forces that could be obtained between&amp;nbsp;experimentally demonstrate these forces. We&amp;nbsp;chose to operate at a frequency of 2.2 GHz&amp;nbsp;and spent the next six months developing&amp;nbsp;a torsion balance system to monitor the&amp;nbsp;force between a fixed antenna and one that&amp;nbsp;was suspended. In addition, we developed&amp;nbsp;a theoretical model for this force that, by&amp;nbsp;April 2012, led us to conclude that the&amp;nbsp;attractive (or tractor beam) forces that could&amp;nbsp;be achieved in this manner were too small.&amp;nbsp;We had hoped for forces at the micro-Newton&amp;nbsp;level, but were only seeing them at the nano-Newton level, which is insufficient for many&amp;nbsp;applications.&lt;/p&gt;&lt;p&gt;Consequently, we redirected&amp;nbsp;our work to the goal of developing a shortrange&amp;nbsp;tractor force between satellites, with&amp;nbsp;great success. Over the next few months,&amp;nbsp;we showed that, within a distance of&amp;nbsp;roughly 100 m, it was feasible to construct a&amp;nbsp;satellite position and orientation system that&amp;nbsp;would allow a next-generation large space&amp;nbsp;telescope to be built with freely floating&amp;nbsp;mirror elements. We verified our predictions&amp;nbsp;experimentally and showed that not only&amp;nbsp;could the entire telescope be steered to&amp;nbsp;a point anywhere in the sky within a few&amp;nbsp;hours, but each element could be stably held&amp;nbsp;to the optical wavelength criteria necessary&amp;nbsp;for diffraction-limited performance.&lt;/p&gt;
&lt;p&gt;An independent portable equipment platform was designed to house a wide variety of electrical equipment encased into a self-contained portable enclosure unit, which not only provides remote data acquisition and control capability, but was also constructed so that it can be set up and safely used within hydrogen environments. The unit takes advantage of the use of a&amp;nbsp;battery powered system, a&amp;nbsp;cooling cycle&amp;nbsp;and&amp;nbsp;a purging system for electrical equipment deployment. This enables cutting-edge and novel equipment to be rapidly deployed, economically support projects, and&amp;nbsp; improves anomaly investigations in remote locations.&lt;/p&gt;
&lt;p&gt;The objective of this project was to use GPU enabled computing to accelerate the analyses of heat transfer and thermal effects. Graphical processing unit (GPU) computing technology can permit modeling tasks that were in the past, restricted to high-end computational facilities; however, now they can be tangible on lower cost high-end workstations. Therefore, utilizing GPU computing has the potential to reduce modeling time by one to two orders of magnitude compared to central processing unit (CPU) workstations data processing speed that have been historically implemented for use.&lt;/p&gt;
&lt;p&gt;The engineering design group upgraded the liquid nitrogen pump system at the HPGF. The pump system supports the site-wide liquid nitrogen supply and its operation is critical for supporting test activities. The new pumping facility was designed with the capability for adding diagnostic utilities to promote health management of the new cryogenic pump skids. This project provides the health management capability by embedding the AAMU into the system providing real-time diagnostic feedback to operators and scheduling preventive maintenance.&amp;nbsp; To accomplish this, LabView&amp;reg; software interface communicates between the TEAMS Product Suite&amp;rsquo;s remote diagnostic server and the pumping control system to display operational health events and suggested maintenance to the user.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;The Real-Time Emergency Action Coordination Tool (REACT) was developed under contract to NASA and deployed for use by the entire agency. &amp;nbsp;NASA REACT is a web-based system for emergency managers to manage crisis using geospatial mapping, real-time data feeds, standardized forms, and disaster impact models. The system utilizes a secure worldwide map and a reporting engine to report situation status throughout the agency by using detailed data and information about each NASA Center. NASA REACT is also available on mobile smartphones for authorized users to edit and view incident status information anywhere in the agency.&lt;/strong&gt;&lt;/p&gt;&lt;p&gt;&lt;strong&gt;Stennis Space Center&amp;rsquo;s focus on rocket propulsion testing and the desire to leverage the existing REACT infrastructure led to the development of a prototype propulsion test monitoring module for use within the REACT system--information was made available through the Emergency Operations Center using SSC&amp;rsquo;s Institutional GIS. This module provides real-time data from propulsion testing support facilities. For this project, NASA identified as the areas of interest SSC&amp;rsquo;s Gas House Distribution Plant and Gas Pipeline Network. Sensors were installed, tested and monitored to determine the relative health of the systems as it related to moisture, temperature and pressure. &amp;nbsp;&lt;/strong&gt;&lt;/p&gt;
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The overall goal of the Technical Education Satellite (TechEdSat) is to employ a small spacecraft to evaluate, demonstrate, and validate two new technologies for future experiments aboard small space satellites and other small payload systems.  Both technologies were initially developed with NASA?s Innovative Partnerships Programs (IPPs). The first technology is the AAC?s Plug-and-Play power architecture, the goal of which is rapid configuration of nanosatellite avionics components.  The second technology is use of two communications satellite constellations, Iridium and Orbcomm, for two way communication with mission operations on Earth.  To evaluate these technologies, San Jose State University students will develop, build, test, and flight qualify a CubeSat for deployment from the International Space Station.  Qualification and development of the CubeSat will be overseen by assigned NASA Ames Research Center mentors from the Office of the Chief Technologist.  The satellite will be launched from International Space Station (ISS) on August 26th, 2012.   It will be inserted into an orbit at 413.2 km apogee and 381.3 km perigee, on an inclination from the equator of 51.60 degrees.  Amateur band beacon transmission will begin forty minutes after launch from ISS.  The experiment will complete and all communications will be shut down 10 days after launch from ISS.  The downward and retrograde release vector will slow the satellite and reduce the altitude of the orbit, until de-orbiting occurs 105 days after launch.  The spacecraft is a single CubeSat unit 10 cm X 10 cm X 10 cm.  The total mass is about 1.33 kg.
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;Small, light-weight and low-cost missions will become increasingly important to NASA&amp;#39;s exploration goals for our solar system. Ideally teams of dozens or even hundreds of small, collapsable robots, weighing only a few kilograms a piece, will be conveniently packed during launch and would reliably separate and unpack at their destination. Such teams will allow rapid, reliable in-situ exploration of hazardous destination such as Titan, where imprecise terrain knowledge and unstable precipitation cycles make single-robot exploration problematic. Unfortunately landing many lightweight conventional robots is difficult with conventional technology. Current robot designs are delicate, requiring combinations of devices such as parachutes, retrorockets and impact balloons to minimize impact forces and to place a robot in a proper orientation. Instead we propose to develop a radically different robot based on a &amp;quot;tensegrity&amp;quot; built purely upon tensile and compression elements. These robots can be light-weight, absorb strong impacts, are redundant against single-point failures, can recover from different landing orientations and are easy to collapse and uncollapse. We believe tensegrity robot technology can play a critical role in future planetary exploration.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;A spacecraft carrying a number of Regolith Biters (RBs) would travel to the vicinity of a small body. From a favorable vantage point, and while remaining within a safe distance in a non-colliding trajectory, it would release the RBs towards the target body. Upon encountering the body, they would bite the regolith (thus retaining a sample), and eject back to orbit. The spacecraft, being endowed with appropriate navigation and tracking capabilities, would rendezvous with and collect those RBs within its reach, and bring them back to Earth. Separating the navigation and sampling concerns removes the need for proximity operations with the small body--the stage in current architectures that carries the most challenges and risks. Eliminating the need for proximity operations brings back to the discussion the exploration of exciting prospects, like highly active comets, fast-rotating bodies, and binary systems. Distributing the sampling problem among a collective of agents provides the opportunity to sample multiple regions in a single mission. It also provides robustness to various environmental conditions, and may enable the distributed, in situ characterization of the body. In the search for reliability, current architectures rely on complexity: an elaborate system should succeed at once. We rely on numbers: a given agent may fail at any stage, but success is attained by the collective.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;The objectives of the Robotic Asteroid Prospector (RAP) project are to examine and evaluate the feasibility of asteroid mining in terms of means, methods, and systems. This study decomposes the challenge of asteroid mining into four key efforts: Mission design, including trajectory and logistics from an Earth-Moon Lagrange Point (EMLP) to the asteroid and return to that EMLP, Spacecraft design including propulsion and Mission operations, Mining technology for microgravity and vacuum operations, and How these efforts can add up to a business case for asteroid mining.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;HOMES (Holographic Optical Method for Exoplanet Spectroscopy) is a space telescope designed for exoplanet discovery. Its double dispersion architecture employs a holographic optical element as a primary objective in conjunction with a novel secondary spectral interferometer. Unlike mirrors and lenses, the holograms are thin and flat. They can be fabricated on thin gossamer membranes and stretched over space frames covering thousands of square meters. This provides the scale of collector needed to capture the photons from very faint sources like exoplanets and bring them to a focus. Because holographic optics focus by the process of dispersion, they are intrinsically spectrographic providing a wealth of detail about the composition of the images they form. Add to this a novel notch filter to dim the star that takes advantage of the spectrographic image, and HOMES is a concept that addresses the demanding specifications of a telescope to find habitable planets within 30 light years of earth.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;WATER WALLS (WW) takes an approach to providing a life support system that is biologically and chemically passive, using mechanical systems only for plumbing to pump fluids such as gray water from the source to the point of processing. The core processing technology of Water Walls is FORWARD OSMOSIS (FO). Each cell of the WW system consists of a polyethylene bag or tank with one or more FO membranes to provide the chemical processing of waste. WW provides four principal functions of processing cells in four different types plus the common function of radiation shielding: &amp;nbsp;1. Gray water processing for urine and wash water, 2. Black water processing for solid waste, 3. Air processing for CO&lt;/span&gt;&lt;sub style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;2&lt;/sub&gt;&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt; removal and O&lt;/span&gt;&lt;sub style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;2&lt;/sub&gt;&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt; revitalization, 4. Food growth using green algae, and 5. Radiation protection to the crew habitat (all cells).&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;The purpose of this proposed research is to develop a new air purification system based on a liquid membrane, capable of purifying carbon dioxide from air in a far more compact and energy efficient system than what is currently possible. The approach relies on recent advances in supported liquid membranes, which allow us to make mechanically stable, ultra-thin supported liquids that have permeability and selectivity for carbon dioxide over one order of magnitude greater than existing approaches. Most critically, because these membranes use a liquid as an active material, it is possible to electrochemically pump the carbon dioxide, making it viable to build an air purification system that uses no mechanical components such as compressors. Such an innovation will dramatically improve NASA&amp;#39;s capabilities to sustain manned spacecraft, including missions to Mars or other long-term space habitation.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;To enable frequent, low-cost opportunities to deliver nanosatellites to destinations beyond Earth orbit, TUI proposes to develop the &amp;ldquo;Nanosatellite Tethered High-Orbit Release&amp;rdquo; (NanoTHOR) module. The NanoTHOR module will enable multiple nanosatellites carried as secondary payloads on upper stages launched into GTO to be injected into Earth-escape trajectories by scavenging orbital momentum and propellant from the upper stage. The NanoTHOR module will utilize a lightweight, re-usable tether to transfer momentum from the rocket stage to the nanosatellite. The use of a rotating tether &amp;ldquo;multiplies&amp;rdquo; the rocket&amp;rsquo;s delta-V by the mass ratio of the stage to the nanosat, enabling it to provide both very-high specific impulse propulsion competitive with the best EP thrusters AND short transfer times competitive with chemical rockets. The tether also enables the stage&amp;rsquo;s orbital momentum to be converted to tether rotational momentum to increase the nanosat toss velocity. After completing its mission, the tether can be de-orbited within one orbit period to eliminate collision or debris risks. The nanoTHOR module will provide a low-cost, low-mass means to enable nanosatellites to be launched as ride-share payloads on GEO satellite missions and then delivered to deep-space trajectories. It will therefore enable NASA to affordably launch flotillas of low-cost nanosatellites into heliocentric orbits to conduct searches for NEOs, to study potential targets for manned exploration of asteroids, to provide &amp;lsquo;nowcasting&amp;rsquo; of solar weather conditions, and to serve as communications relays for manned and unmanned missions beyond Earth orbit.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;This project develops a process for automated on-orbit construction of very large structures and multifunctional components. The foundation of this process is a novel additive manufacturing technique called &amp;lsquo;SpiderFab&amp;rsquo;, which combines the techniques of fused deposition modeling (FDM) with methods derived from automated composite layup to enable rapid construction of very large, very high-strength-per-mass, lattice-like structures combining both compressive and tensile elements.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;The Plasma Magnetoshell is based on demonstrated experimental results and the successful implementation would dramatically decrease mission risk, launch cost, mass, and overall radiation exposure. The Plasma Magnetoshell is a high-Beta (the ratio of plasma to magnetic field energy density) dipole plasma configuration which would initially be populated with ambient atmospheric gases. This plasma is formed, sustained, and expanded with an electrodeless Rotating Magnetic Field (RMF), which has been shown in previous experiments to generate the required, fully ionized, high temperature magnetized plasma. RMF plasma formation induces large currents in the plasma that inflate and maintain the large-scale magnetic structure. The primary drag-inducing interaction between the magnetically confined plasma ions and the incoming neutral atmospheric particles is that of charge exchange, which has the largest cross section. After a charge exchange, the now magnetized atmospheric ion reacts its directional momentum (in the frame of the spacecraft) onto the magnet via field line bending and stretching.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;The surface of Venus is the most hostile environment in the solar system, with a surface temperature hotter than an oven, and a high-pressure, corrosive atmosphere. It is significant that, although humans have sent rovers to Mars with operating lifetimes of eight years and counting, the most capable mission to the surface of Venus has been a stationary lander that survived for only two hours. Exploring the surface of Venus with a rover would be a &amp;ldquo;stretch&amp;rdquo; goal, which will push the limits of technology in high-temperature electronics, robotics, and robust systems. &amp;nbsp; In work to develop sensors to work inside of jet engines, NASA Glenn has developed electronics that will continue to function even at the Venus temperature of 450&amp;deg;C. These electronic components represent a breakthrough in technological capability for high temperatures. We have also tested solar cells up to Venus surface temperatures; although the power density produced is low (because of the high cloud levels and thick atmosphere), we can produce electrical power on the surface. So the fundamental elements of a rover for Venus are not beyond the bounds of physics: we could survive the furnace of Venus-- if we can come up with an innovative concept for a rover that can move on extremely low power levels.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;We propose a new mission concept, called MAGNETOUR, that enables a spacecraft to orbit and travel between multiple moons of an outer planet, using very little or even no propellant. To achieve this free-lunch &amp;lsquo;Grand Tour&amp;rsquo;, we e&lt;/span&gt;xploit the unexplored combination of magnetic and multi-body gravitational fields of planetary systems. This concept involves combining two main innovations:&lt;/p&gt;
&lt;ol&gt;
	&lt;li&gt;
		Design of a very low delta-v tour of planetary moons by considering the intrinsic multi-body gravitational dynamics of planetary systems, and&lt;/li&gt;
	&lt;li&gt;
		Use of the electromagnetic Lorentz force as a revolutionary means for performing the required low delta-v maneuvers of our low-energy tour.&lt;/li&gt;
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	&amp;nbsp;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;The Voyager Spacecraft have reached the Heliopause and greatly improved our understanding of the region. This journey took 35 years. A fuller understanding of the Heliopause would require in-situ measurements at various points in the Heliopause, which is impractical for current propulsion methods and mission timelines. Further, the solar system plane is inclined above the galactic plane by ~60&amp;deg;, doubling the science targets (six cardinal directions in both reference frames.) A total of 10-12 probes will be needed to explore the heliopause along both frames of reference and truly understand the 3d structure of the region. We will design a mission architecture that makes this scenario realistic from both a cruise time and mission cost perspective by using solar sail-enabled trajectories and designing a probe that can be manufactured by industry.&lt;/span&gt;&lt;/p&gt;
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	This NASA Innovative Research Grant activity conducts engineering analysis to demonstrate the feasibility and advantages of applyi?ng a breakthrough remote sensor calibration concept to a wide range of future NASA remote sensor science missions, e.g., PACE, GEO-CAPE, CLARREO, HySpIRI, GACM and Heliophysics research.&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;Our objective is to investigate the conditions to manipulate and maintain the shape of an orbiting cloud of dust-like matter so that it can function as an ultra-lightweight surface with useful and adaptable electromagnetic characteristics, for instance, in the optical, RF, or microwave bands.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;Atom interferometers are more sensitive to inertial effects. This is because atoms in their inertial frame are ideal test masses for detection of gravity effects and gravity Waves. The internal and external degrees of freedom of atoms are used to amplify the gravity wave phase.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;Since the Apollo era, sample return missions have been primarily limited to asteroid sampling. More comprehensive sampling could yield critical information on the formation of the solar system and the potential of life beyond Earth. Hard landings at hypervelocity (1-2 km/s) would enable sampling to several feet below the surface penetration while minimizing the Delta V and mass requirements.&amp;nbsp; Combined with tether technology a host of potential targets becomes viable. The proposed work seeks to design, develop and test a hard impact penetrator/sampler that can withstand the hard impact and enable the sample to be returned to orbit. Tether technology for release of the penetrator and capture of the sample eliminate many of the restrictions that presently inhibit the development of sample return missions. The work builds upon in hypervelocity laboratory testing that use 1&amp;rdquo; Al projectiles that investigate crater formation and penetration through hard surfaces. The proposed work will enable realistic size (6&amp;quot; diameter) projectiles to be studied by taking advantage of the development of cheap high power commercial rocket motors that will enable impacts up to Mach 2 for Phase I. With this data, methodologies for studying higher velocity impacts can be developed along with mission scenarios to test the viability of mission return samples in the near future. Successful development of sample return capabilities will provide a major impetus for solar system exploration.&lt;/span&gt;&lt;/p&gt;
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	&lt;span style="font-family: &amp;quot;Lucida Grande&amp;quot;;"&gt;We propose a Phase I study for a novel concept of a supersonic bi-directional (SBiDir) flying wing (FW) that has the potential to revolutionize supersonic flight with virtually zero sonic boom and ultra-high aerodynamic efficiency. The SBiDir-FW planform is symmetric about both the longitudinal and span axes. For supersonic flight, the planform can have as low aspect ratio and as high sweep angle as desired to minimize wave drag and sonic boom. For subsonic mode, the airplane will rotate 90deg in flight to achieve superior stable aerodynamic performance. The conflict of subsonic and supersonic aerodynamic performance of conventional fuselage-wing configuration is hence removed. The preliminary CFD simulation for a SBiDir-FW business jet (BJ) at Mach numbers of 1.6 and 2.0 indicates that the configuration generates no N-wave sonic boom on the ground at a high lift to pressure drag ratio L/Dp of 16. The superior supersonic aerodynamic performance is benefited from the sharp nose and ultra-slender body with a low aspect ratio of 0.33, which translates to a very high subsonic aspect ratio of 33 for high subsonic performance. This proposal has three objectives: 1) design refinement of a supersonic SBiDir-FW BJ configuration using CFD; 2) mission analysis assisted with CFD simulation for the supersonic SBiDir-FW BJ to study the feasibility; and 3) wind tunnel testing of the SbiDir-FW BJ to verify its supersonic aerodynamic performance and sonic boom signature. The research team is highly qualified to perform the proposed tasks.&lt;/span&gt;&lt;/p&gt;
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&lt;p&gt;The &amp;ldquo;Variable Vector Countermeasure Suit (V2Suit) for Space Habitation and Exploration&amp;rdquo; is a visionary system concept that will revolutionize space missions by providing a platform for integrating sensors and actuators with daily astronaut intravehicular activities, and testing the interactions between countermeasures to improve human health and adaptation countermeasures. The V2Suit uses control moment gyroscopes within a miniaturized module placed on the major segments of the body to provide a &amp;ldquo;viscous resistance&amp;rdquo; during movements &amp;ndash; a countermeasure to the sensorimotor and musculoskeletal adaptation performance decrements that manifest themselves while living and working in microgravity, and during gravitational transitions during long-duration spaceflight, including post-flight recovery and rehabilitation. Effective countermeasures to this de-conditioning and the unique sensorimotor characteristics associated with living and working in 0-G are critical for future space missions. This proposed project is a follow-on to the current NIAC Phase I V2Suit, which is exploring the concept and maturing the technology through proof-of-concept simulation and limited hardware-in-the-loop testing. A technology readiness level of 2 is expected at the end of Phase I, and through further Phase II study and brassboard unit development the technology readiness level is estimated to be an early 4. This proposed Phase II project has four integrated aims for further development of the concept studied in the Phase I award, assessing the V2Suit in a mission context, and assessing the programmatic benefits &amp;ndash; all contributing to a technology development roadmap for operational demonstration. (This is a project within the NASA Innovative Advanced Concepts, NIAC, program.)&lt;/p&gt;
&lt;p&gt;Automated building technologies will revolutionize the way structures are built on Earth, in dense urban environments, in difficult-to-build and difficult-to-service sites, or in remote and hostile regions of the globe. The technologies under development by our group have the potential to simplify construction logistics, reduce the need for hard physical labor by assigning humans to a strictly supervisory role, eliminate issues relating to human safety and produce intricate, aesthetically refined designs and structures at significantly reduced construction cost. Space architecture in general and Lunar and Martian structures in particular will also provide a rich new aesthetic vocabulary for architects to employ in the design and creation of buildings that employ high technology and building information modeling that is vital for optimizing use of materials and energy that is critical to building economics.&lt;/p&gt;
&lt;p&gt;This technique uses the magnetic fields from current passing through coils of high-temperature superconductors (HTSs) to support spacecraft structures and deploy them to operational configurations from their positions as stowed inside a launch vehicle fairing. The chief limiting factor in spacecraft design today is the prohibitively large launch cost per unit mass. Therefore, the reduction of spacecraft mass has been a primary design driver for the last several decades. The traditional approach to the reduction of spacecraft mass is the optimization of actuators and structures to use the minimum material required for support, deployment, and interconnection. Isogrid panels, aluminum or composites, and gas-filled inflatable beams all reduce the mass of material necessary to build a truss or otherwise apply surface forces to a spacecraft structure. We instead look at using electromagnetic body forces generated by HTSs to reduce the need for material, load bearing support, and standoffs on spacecraft by maintaining spacing, stability, and position of elements with respect to one another.&lt;/p&gt;
&lt;p&gt;Photons weigh nothing. Why must even small space telescopes have high mass? Our team has demonstrated this is not the case using a completely novel approach to producing and correcting active optical primary mirrors to be used specifically for NASA&amp;rsquo;s future large space telescope missions. Unprecedented advances in nano-engineered meta-materials have produced a laser actuated liquid crystal elastomer (LCE) polymer substrate with controllable reversible bi-directional bending. Using our novel optically controlled molecular actuators allows substitution of optically induced control for rigidity and mass.&lt;/p&gt;
&lt;p&gt;Atmospheric confetti. Inchworm crawlers. Blankets of ground penetrating radar. These are some of the unique mission concepts which are enabled by a printable spacecraft. Flexible printed electronics is a wide-ranging technology that can enhance or even enable many engineering applications. Our concept is to utilize the commercial technology of printed electronics to design and fabricate an entire end to end functional spacecraft. The novel advancement (and therefore the technical challenge) of the concept is to apply printed electronics in a multi-functional platform by implementing every subsystem that a spacecraft might need from the scientific sensor through the data downlink and have it survive and function in a space environment. These requirements push the current state of the art for functionality as well as introduce design and manufacturing compatibility challenges among the functional subsystems. Current industry growth and commercial investment is expected to advance the functionality of available basic building blocks and components synergistically with NASA&amp;rsquo;s needs.&lt;/p&gt;
&lt;p&gt;Current nuclear fusion efforts have focused on the generation of electric grid power and are wholly inappropriate for space transportation as the application of a reactor based fusion-electric system creates a colossal mass and heat rejection problem for space application. The Fusion Driven rocket (FDR) represents a revolutionary approach to fusion propulsion where the power source releases its energy directly into the propellant, not requiring conversion to electricity. It employs a solid lithium propellant that requires no significant tankage mass. The propellant is rapidly heated and accelerated to high exhaust velocity (&amp;gt; 30 km/s), while having no significant physical interaction with the spacecraft thereby avoiding damage to the rocket and limiting both the thermal heat load and radiator mass.&lt;/p&gt;
&lt;p&gt;The NIAC research effort entitled &amp;ldquo;The Ghost Imaging of Space Objects&amp;rdquo; has been inspired by the original 1995 Ghost Imaging and Ghost Diffraction experiments that harnessed quantum-correlated photons to recover an object&amp;rsquo;s image from a measurement lacking spatial resolution, but utilizing an empty reference channel. Various applications of this phenomenon have been soon proposed, ranging from the optical imaging exceeding the classical resolution limit (Rayleigh limit), to the ultimately secure quantum communications and super-dense signal encoding. It was also realized, around 2004-5, that not only quantum-correlated but even a common thermal source of light can be used for the Ghost Imaging, although at a cost of a reduced contrast. Since then, the possibility of ghost-imaging of space objects has been intriguing many physicists. Unfortunately, the need for an optical beam splitter to be placed between the thermal light source (e.g., a star), the object and the observer severely diminished the practical value of this idea.&lt;/p&gt;
&lt;p&gt;A Hypervelocity Asteroid Intercept Vehicle (HAIV) mission architecture, which blends a hypervelocity kinetic impactor with a subsurface nuclear explosion for optimal fragmentation and dispersion of hazardous near-Earth objects (NEOs), has been developed through a 2011 NIAC Phase I study. Despite the uncertainties inherent to the nuclear disruption approach, disruption can become an effective strategy if most fragments disperse at speeds in excess of the escape velocity of an asteroid so that a very small number of fragments impacts the Earth. Thus, the proposed HAIV system will become essential for reliably mitigating the most probable impact threat: NEOs with warning times shorter than 10 years. It offers a potential breakthrough or great leap in mission capabilities for mitigating the impact threat of NEOs. The proposed Phase II study further develops the HAIV-based mission architecture and explores its potential infusion options within NASA and beyond.&lt;/p&gt;
Multi-Modal Neurodiagnostic Tool for Exploration Missions (A} Project
A Multi-Depth Underwater Spectroradiometer for Validation of Remotely-Sensed Ocean Color and Estimation of Seawater Biogeochemical Properties (A) Project
Extreme Environment Hybrid Gearbox Technology (A) Project
New Wireless Sensors for Diagnostics Under Harsh Environments (A) Project
Intelliface - Intelligent Assistant for Interfacing Diagnosis and Planning Systems Project
Advanced Supported Liquid Membranes for CO2 Control in EVA Applications Project
Fiber Optic Temperature Sensors for Thermal Protection Systems Project
Real-Time Smart Tools for Processing Spectroscopy Data Project
Data Concentrator for Modular and Distributed Control of Propulsion Systems (A) Project
Radiation-Hardened HDTV Sensors (A) Project
Multi-Specimen Variable-G Facility for Life and Microgravity Sciences Research Project
&lt;p&gt;A review of mobile applications (apps) and portable electronic tools/mobile platforms (that could be used by propulsion testing field users at SSC) was conducted. Additionally, a preliminary prototype mobile application (app) was also initiated. In the rocket engine test environment, Test Preparation Sheets (TPS) are used to ensure safety compliance is maintained, and they serve as advisors to test directors and project engineers on all safety matters. This mobile app would enable the ability of TPS to be downloaded to a mobile platform in the field (i.e. at a test complex).&amp;nbsp; Having this ability, would modernize monitoring tasks, expedite data processing, and provide real-time data input.&lt;/p&gt;
&lt;p&gt;The project will devise test and development approaches to support development of large scale composite payload fairing structures, including conducting tests and analyzes of structures that are representative of a 10 m diatmeter composite payload fairing for a 100 to 130 mt Space Launch System (SLS).&amp;nbsp; The project will develop test procedures for large composite sturctures testing and fabricate a 1/6th-arc panel for a 10 m diameter composite fairing to demonstrate full-scale materials and manufacturing technologies for&amp;nbsp; composite payload fairing structures.&lt;/p&gt;
&lt;p&gt;The purpose of this project is to develop state-of-the-art, green precision cleaning technologies for NASA&amp;rsquo;s 21&lt;sup&gt;st&lt;/sup&gt; Century Launch Complex thus eliminating long-term environmental costs to the Program.&amp;nbsp; Precision cleaning is of critical importance in the aerospace industry.&amp;nbsp; Failure to clean to specified levels may result in problems ranging from impaired performance to catastrophic failure.&amp;nbsp;&lt;/p&gt;&lt;p&gt;Of particular concern is the cleaning of systems containing strong oxidizers such as liquid oxygen (LOX) or hypergolic fuels.&amp;nbsp; Currently, precision cleaning at Kennedy Space Center is performed using dual-solvent process in which the first solvent, Vertrel MCA, is used to clean the component and a second solvent, HFE-7100, is used as a final rinse and analytical test fluid.&amp;nbsp; Highly fluorinated compounds such as those used in Vertrel MCA are extremely persistent in the environment and are potent greenhouse gases. Continued use of this or similar solvents will lead to high remediation costs that must be carried by the Program for years to come.&lt;/p&gt;&lt;p&gt;Historically, precision cleaning has used chlorofluorocarbons (CFCs), such as Freon, because it was non-toxic and performed extremely wll.&amp;nbsp; When Freon, and other CFCs, were banned due to their harmful environmental effects, new solvents were identified that were similar compounds but were not yet regulated.&amp;nbsp; Eventually, these solvents also become regulated and unavailable for use.&amp;nbsp; This project specifically did not consider halogenated solvents in order to find solvents or technologies that would not face future environmental regulations.&lt;/p&gt;
&lt;p&gt;This project will develop the capability to identify anomalous conditions (indications to potential impending system failure) in ground system operations before such failures occur. These indicators are not presently detectable by traditional command and control and fault detection systems. &amp;nbsp;This project enables the delivery of system&amp;#39;s health advisories to ground system operators so they can take action prior to experiencing systems failures.&amp;nbsp;Inductive Monitoring System (IMS)&amp;nbsp;detected&amp;nbsp;anomalies can be sent to a diagnostic software&amp;nbsp;module for diagnosis.&lt;/p&gt;&lt;p&gt;Anomaly Detection provides the 21st Century Launch Complex Program with the ability to identify/recognize systems&amp;#39; anomalies before they become faults in the system; it supports the resolution of such anomalies to assure system availability and mission success. This capability also allows reduction in systems&amp;#39; maintenance costs by dictating when maintenance is needed (Maintenance-on-Demand) versus performing maintenance on schedule.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Corrosion is an extensive problem that impacts National Aeronautics and Space Administration (NASA) and&amp;nbsp;Department of Defense (DoD).&amp;nbsp; The deleterious effects of corrosion result in steep costs, asset down-time affecting mission readiness, and safety risks to personnel.&amp;nbsp; Consequently, it is vital to reduce corrosion costs and risks in a sustainable manner.&lt;/p&gt;&lt;p&gt;NASA and DoD&amp;nbsp;have numerous structures and equipment that are fabricated from stainless steel.&amp;nbsp; The standard practice for protection of stainless steel is a process called passivation which removes free iron contamination from the surface and forms a&amp;nbsp;metal oxide layer to prevent corrosion.&amp;nbsp; Typical passivation procedures call for the use of nitric acid which exhibits excellent corrosion performance; however, there are a number of environmental, worker safety, and operational issues associated with its use.&lt;/p&gt;&lt;p&gt;The longtime military specification (QQ-P-35C) for the passivation of stainless steel was cancelled in favor of newer specifications which allow for the use of citric acid in place of nitric acid.&amp;nbsp; Citric acid offers a variety of benefits that include increased safety for personnel, reduced environmental impact, and reduced operational cost.&amp;nbsp; There have been few studies, however, to determine whether citric acid is an acceptable alternative for NASA and DoD applications; therefore, NASA and DoD&amp;nbsp;agreed to collaborate on an effort to validate citric acid as an acceptable passivating agent for stainless steel.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The Synchronized Position, Hold, Engage, Reorient, Experimental Satellites &amp;ndash; VERTIGO (SPHERES-VERTIGO)&amp;nbsp;developed by the Massachusetts Institute of Technology (MIT)&amp;mdash;are free-floating, soccer-ball-sized robots with their own propulsion and power. They are used aboard the ISS to study formation flight and other control system algorithms.&amp;nbsp;For this experiment, these same SPHERES will be programmed with thruster firings that will emulate common maneuvers carried out by launch vehicles and spacecraft. This motion will impart energy to the fluid inside the experiment, which will measure its effects.&amp;nbsp;&lt;/p&gt;&lt;p&gt;The ISS provides the perfect environment to conduct liquid behavior studies in microgravity. This investigation is planned to collect valuable data on how liquids move around inside of a container when external forces are applied to that container &amp;ndash; this simulates how rocket fuels move around inside their tanks when motor thrusts are used to push the rocket through space.&amp;nbsp;The slosh experiment takes advantage of hardware already on the ISS.&lt;/p&gt;&lt;p&gt;The primary slosh experiment component is a clear, pill-shaped Lexan tank in the middle of the assembly. This tank is shrouded by a tan box designed to prevent the ISS ambient lights from interfering with the cameras. Also in the middle, is the center hub made of aluminum. This center hub has two arms to hold two high-resolution cameras. These cameras will collect&amp;nbsp;video of the fluid inside the tank. The center hub assembly is connected to a larger frame, which connects to the two SPHERES units through a clamp system. VERTIGO computers attached to the SPHERES units will collect the data from the cameras and the onboard inertial measurement units.&amp;nbsp;These computers are already on the ISS and will be used by the slosh experiment as storage and power for the cameras and accelerometers.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;This project will explore a recent advancement in Phase Change Permeation&amp;trade; technology to enable improved (1) water recovery from urine/brine for Environmental Control and Life Support Systems, and (2) water delivery to plants for potential use in microgravity. The innovation is the use of a phase change permeation membrane to passively and selectively mobilize water in microgravity.&lt;br /&gt;&lt;br /&gt;Test objectives for water purification will determine the effects of temperature and waste water chemical composition on the water flux rate across the membrane and the chemical and microbiological water quality of permeate and effluent streams.&amp;nbsp;Test objectives for water delivery to plants will determine the soil wetting characteristics of the Dutyion&amp;trade; membrane material in normal gravity in preparation for future proposed flight testing.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;This project seeks to develop a sensor to measure blowing soil during a lunar landing and also provide a low-mass, low-cost, low-complexity alternative for detecting valuable mineral deposits. We plan to demonstrate feasibility of the simplest, lowest-mass method of measuring density of a cloud of lunar soil ejected by rocket exhaust and using new math techniques with a small baseline laser/camera system.&amp;nbsp;The focus is on exploring the erosion process that occurs when the exhaust plume of a lunar rocket impacts the regolith.&lt;/p&gt;&lt;p&gt;Also, predicting the behavior of the lunar soil that would be blasted from a lunar landing/launch site shall assist in better design and protection of any future lunar settlement from scouring of structures and equipment. NASA is gathering experimental data to improve soil erosion models and understand how lunar particles enter the plume flow.&lt;/p&gt;
&lt;p&gt;Corrosion is a serious problem that has enormous costs for the nation (4.2&#37; GDP in 2007) and worldwide. Kennedy Space Center is located in one of the most naturally corrosive areas in the world. Acidic exhaust from the solid rocket boosters aggravates these natural conditions. New space vehicles are likely to use the same solid rocket fuel used to launch the Space Shuttle. Launching facilities and ground support equipment will continue to need corrosion protection.&lt;/p&gt;&lt;p&gt;Current research is focused on&amp;nbsp;encapsulating environmentally friendly&amp;nbsp;corrosion inhibitors and incorporating them&amp;nbsp;into commercially available coatings to test&amp;nbsp;their effectiveness. Accelerated corrosion&amp;nbsp;tests have shown that corrosion-activated release&amp;nbsp;microcapsules and particles can&amp;nbsp;be used as inhibitor delivery systems to&amp;nbsp;improve the corrosion protection of several&amp;nbsp;commercially available coatings. This work is&amp;nbsp;being conducted in collaboration with several&amp;nbsp;industry partners who are interested in the&amp;nbsp;NASA-developed smart coating technology.&lt;/p&gt;
&lt;p&gt;The objective is to design, build and functionally test a miniature release mechanism for CubeSats and other small satellites. The WFF 6U satellite structure will be used as the baseline design reference. Design goals for the unit include:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Low cost&lt;/li&gt;&lt;li&gt;Non-explosive, low release energy&lt;/li&gt;&lt;li&gt;Packaging height target of 0.25 inches or less&lt;/li&gt;&lt;li&gt;Two fault tolerance initiation&lt;/li&gt;&lt;li&gt;Resettable and usable for at least 10 cycles&lt;/li&gt;&lt;li&gt;Low power&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;The WFF 6U deployer will be improved in 11 key areas:&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;1. Mass &amp;amp; Joint Reduction&lt;/p&gt;&lt;p&gt;2. Two Stage Release&lt;/p&gt;&lt;p&gt;3. Door Orientation&lt;/p&gt;&lt;p&gt;4. Satellite Preload System Improvement&lt;/p&gt;&lt;p&gt;5. Sounding Rocket Fitment&lt;/p&gt;&lt;p&gt;6. Quick Disconnect&lt;/p&gt;&lt;p&gt;7. Launch Vehicle Interface Update&lt;/p&gt;&lt;p&gt;8. Deployment Verification System&lt;/p&gt;&lt;p&gt;9. Shear Pin Preload System Improvement&lt;/p&gt;&lt;p&gt;10. Deployment Spring Interface&lt;/p&gt;&lt;p&gt;11. Nitrogen Purge System&lt;/p&gt;&lt;p&gt;Once the improvements have been incorporated into the design, detailed structural analysis will be completed to ensure survival under predicted environmental loading conditions.&amp;nbsp; A qualification unit of the improved design will be manufactured and undergo functional, vibration, and thermal testing.&lt;/p&gt;
&lt;p&gt;There are two parts to this project: technology development and technology demonstration and infusion into programs. The development of the DTN services is funded and managed by Space Communications and Navigation (SCaN). The demonstrations and infusion into Humans Space Flight programs is managed by Advanced Exploration Systems (AES).&lt;/p&gt;&lt;p&gt;Currently, protocols to move data have been developed and demonstrated in the lab. These are being infused into operational systems, starting with the International Space Station.&lt;/p&gt;&lt;p&gt;The future development services are: security, network management, routing, quality of service, key management, and deployment services (e.g., timing). As these are developed by SCaN, they will be demonstrated by AES and moved into HEOMD programs. In addition, there are international agreements to use DTN; AES will manage the US part of international Human Space Flight tests and usage.&lt;/p&gt;
&lt;p&gt;This effort leverages ESTO and SBIR investments aimed at enabling &lt;em&gt;fully polarimetric digital beamforming multimode&lt;/em&gt; radar, &lt;em&gt;high resolution&lt;/em&gt; (wideband) measurements, and &lt;em&gt;advanced digital radar waveform synthesis and processing&lt;/em&gt;. The effort will build upon the technology path set out by the Digital Beamforming Synthetic Aperture Radar (DBSAR) and leverage three new developments to implement the most advanced polarimetric Digital Beamforming L-Band radar architecture for airborne applications.&lt;/p&gt;
&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;New thin film low friction coating technologies have recently been developed and matured to the point for use in this IRAD actuator work.&lt;/p&gt;&lt;p&gt;The new novel materials have exceptionally strong hardness and low coefficient of friction properties. The coatings&amp;nbsp;have been&amp;nbsp;applied to the actuator drive components.&lt;/p&gt;&lt;p&gt;The next step in this project is the analysis of the performance and life tested for potential future space flight application, which&amp;nbsp;is underway.&lt;/p&gt;
&lt;p&gt;This novel molecular adsorber coating would alleviate the size, weight, and complexity issues of traditional molecular adsorber puck.&amp;nbsp; A flexible tape version is being developed.&amp;nbsp; The white formulation of the molecular adsorber coating has been qualified to TRL 6 for possible flight project infusion.&lt;/p&gt;
&lt;p&gt;Our objective is to apply CVD and non-CVD carbon nanotubes to complex shapes that numerous scientists have requested for stray light control.&amp;nbsp; Currently, CVD nanotubes can only be grown on flat surfaces due to limitations in line-of-sight physical vapor deposition techniques such as e-beam evaporation. &amp;nbsp;&amp;nbsp;For CVD our adhesion and catalyst layers must be applied on the on the component with extreme uniformity to a thickness of 1 to 2 nm for ideal performance.&amp;nbsp;&amp;nbsp; Then the component must be placed in the thermal reactor furnace flow in a way that allows uniform exposure to the carbon bearing gas. &amp;nbsp;Our first focus area is to utilize atomic layer deposition (ALD) to apply our adhesion and catalyst layers conforming to the desired substrate surface.&amp;nbsp; This will allow fabrication of components that are dark on all surfaces instead of just on one surface.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;&lt;em&gt;Our first objective is that of nanostructured devices for advanced light detection.&lt;/em&gt;&lt;/strong&gt;&amp;nbsp; Our periodic structures exhibit absorptive (nano-antenna) and reflective (magnetic mirror) resonances across the visible to near infrared wavelength range.&amp;nbsp; Fabrication of these &amp;ldquo;nano-antennae&amp;rdquo; can be utilized for enhanced detection and imaging of light and the toolbox of design and fabrication tools we have developed will be applied to making proof of concept devices.&amp;nbsp; Our goal will be to build a superconducting single photon counting detector.&amp;nbsp; While superconducting nano wire single photon counting detectors have been built before, ours will be designed to do integral spectroscopy&lt;/p&gt;&lt;p&gt;&lt;strong&gt;&lt;em&gt;In our second objective; metamaterials for advanced imaging&lt;/em&gt;&lt;/strong&gt;, we are in the process of completing an impedance matched and nanowire edged absorber devices for diffraction suppression.&amp;nbsp; We will refine our designs based on observed performance of these types of devices with the goal of performing suppressing higher orders of the Airy pattern by apodizing the edge of our test optic.&amp;nbsp; To reiterate, essentially the same periodic metallic nanowire pattern as designed and fabricated for our detector use can selectively absorb light at the edge of our device to prevent the high order &amp;ldquo;ringing&amp;rdquo; observed in the Airy pattern.&lt;/p&gt;
&lt;p&gt;This IRAD proposes to evaluate how stress polishing can be used to extend the application of super-polishing to fast aspheres and freeforms, removing sub-aperture MSF errors, such as tool marks, from diamond-turned aluminum optics.&amp;nbsp; It will leverage an old technique for manufacturing aspheres&amp;mdash;stress polishing with a large tool. The aspheric surface will be generated using small tool manufacturing techniques. After the asphere is generated, a mechanical load will be placed onto the optic to deform the asphere into a sphere, using an interferometer to fine tune the deformation.&amp;nbsp; After the asphere is deformed into a sphere, the sub-aperture tool marks can be removed by post-polishing using the Goddard super-polishing process, a process limited to spheres and flats due to the fact that it requires the use of a tight fitting large polishing tool.&lt;/p&gt;
&lt;p&gt;The sensor uses graphene based&amp;nbsp;devices to sense the surface potential of a graphene channel exposed to an analyte. When analyte molecules adsorb onto the graphene surface, they induce a local change in electrical resistance. This effect is very pronounced in graphene due to the high surface area; high electrical conductivity; and inherent low noise, which makes the changes in resistance detectable.&lt;/p&gt;
&lt;p&gt;The radiometer channel will have significant filtering to reduce the contamination of the radar signal into the radiometer channels.&lt;/p&gt;&lt;p&gt;The successful isolation between the channels can then be confirmed through correlation calculations between the radar and radiometer data. &amp;nbsp;After aggressive thresholding and filtering to isolate the radar and radiometer channels, the radiometer data can be averaged to provide a conventional brightness temperature product.&lt;/p&gt;
&lt;p&gt;We propose to demonstrate the use of these so-called signals-of-opportunity (SOP) to perform bi-static active microwave remote sensing of land surfaces. Specially, we will demonstrate the exploitation of geostationary satellite transmissions within the direct broadcast service (DBS) to sense changes in a reflecting surface (e.g., the ground).&lt;/p&gt;&lt;p&gt;&amp;bull;Develop a RF receiver/interferometer system to receive broadcast signals of DirecTV satellites to perform bi-static active microwave remote sensing of the Earth&amp;rsquo;s surface.&lt;/p&gt;&lt;p&gt;&amp;bull;Demonstrate the concept of using signals-of-opportunity (SOp) to perform active bi-static active microwave remote sensing.&lt;/p&gt;&lt;p&gt;&amp;bull;Perform proof-of-concept ground measurements useful for sensing soil moisture and vegetation, snow, and sea ice.&lt;/p&gt;
&lt;p&gt;Doppler measurements from a rapid moving platform, such as spacecraft, or radars using fast scanning antennas have been especially challenging due to spectrum broadening and rapid decorrelation between successive pulses.&lt;/p&gt;
&lt;p&gt;Our goal is to drastically improve the frequency precision while retaining the fast tuning speed of widely tunable lasers&lt;/p&gt;
&lt;p&gt;Absorbers for soft x-rays need to be made thinner and with larger area, to collect more photons, and with minimal number of support stems. However, the structure is then more challenging to fabricate and more subject to distortion or damage from internal or external stress. We will test multiple fabrication/design innovations.&lt;/p&gt;
&lt;p&gt;Strained Layer Superlattice (SLS) detectors are a new class of detectors.&amp;nbsp;&amp;nbsp; In our FY12 IRAD &amp;ldquo;&lt;strong&gt;Strained Layer Superlattice Infrared Detector Array Characterization&amp;rdquo; &lt;/strong&gt;we verified that these devices exhibit a dramatic increase in quantum efficiency (QE) over quantum well infrared photodetectors (QWIPs) and are approaching QE values comparable with mercury cadmium telluride and indium antimonide detectors.&amp;nbsp;&amp;nbsp; The anticipated advantages of SLS detector technology over existing IR detectors are: high sensitivity, band-gap tunable wavelength response (similar to QWIPs), warmer operating temperatures, array spectral uniformity (yet to be realized), high temporal stability, relatively low cost of manufacturing, scalability (to very large format arrays) and multiple vendor sources all contributing to higher performing scientific instruments.&amp;nbsp; Warmer and more stable focal planes lead to simpler instrument designs which result in higher reliability, longer mission lifetimes and reduced costs.&amp;nbsp;&amp;nbsp; In our FY12 IRAD we obtained a test SLS array and performed extensive tests to ascertain the veracity of researcher claims, as well as to assess the potential applications to NASA missions from a practical infusion standpoint.&amp;nbsp;&amp;nbsp; The most important result of that investigation was the verification of the (unexpected) very high QE.&amp;nbsp; However, along with the dramatic improvement in QE we measured much higher dark current and the array was quite non-uniform. Before we embark on an ambitious in-house program to design and fabricate SLS detectors it would be very valuable to build an IR camera system using the existing SLS array we currently have and perform some local field tests.&amp;nbsp; We believe that actual IR imaging of external environment scenery will prove most valuable.&lt;/p&gt;
&lt;p&gt;The storage of cryogenic propellants is challenging because heat leaks into the cryogenic storage tanks no matter how good the insulation, resulting in a necessity to vent and maintain the propellant at the appropriate thermodynamic condition for engine operation and tank safety. &amp;nbsp;Although it is challenging to store LO2, it is even more difficult to store LH2 because of its lower boiling point. &amp;nbsp;There is therefore an increased focus for demonstrating LH2 storage in vent-free conditions.&lt;/p&gt;
&lt;p&gt;The end goal of this project is to develop proof-of-concept infrared detectors which can be integrated in future infrared instruments engaged in remote sensing.&amp;nbsp; We plan to evaluate several materials for their compatibility and performance.&lt;/p&gt;
&lt;p&gt;The project aims to develop a miniature packaging platform for the integration of MEMS mass spectrometer components to form the basis of a Micro Mass Spectrometer System for small, low mass, low power deployable sensor array applications. &amp;nbsp;Miniaturized packaging of MEMS mass spectrometer components into a functional mass spectrometer microsystem will be achieved through MEMS fabrication and miniaturized custom electronic and vacuum housing techniques.&lt;/p&gt;
&lt;p&gt;To date, we have (i) designed and fabricated both common cathode and common anode SiC detector arrays; (ii) designed and fabricated the detector packaging (FPA), and (iii) simulated, designed and fabricated a low-noise, compact pre-amplifier board. The FPA is mounted in the middle of the preamp board, to form the SiC array test assembly.&lt;/p&gt;&lt;p&gt;The project will integrate the SiC array assembly and optimize it for noise performance.&amp;nbsp; We will then construct a UV test setup capable of going from VUV to 385 nm spectral wavelength region, to characterize the SiC array.&amp;nbsp; The characterization will include dark current, noise, relative response and QE. The data analysis results will be the final end product.&lt;/p&gt;
&lt;p&gt;The device consists of a graphene piece deposited on a Si substrate with&amp;nbsp;certain&amp;nbsp;thickness of&amp;nbsp;insulation layer. In our initial experiment, constant radiation was applied above the GFET and device conductance was measured before and after the radiation. We observed an increase of the device mobility (transconductance) after the radiation. This demonstration showed that graphene is radiation hard and its conductance changes with radiation. With the IRAD fund, we will continue exploring sensing mechanisms in GFETs and identify optimal absorber substrates and device geometries to improve radiation detection speed, sensitivity, and energy resolution of our GFET-RS devices.&lt;/p&gt;
&lt;p&gt;This is a drastic enhancement to the current prototype which only allows us to collect visible light and reconstruct a single wavelength image. This approach is a high risk, potentially high-payoff method to address the problem of data volume transmission to Earth resulting from high-resolution hyperspectral imaging.&lt;/p&gt;
&lt;p&gt;The first year objective of this multi-year project is to develop a plan to assemble the common, essential monitoring and control functions required by spacecraft and instrument power systems and implement them in a semi-custom application specific integrated circuit (ASIC), a Power System-on-a-Chip (PSOC).&lt;/p&gt;&lt;p&gt;This approach promises at least 50&#37; miniaturization of the presently used control circuits, to increase reliability and reduce development cost through re-use, and lower component count, while increasing robustness of spacecraft systems to extreme temperature and radiation environments.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;System on a chip is a method to increase engineering efficiency. State of the art components are increasing in gate count as expected according to Moore&amp;rsquo;s law. In the past, a single engineer could write all of the code that would be placed into a smaller programmable component. As component density has increased, it now typically takes several engineers to develop a single chip. In the near future, design modularity and design reuse will be required to maintain engineering efficiency.&lt;/p&gt;&lt;p&gt;System on a chip allows NASA to develop or buy a library of functions which can be stitched together using a common interconnect bus. This promotes code reuse and greatly increases the speed at which a large, complex design can be developed. The direct benefits are efficiency and remaining competitive. This design methodology paves the way for the final goal of developing a complete spacecraft on a chip.&lt;/p&gt;&lt;p&gt;The goal of this project is to lay the key groundwork for being able to build a complete spacecraft on a chip.&lt;/p&gt;
&lt;p&gt;The primary objective is to determine whether this small satellite transporter is capable of transporting at least four 6U CubeSats is possible for a given set of mission scenarios.&amp;nbsp; The effort will include:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Defining a mission trade space for both LEO and deep space missions&lt;/li&gt;&lt;li&gt;Developing&amp;nbsp;flight dynamics options&amp;nbsp;and delta-v estimates&amp;nbsp;for the set of chosen mission scenarios&lt;/li&gt;&lt;li&gt;Conducting propulsion system trades with respect to propellant options, propulsion tanks, thruster types, etc. for each of the chosen mission scenarios&lt;/li&gt;&lt;li&gt;Performing mechanical systems trades to investigate structural configurations with respect to the propulsion system results that&amp;nbsp; would include a number of mass saving approaches&lt;/li&gt;&lt;li&gt;Determining mission possibilities for the SST&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;Goddard&amp;rsquo;s SpaceCube 2.0 is the latest in a line of compact, high-throughput, reconfigurable signal-processing platforms for space applications. &amp;nbsp;Different versions of the SpaceCube have served or will serve on numerous missions including the Materials International Space Station Experiment (MISSE-7),&amp;nbsp; the Hubble Space Telescope Servicing Mission 4 (HST-SM4), Small Rocket/Spacecraft Technology (SMART), Intelligent Payload Experiment (IPEX) CubeSat mission, and the geostationary robotic servicing RESTORE mission.&lt;/p&gt;&lt;p&gt;The work performed in this project consists of porting the Navigator GPS receiver to SpaceCube 2.0 flight platform. This involves porting Navigator&amp;rsquo;s software and firmware to SpaceCube and building a GPS radio frequency (RF) front-end electronics that will interface the GPS antennas to the signal processing module on the SpaceCube 2.0 chassis. Porting Navigator to SpaceCube will significantly advance the utility of SpaceCube by incorporating navigation capabilities that are currently lacking. Additionally, the flexibility and expandability of SpaceCube will allow for adding new capabilities to the Navigator GPS receiver including digital beamforming of a phased-antenna array and the modernized GPS L2C and L5 signals tracking capabilities.&lt;/p&gt;
&lt;p&gt;Study the performance of numerical integrators for flight dynamics analysis&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The multi-core processor supports several operating systems including state of the art multiprocessing operating systems, such as Linux SMP, and use ANSI C/C++ allowing existing code to be easily integrated.&lt;/p&gt;&lt;p&gt;We will evaluate and implement existing techniques to streamline our data processing system.&amp;nbsp; We will perform benchmark tests (or timing tests) to evaluate our improvements in processing speed needed to solve the problem.&lt;/p&gt;&lt;p&gt;Our goal is to embed the processor in the on-board electronics, therefore, we must determine the smallest number of cores that provide sufficient processing capabilities compatible with the power resources of the balloon experiment and low earth orbiting satellite.&lt;/p&gt;
&lt;p&gt;LabNotes is an IPad/IPod software application (app) and low-cost USB connector harness that can be used to operate and collect data from scientific instruments.&lt;/p&gt;
&lt;p&gt;
	Promote and encourage process and workflow reuse&amp;nbsp; within NASA Earth eXchange (NEX) by developing a proactive recommendation technology based on collective NEX user behaviors.&lt;br /&gt;
	Leverage social network analysis to intelligently extract hidden knowledge from a shared computing platform&lt;br /&gt;
	Extend our understanding of Earth science workflow interoperability and composition&lt;br /&gt;
	Provide a recommend-as-you-go workflow development environment&lt;br /&gt;
	Allow Earth science community to make more effective use of computational resources&lt;br /&gt;
	Enable more virtual collaboration through workflow reuse&lt;/p&gt;
&lt;p&gt;
	Develop a mission simulation and evaluation platform for terrestrial hydrology missions by creating an end-to-end observation system simulation experiment (OSSE) platform by using NASA LIS&amp;rsquo; data assimilation, optimization, and uncertainty estimation tools.&amp;nbsp; This platform will enable:&lt;br /&gt;
	Quantifying the impact of observations through a variety of OSSE configurations and evaluation metrics related to terrestrial hydrologic science and applications&lt;br /&gt;
	Improving the use of products for end-use applications and science, and quantifying the mission risks for GPM and GRACE-II&lt;/p&gt;
&lt;p&gt;
	Develop a packaged data management infrastructure for the comparison of generated climate model output to existing observational datasets that includes capabilities for re-gridding model and/or observational data and the computation of metrics (bias, RMS error, etc) describing the relationship between the models and the observations.&lt;br /&gt;
	&lt;br /&gt;
	Infuse the database and analysis framework with the Coordinated Regional Climate Downscaling Experiment (CORDEX), the National Climate Assessment (NCA), Earth System Grid (ESG), and USC/UC Merced (STEEDS).&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop advanced on-board processing to meet the requirements of the Decadal Survey missions:&lt;br /&gt;
	advanced instruments (hyper-spectral, SAR, etc) require advanced on-board processing to facilitate the timely conversion of ES &amp;ldquo;data&amp;rdquo; into ES &amp;ldquo;information&amp;rdquo;&lt;br /&gt;
	mission enabling technology to reconfigure/adapt on the fly; detect and react to events; produce data products on-board for direct downlink, quick look, and &amp;ldquo;first responder&amp;rdquo; real-time awareness; enable &amp;ldquo;sensor web&amp;rdquo; multi-platform collaboration; and perform on- board &amp;ldquo;lossless&amp;rdquo; data reduction by moving &amp;ldquo;ground&amp;rdquo; functions on-board&lt;br /&gt;
	&lt;br /&gt;
	SpaceCube 2.0 will directly support ACE, DESDynI, GEO-CAPE, HyspIRI, ICESat-II, LIST, SCLP, SMAP, SWOT, and 3D-Winds.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop a service-oriented hazard/disaster monitoring data system enabling both science and decision-support communities to monitor ground motion in areas of interest with InSAR and GPS.&lt;br /&gt;
	Enable high-volume and low-latency automatic generation of NASA Solid Earth science data products (InSAR and GPS) to support hazards monitoring.&lt;br /&gt;
	Enable improved understanding through visualization, mining, and cross-agency sharing of results.&lt;br /&gt;
	Enable interoperable discovery, access, and sharing of derived actionable products for hazards monitoring.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop W-band Gallium Nitride (GaN) MMICs to enable the advanced cross-track scanning, dual-frequency Doppler cloud radar concept in support of the Aerosol-Cloud-Ecosystem (ACE) mission.&lt;br /&gt;
	Targeted GaN MMIC component performance goals are:&lt;br /&gt;
	Power amplifier (PA): 1 Watt with 12 dB gain.&lt;br /&gt;
	Low noise amplifier (LNA): &amp;lt;6 dB noise figure with&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp; 17 dB gain.&lt;br /&gt;
	Single pole double throw switch (SPDT): &amp;lt;3 dB insertion loss.&lt;br /&gt;
	Phase shifter: 4 bit resolution and &amp;lt;8 dB insertion loss.&lt;br /&gt;
	Integrated MMIC chip with all transceiver front end functions.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Improve the use of land cover data by developing an advanced framework for robust classification using multi-source datasets:&lt;br /&gt;
	Develop, validate and optimize a generalized multi-kernel, active learning (MKL-AL) pattern recognition framework for multi-source data fusion.&lt;br /&gt;
	Develop both single- and ensemble-classifier versions (MKL-AL and Ensemble-MKL-AL) of the system.&lt;br /&gt;
	Utilize multi-source remotely sensed and in situ data to create land-cover classification and perform accuracy assessment with available labeled data; utilize first results to query new samples that, if inducted into the training of the system, will significantly improve classification performance and accuracy.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop interferometric High Spectral Resolution Lidar (HSRL) receiver component technology that will reduce mass, power, volume, risk, and cost for the Aerosols-Clouds-Ecosystems (ACE) Decadal Survey mission.&amp;nbsp; This interferometer will be a significant advance over the current HSRL-2 interferometer:&lt;br /&gt;
	More robust frequency locking (one degree of freedom vs. 3 in current design)&lt;br /&gt;
	Higher long-term calibration stability (increased accuracy in science retrievals)&lt;br /&gt;
	Allows simpler supporting detectors, electronics, and frequency locking architecture&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop an Automated Event Service system that:&lt;br /&gt;
	Methodically mines custom-defined events in the reanalysis data sets of global atmospheric models.&lt;br /&gt;
	Enables researchers to specify their custom, numeric event criteria using a user-friendly web interface to search the reanalysis data sets.&lt;br /&gt;
	Supports Event Specification Language (ESL) for more flexibility and versatility.&lt;br /&gt;
	Contains a social component that enables the dynamic formation of collaboration groups for researchers to cooperate on event definitions of common interest.&lt;br /&gt;
	Provides rapid results via high performance computing and advanced search technologies.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Fuse high performance reconfigurable processors with emerging fault-tolerance &amp;amp; autonomous processing techniques for a 10-100x decrease in processing time.&lt;br /&gt;
	This means more science experiments conducted per day &amp;amp; more thorough, timely analysis of captured data.&lt;br /&gt;
	Addresses the ability to quickly react &amp;amp; adapt processing or mission objectives in real-time, by combining autonomous agents with reconfigurable computing.&lt;br /&gt;
	Enables Autonomous On-board Processing for Sensor Systems (A-OPSS), via a tool-suite that generates a run-time system for sensor systems to autonomously detect changes in collected data &amp;amp; tune processing in a controlled manner to adapt to unforeseen events.&lt;br /&gt;
	Decadal Survey Missions: Primary - DESDynl, HyspIRI, GEO-CAPE; Secondary &amp;ndash; SMAP, SWOT&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Provide a collaborative research environment to streamline software delivery and execution process.&lt;br /&gt;
	Integrate cloud computing with NASA science algorithms&lt;br /&gt;
	Improve accessibility of data.&lt;br /&gt;
	Evaluate the efficacy of cloud services for NASA science algorithms.&lt;br /&gt;
	Enable scientists to contribute algorithms, software, data, and results in the broader science community.&lt;br /&gt;
	Demonstrate an end-to-end pipeline for data processing and modeling software.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Support the vision of Earth Science research as a community enterprise and provide building blocks for the Earth Science Collaboratory.&amp;nbsp; Leverage the evolving technology landscape to design an architecture for scalable collaboration&lt;br /&gt;
	Collaborations can scale from individuals sharing science resources, to sharing within groups such as science mission teams, to sharing with the entire science community.&lt;br /&gt;
	Design and build software components that fit the way researchers currently perform scientific analysis.&lt;br /&gt;
	These new components should work as part of researchers&amp;rsquo; current analysis tools.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Demonstrate 2&amp;beta; + 2&amp;alpha; + 2&amp;delta; High Spectral Resolution Lidar (HSRL) and Doppler wind lidar measurements simultaneously at 355nm and 532nm using a single multiwavelength interferometric receiver.&lt;br /&gt;
	&amp;nbsp;Demonstrate system components:&lt;br /&gt;
	High efficiency multi-wavelength optical autocovariance interferometer and integrated 2&amp;beta; + 2&amp;alpha; + 2&amp;delta; receiver&lt;br /&gt;
	HOAWL calibration and retrieval algorithms&lt;br /&gt;
	Validated radiometric and integrated HOAWL receiver performance models&lt;br /&gt;
	&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop, integrate and demonstrate a 2-micron pulsed Integrated Path Differential Absorption Lidar (IPDA) instrument CO2 Column Measurement from Airborne platform&lt;br /&gt;
	Conduct ground validation test to demonstrate CO2 retrieval&lt;br /&gt;
	Conduct engineering test flights to demonstrate CO2 retrieval from UC-12 aircraft&lt;br /&gt;
	Conduct post flight data analysis for the purpose of evaluation of CO2 measurement capability&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Optimize the performance of Gallium Antimonide (GaSb)-based 2.05 mm lasers (previously developed under JPL&amp;rsquo;s Research and Technology Development (R&amp;amp;TD) Program) for emission at the precise wavelength of 2.05 mm with an angular emission for efficient coupling into polarization maintained (PM) optical fiber&lt;br /&gt;
	Develop a robust fiber coupled hermitically sealed package to house the diode laser while maintaining its high power and narrow linewidth performance&lt;br /&gt;
	&amp;nbsp;Integrate these lasers in the frequency locked system (currently developed under under JPL R&amp;amp;TD Program) to demonstrate a frequency stable laser with at least 10 mW output power (with a 40-50mW goal), ~100 KHz linewidth, and 1 MHz long-term stability&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
Earth Science Mission Control Center Systems Study Project
&lt;p&gt;
	Facilitate use of Goddard Cumulus Ensemble (GCE), Weather Research and Forecasting Model (WRF), and Goddard Multi-scale Modeling Framework (MMF) with bin microphysics schemes that model aerosol-cloud-radiation interaction to:&lt;br /&gt;
	remove the largest source of uncertainty in climate modeling&lt;br /&gt;
	allow large-domain, long-term integrations to significantly improve the modeling capability of the aerosol effects for weather prediction and climate change studies&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop, integrate, and deploy software-based tools to coordinate asynchronous, distributed missions and optimize observation planning spanning simultaneous observations across multiple sensor systems to improve science return from Earth observing systems&lt;br /&gt;
	Develop and infuse situation awareness, situation assessment, planning and scheduling technologies for the coordination of independently managed missions into the Draper Earth Phenomena Observation System (EPOS)&lt;br /&gt;
	Infuse EPOS into NASA Earth science missions including HS3, ATTREX, and EO-1&lt;br /&gt;
	Demonstrate the resulting integrated &amp;ldquo;system of systems&amp;rdquo; targeting disaster data management&lt;br /&gt;
	&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop the technology to provide the fusion of observations and operational model simulations to help improve the understanding and forecasting of hurricane processes. Specifically:&lt;br /&gt;
	Develop processing techniques to enable multi-source data fusion across hurricane forecast models, satellite data, and in situ sensors.&lt;br /&gt;
	Develop tools to manage the validation and assessment of model comparisons to more easily evaluate the performance of different numerical models.&lt;br /&gt;
	Develop interactive visualization techniques to enable analysis of highly complex systems.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Define and facilitate implementation of a &amp;lsquo;system of systems&amp;rsquo; architecture for disaster mitigation and risk assessment responsive to GEOSS task DI-06-09 on Use of Satellites for Risk Management&lt;br /&gt;
	Leverage technology in service oriented architectures including sensor webs, web services and automation (e.g. EO-1 SensorWeb and VMOC) &lt;br /&gt;
	Coordinate with international (e.g. CEOS/WGISS, IC) and national (e.g. USGEO, USGS, NOAA) partners&lt;br /&gt;
	Prototype key capabilities enabled by the GEOSS architecture to validate and document user and web service interfaces&lt;br /&gt;
	Demonstrate architecture benefits: reduce latency, produce more useful products on-demand, and reduce costs by reuse&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Quantify the science benefits of GRACE-II mission comprised of multiple pairs of smallsats using realistic expected performance of smallsats and a miniaturized laser ranging system.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Design of the three array focal plane includes calculation of the various pixel performance specifications to optimize for each sub-array. Meeting the demanding specifications of each design is complicated by the fact that certain layers in the fabrication (such as the superconducting device layer that determines operation temperature) are common to the three arrays, limiting the design space.&lt;/p&gt;&lt;p&gt;Additionally, the presence of the different device scales presents a challenge to wiring of the array and the need to develop a low crosstalk crossover method for sorting the array into region that can share common bias of its pixels.&amp;nbsp; The second phase of the work will focus on improving the heatsinking in these arrays.&amp;nbsp; The heatsinking will be added last so that it can be varied in properties and heatsunk regions can be segregated.&amp;nbsp; While more open-ended, this research will explore how improvements in practical array performance can be achieved.&lt;/p&gt;
&lt;p&gt;The SWIR wavelengths are essential for science requirements for aerosol retrievals over land, for enhanced particle microphysics, and for aerosol absorption estimates.&amp;nbsp; SWIR wavelengths also add important microphysical and thermodynamic information for cloud particles.&lt;/p&gt;
&lt;p&gt;
	Integrate LVIS lidar capability onto the Global Hawk (GH) to enable high altitude mapping of land, vegetation, and ice&lt;br /&gt;
	Provide operational capability and data storage for 30+ hours of GH operations&lt;br /&gt;
	Demonstrate operations on Global Hawk platform with test flights&lt;/p&gt;
&lt;p&gt;
	Design, fabricate, and calibrate a compact helium magnetometer for high-accuracy measurements of Earth&amp;rsquo;s magnetic field&lt;br /&gt;
	Provide vector and scalar measurements from a single instrument&lt;br /&gt;
	Utilize scalar measurements to self-calibrate the vector component measurements&lt;br /&gt;
	Intended for surface, sub-orbital, and orbital platforms&lt;br /&gt;
	Achieve superior calibrated vector accuracy (&amp;plusmn;1 nT per component) not possible with fluxgate magnetometers&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Real-time quantification of volcanic gaseous and particulate releases from analysis of satellite-based Thermal Infrared (TIR) spectral imagery data&lt;br /&gt;
	Real-time visualization of the impact of changes in model parameters on the fit between observed and model radiance spectra.&lt;br /&gt;
	Graphical Processing Unit (GPU) implementation of MODTRAN&amp;rsquo;s TIR radiance algorithms integrated into an interactive toolkit for retrieving and mapping the 3-D composition of atmospheric plumes using JPL established retrieval algorithms.&lt;br /&gt;
	Achieve 100 fold run-time reduction of radiative transfer calculations vs. state-of-the-art MAP_SO2 model.&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Develop an UV-NIR (350nm to 1050 nm) portable remote imaging spectrometer (PRISM) for flight on a variety of airborne platforms with high SNR and response uniformity optimized for coastal ocean science:&lt;br /&gt;
	Unprecedented sensitivity for assessing the large dynamic range in observed coastal reflectance at ~3 nm spectral resolution&lt;br /&gt;
	Provide performance exceeding the state-of-the-art in light throughput, spectral and spatial uniformity, and polarization insensitivity by factors of 2-10, while extending the spectral range into ultraviolet&lt;br /&gt;
	Provide a two-channel SWIR (1240 nm and 1640 nm) radiometer to facilitate application of the atmospheric correction algorithm&lt;/p&gt;
Software Infrastructure to Enable Modeling &amp; Simulation as a Service (M&amp;SaaS) Project
&lt;p&gt;
	Integrate the UAVSAR L-band radar to the Global Hawk UAV Bay 25&lt;br /&gt;
	Provide long range (~ 9000 nmi) to enable data collection of distant areas of interest without complicated deployments&lt;br /&gt;
	Study the ability of the Global Hawk to accommodate UAVSAR &amp;ldquo;Mini-Pods&amp;rdquo; under each wing to enable precision topographic maps and single pass polarimetric interferometry (SPI) providing vertical structure of ice and vegetation.&lt;/p&gt;
&lt;p&gt;Particle instruments in general such as mass spectrometers and plasma analyzers face two common problems that degrade their performance: (a) penetrating radiation through the walls of the instruments resulting in higher noise levels due to increased background signal and (b) undesirable foreground signal (e.g. ions and UV) through the aperture which degrades the useful signal. Both have the effect of reducing the useful S/N in an instrument and therefore performance. Those issues become more severe in certain environments such as the radiation belts but also in FOVs facing the solar geo &amp;ndash; coronal light contamination. Typical mitigation techniques for background include increasing the walls of the instruments &amp;ndash; with a heavy impact on mass, which is often impractical &amp;ndash; or increasing thresholds in suppression.&lt;/p&gt;&lt;p&gt;Although the use of foils and coincidence timing in plasma instrumentation is common, &lt;em&gt;the foil and coincidence technique we propose has never been implemented for background/foreground suppression in this way. &lt;/em&gt;The proposed technique will solve this problem for future instruments in high radiation environments.&lt;/p&gt;
&lt;p&gt;&amp;nbsp;CREPT will measure electrons and protons in multiple differential energy channels.&lt;/p&gt;
&lt;p&gt;The&amp;nbsp;Wide Field-of-View (FOV)&amp;nbsp;Soft X-Ray Imager proposes to&amp;nbsp;be a state-of-art instrument with applications for numerous heliospheric and planetary missions.&amp;nbsp; The result is expected to provide improved global space environment&amp;nbsp;models that will benefit scientists and the general public.&lt;/p&gt;
&lt;p&gt;When investigating the processes in the atmosphere, measurement of trace gas concentrations is&amp;nbsp;essential.&amp;nbsp; However, measuring trace gas concentrations is very challenging because exteme sensitivity to detection.&amp;nbsp;&amp;nbsp; &lt;strong&gt;LIDaR&lt;/strong&gt; (&lt;strong&gt;L&lt;/strong&gt;aser &lt;strong&gt;I&lt;/strong&gt;maging &lt;strong&gt;D&lt;/strong&gt;etection and &lt;strong&gt;R&lt;/strong&gt;anging) is an optical remote sensing technology that can measure the distance to, or other properties of, targets by illuminating the target&amp;nbsp;using laser light and analyzing the backscattered light. LIDAR technology has many applications including atmospheric physics.&lt;/p&gt;&lt;p&gt;The proposed technology uses LIDaR to determine atmospheric trace gas concentrations.&lt;/p&gt;
&lt;p&gt;A miniaturized, solid-state frequency-quadrupled Nd:YAG laser system&amp;nbsp; will be tested for performance and mechnically packaged to support future mission-driven instrumentation.&lt;/p&gt;
&lt;p&gt;The Neutral Atom Sensor Project examines advances in energetic neutral atom (ENA) imager for broad planetary&amp;nbsp; applications.&lt;/p&gt;
&lt;p&gt;The Digital Radio Prototype project evaluates and tests digital receiver and spectral analyiss tools for various planetary environment.&lt;/p&gt;
&lt;p&gt;The Deployable Entry-system ProjecT (ADEPT) will develop requirements for the ADEPT flight test.&amp;nbsp; Prior entry systems used high mass thermal protection systems.&amp;nbsp; This project is focused on increasing the TRL of an alternative, deployable entry system that is appropriate for medium size planetary missions.&lt;/p&gt;
&lt;p&gt;The CubeSat Capabilities for Space Science Missions combines science and engineering talent at Goddard Space Flight Center and the Wallops Flight Facility to understand requirements and contraints for&amp;nbsp;the science-driven Cubesat framework.&amp;nbsp; The project prototype design incorporates current capabilities, as well as,&amp;nbsp;capabilities expected to be available 2018 - 2023.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The Improved Mass Spectrometer&amp;nbsp;project will develop system requirements and analyze the path to space qualification.&amp;nbsp;&amp;nbsp; The results of this project will provide substantially improved analytical capabilities for in situ analysis for future missions.&lt;/p&gt;
&lt;p&gt;Geochronology is the science of determining the age of rocks, fossils, and sediments.&amp;nbsp; The science of geochronology is the prime tool used to attempt to derive absolute age dates for all fossil assemblages and determine the geologic history of the Earth and extraterrestrial bodies.&lt;/p&gt;
&lt;p&gt;The In Situ Mass Spectrometer projects focuses on a specific subsystem to leverage advanced research for laser-based in situ mass spectrometer development project.&amp;nbsp; This subsystem component is being developed in parallel with a laser spectrometer for integration.&lt;/p&gt;
&lt;p&gt;The Instrument for Trace Gas Measurements will provide advances in situ measurement instrumentation for planetary atmospheres and surfaces.&lt;/p&gt;
&lt;p&gt;The SPOT test bed consists of three one-meter-class segments on tip/tilt and piston actuators.&amp;nbsp; The purpose of the test bed is to demonstrate wavefront sensing and control technologies for large segmented telescope architectures, without requiring separate dispersive elements or periodic rephasing.&amp;nbsp; The SPOT architecture utilizes a point source at the radius of curvature of the mirrors and performs image-based wavefront sensing (WFS), also known as phase retrieval.&lt;/p&gt;
&lt;p&gt;The objectives of this proposal are twofold: 1) develop a suite of flight software tools for utilizing the advanced capabilities inherent in the guide-mode features of the present generation of near-infrared detectors, and 2) develop an implementation of sample-up-the-ramp processing for NIR detector readouts that gracefully handles signal saturation and cosmic-ray hits during an exposure.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;The objectives of the guide mode software development are to learn how to generate optimal clocking sequences for interleaving rapid readout of multiple guide windows with slower readout of science data from the rest of the detector, and to develop software to implement these sequences in the SIDECAR&amp;trade; ASIC for use in flight applications.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;We plan to produce filters with holes so small that longer wavelength photons are unable to propagate through, whereas the shorter wavelength x-ray photons simply pass through the holes unimpeded. This type of filter is called a &amp;ldquo;grill filter&amp;rdquo; and the desired functionality is possible due to the large separation in frequency between the block and pass bands.&lt;/p&gt;
&lt;p&gt;The effort will involve a mechanical and thermal study for installation of CRS into the Global Hawk, RF design for integrating the HIWRAP Ka-band transceiver with CRS and a new subscale prototype antenna for ACE, and specification and testing of a Ka-/W-band radome necessary in front of the antenna. The proposed work will be a solid design concept for a dual-frequency CRS that can be readily implemented on the Global Hawk. Since CRS is currently single frequency (W-band) and the NGES antenna is dual-frequency (Ka- and W-band), this effort investigates what is necessary to use the HIWRAP Ka-band transceiver with CRS timing and other interfaces. Finally, the Global Hawk installation will require a dual-frequency radome and part of this effort will investigate suitable radome materials that is transparent at at both operating frequencies.&lt;/p&gt;
&lt;p&gt;The plan to develop a cost-compliant EV-i instrument concept entails developing a science and instrument-performance trade space that considers channel selection, spatial resolution and swath, as well as auxiliary information obtained by potential co-manifested instruments. The trade-space is fairly complex, but by defining a small set of instrument/mission configurations, a cost matrix will indicate a point design of a CISSIR-like instrument that meets the EV-i cost constraint.&amp;nbsp; Requirements for power dissipation cause the addition of mass and other complexities for the present design.&amp;nbsp; We believe that we can successfully reduce the power consumption with compounded benefit in mass and cost.&lt;/p&gt;
&lt;p&gt;The entire BACAR project is organized following a standard design/build top-level process that includes: conceptual design, trade studies, preliminary design, critical design and fabrication/test.&lt;/p&gt;
&lt;p&gt;Tropospheric ozone (O3) is an important greenhouse gas.&amp;nbsp; Background concentrations of tropospheric O3 have increased 100-200&#37; over the past century producing a climatic impact comparable to that of CH4 (exceeded only by CO2 among other greenhouse gases). Aerosol increases generally have the opposite direct climate impact, diminishing greenhouse warming by reflecting more sunlight back to space.&amp;nbsp; Aerosol also affects cloud processes, an indirect climate effect that is unquantifiable today. Changes in the large-scale atmospheric composition contribute to worsening local air quality in many regions. Declining air quality in the US costs the public billions in health care and lost productivity, produces several thousand premature fatalities annually [1], damages our environment, and decreases our standard of living.t&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The goal of this study is to build a breadboard spectrometer and prove the functionality of the optical-mechanical assembly for the COEDI instrument concept.&amp;nbsp; We will verify spectrometer performance in the lab using off-the-shelf optics, existing sources and integrating spheres through test measurements of image quality, dispersion, slit curvature, and optical throughput.&amp;nbsp; The design concept will be further refined based on optical and mechanical modeling analysis.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;An IRAD award in FY 2011 enabled the G-LiHT concept to be designed, assembled, installed and tested on a NASA fixed-wing, airborne platform.&lt;/p&gt;
&lt;p&gt;A CubeSat is a volume-limited, standardized smallsat form factor (typ. 1-6U, where 1U&amp;nbsp;=&amp;nbsp;10&amp;nbsp;cm&lt;sup&gt;3&lt;/sup&gt;) that occasionally needs to be equipped with an active attitude control system, e.g. reaction wheels needed for high-resolution science imaging, orbit maintenance, and maximum irradiance on solar cells. The proposed architecture provides improved performance over traditional wheels and satisfies the push for component miniaturization, increased pointing accuracy, and power efficiency on CubeSats.&lt;/p&gt;
&lt;p&gt;The broad&amp;nbsp;objective of this project is to accurately model fuel slosh in a low-gravity environment and then connect the fuel slosh model to a simulation&amp;nbsp;environment that will allow for the testing of attitude control algorithms.&amp;nbsp; STAR-CCM+, a commercially available&amp;nbsp;computational fluid dynamics (CFD) software package, is used to&amp;nbsp;model the fuel slosh and output forces, torques, and center of&amp;nbsp;mass&amp;nbsp;position changes&amp;nbsp;due to the&amp;nbsp;fuel slosh.&amp;nbsp; Freespace is&amp;nbsp;used&amp;nbsp;as the simulation environment to test the attitude control algorithms.&amp;nbsp; The Solar Dynamics Observatory (SDO) spacecraft is modeled with mission like maneuvers.&amp;nbsp;&lt;/p&gt;&lt;p&gt;SDO was chosen because the spacecraft&amp;nbsp;went into a safe mode due to the attitude control system not being able to accurately point the spacecraft.&amp;nbsp; The forces and torques that caused this problem came from SDO&amp;#39;s fuel slosh.&lt;/p&gt;&lt;p&gt;Below&amp;nbsp;are listed key accomplishments of this project.&lt;/p&gt;&lt;ul&gt;&lt;li&gt;CFD modeling of bare SDO tank&lt;/li&gt;&lt;li&gt;CFD modeling of SDO tank with static propellant management device (PMD) vanes&lt;/li&gt;&lt;li&gt;CFD modeling of SDO tank with deformable PMD vanes&lt;/li&gt;&lt;li&gt;Linking of above CFD models to Freepsace&lt;/li&gt;&lt;li&gt;Testing of linked CFD models and Freespace with SDO like spacecraft maneuvers&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Availability of a safe, low-pressure, lightweight, compact hydrogen storage system is an enabling technology for hydrogen electric fuel cell usage for space exploration and advanced aircraft electric propulsion systems.&amp;nbsp; Titanium hydride is being be used as a model material for proof of concept.&amp;nbsp; Other hydrides with more hydrogen per unit mass will then be evaluated.&amp;nbsp; Ultimately, nanostructured materials (such as carbon nanotube sheets) with potential to store large quantities of hydrogen in a very small volume will be explored.&lt;/p&gt;
&lt;p&gt;We propose the investigation of pyroelectric energy harvesters with enhanced efficiencies through quantum wells induced by a multilayer design.&amp;nbsp; Pyroelectric materials generate surface charges/voltage when heated or cooled.&amp;nbsp; This type of material has been investigated for energy harvesting applications, but have thus far yielded power far below theoretically calculated outputs.&amp;nbsp; The innovation here is the multilayer design that takes advantage of quantum wells induced by thin layers of materials with mismatched band gaps to enhance local polarization of confined charge particles by a potential well with discrete energy thus enhancing power generation.&lt;/p&gt;
&lt;p&gt;NASA Langley has succeeded in growing a rhombohedrally oriented single crystal SiGe on sapphire substrate. This opens up new challenges in micro-electronics. Since the carrier mobility in single crystal SiGe shows 2.5 (electron)&amp;nbsp; and 5 (hole)&amp;nbsp; times respectively faster than in mono-crystal silicon, the development of ultra fast chipsets is possible to go beyond the bottleneck of data transmission in telemetry system.&amp;nbsp; These results open up new oppotunities to build other electronic application chipsets beyond the prevailing clock frequency based on the miniaturization of the feature size. The research at NASA will eventually lead to collaboration with industries to build ultra-fast chipsets based on our single crystal SiGe wafers.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Quantum-well structures embodied on single crystal silicon germanium drastically enhanced carrier mobilities.&amp;nbsp; The cell-to-cell circuits of quantum-well PV cells are laid out at the bottom of epitaxial layers, unlike the circuits laying out at the top of the conventional PV cells which cut off the incident solar flux up to 15&#37; level. Since the circuit layout is built at the bottom of PV array, the circuits are densely laid out to reduce the internal resistance substantially. Again since silicon germanium compound has much broader bandgap structure than silicon alone, it can utilize more solar energy to free up valence band electrons. Structurally, the sapphire substrate surface of quantum-well PV cells is very strong and does not require any special protective coatings and frames to hold them. Therefore, the anticipated life of quantum-well PV cells is more than ten-times longer than Si PV cells. Summing up these advantages of quatum-well PV cells, the overall conversion efficiency would reach well beyond 35&#37; and the energy density would be tripled as compared to the conventional PV cells. The overall cost factor would be 5 cents per kWh competitively.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The MHSHS concept is unique in integrated TPS with primary load carrying structure. This approach offers the potential to reduce mass and increase volume while providing a dimensionally stable vehicle outer mold line for precision landing in cases where heating rates are well below 200 W/cm-2. A building block approach is being persued to develop this technology ultimately needed for advanced missions while in the interim providing a more lightweight alternative for use on ISS return missions.&lt;/p&gt;
&lt;p&gt;Doped Chiral Polymer Metamaterials (DCPM) with tunable resonance frequencies have been developed by adding plasmonic inclusions into chiral polymers with variable orientations. Amplifying the chiral parameter (k) while lowering the real part of the permittivity (e&amp;rsquo;) can achieve metamaterials without having a negative permeability (&amp;micro;&amp;rsquo;) or complex architecture. Commercially available chiral polymers are doped with plasmonic particles using a novel supercritical fluid&amp;nbsp; infusion method.&amp;nbsp; Lightweight, flexible DCPM offers compact and light devices capable of beam steering, beam dispersion reduction, miniature solid state filters, ultra-thin backward &amp;amp; conformal antennas, superlenses, and optical limiters to create supersensitive earth/interplanetary sensors, telescopes, and improved communications for various NASA missions.&lt;/p&gt;
&lt;p&gt;The high-permittivity substrate (er = 10.2) allows individual antenna patches to be made smaller and also mimics substrates (Si, SiC, GaAs, InP, GaN) used in MMIC and OEIC technology. If successful, the antennas may be integrated together with receiver components on the same substrate for miniaturization. Another important benefit is that surface waves are inhibited so that devices on the same substrate are isolated from each other.&lt;/p&gt;
&lt;p&gt;Mid Infrared DIAL systems can provide vital data needed by atmospheric scientists to understand atmospheric chemistry. The Decadal Survey recommended missions, such as ASCENDS and GACM, to measure atmospheric constituents such as CO2, CH4, CO, O3, NO2, SO2, and CH2O.&amp;nbsp; However, as noted by the Decadal Survey, mid infrared solid state lasers needed for DIAL systems are not available. This program proposes a systematic search for novel mid infrared solid state lasers utilizing a quantum mechanical model and verifying results using spectroscopy.&amp;nbsp; Specifically novel mid infrared lasers will be sought to measure the atmospheric constituents noted above.&amp;nbsp; A 2 front approach is proposed.&amp;nbsp; On 1 front, Langley&amp;rsquo;s quantum mechanical model will be used, where applicable, to predict good laser materials.&amp;nbsp; On the other front, mid infrared spectrometers will measure both absorption and fluorescence spectra will to be analyzed.&amp;nbsp; This information will verify the quantum mechanical model predictions and serve as input parameters for laser models. A successful program ends with the identification of a good laser material for at least 1 of the listed atmospheric constituents and a measurement of its germane spectroscopic parameters.&amp;nbsp; The eventual goal is the demonstration of a mid infrared laser suitable for remote sensing work.&lt;/p&gt;
&lt;p&gt;This delta-sigma technique may be thought of as a form of analog-to-digital converter (ADC). The proposed network offers a means of processing electronic signals from transducers directly into a form of digital representation. By using integrated circuit methodologies, it is expected that very small signals can be measured more accurately than the more usual discrete-evel methods (ie: using discrete parts and printed circuit boards). In this particular study, these techniques are applied to photodetectors. By maintaining the quality of signals in the lower end of the dynamic range, a successful implementation will allow the use of smaller lasers (or further detection range for the same laser power) for a given application while implementing the receiving electronics in a much smaller and lower power package.&lt;/p&gt;
&lt;p&gt;The objective of the project is to initiate realization of the Digital Twin concept for composites by coupling state-of-the-art, nondestructive characterization techniques with 3D numerical modeling to study the constituent-level failure of FRP composites. Near-term implications for this work include significantly increasing our understanding of the fundamental, constituent-level, failure mechanisms in current FRP composites through ultra-realistic, multi-physics simulations. The work will have long-term impacts on the design of innovative composites by virtual testing and on the incorporation of composites into the Digital Twin framework. The initial benchmark for success will be the high resolution (i.e. 385 nm) characterization, reconstruction, and finite element discretization of an approximately 130&amp;times;130&amp;times;130 mm3 volume of unidirectional graphite/epoxy composite (e.g. IM7/8552, AS4/3501-6).&lt;/p&gt;
&lt;p&gt;Compared with carbon nanotubes, BNNT&amp;#39;s possess better mechanical properties and are thermally stable to much higher temperatures. The potential benefits of BNNT-reinforced structural materials can only be explored if commercial quantities of high purity, low defect BNNT&amp;#39;s are available to the aerospace industry.&amp;nbsp;The majority of nanotube production for structural composires is focused on generating &amp;#39;yarn&amp;#39; for continuous reinforcement of polymer-based matrices.&amp;nbsp; The goal of this effort is to synthesize relatively short &amp;#39;fibers&amp;#39; for discontinuous reinforcement of metal- or ceramic-based matrices.&lt;/p&gt;&lt;p&gt;A novel combination of the RFPS process with a chemical reaction chamber for rapid, in-situ synthesis is envisioned.&amp;nbsp; The effort will draw on extensive work performed in Russia during the 1980&amp;#39;s (Tumanov, et al.).&amp;nbsp; Their nuclear industry developed &amp;#39;plasma-chemical synthesis&amp;#39; of nano-sized powders of metal oxides, carbides and nitrides.&amp;nbsp; The lack of consumable electrodes and the confined environment characteristic of RFPS offer big advantages over the DC and atmospheric plasma techniques employed in the prior work.&amp;nbsp; It is anticipated that the approach will yield abundant quantities of high purity nanotubes of the order of 10 microns long.&amp;nbsp; A goal will be to separate single- and multi-walled species during the process.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;FLEET uses a 100 fs laser to excite a multi-photon process that makes the gas (N2 or air) glow.&amp;nbsp; Images of the glowing gas taken at set time intervals allow the gas velocity to be measrued.&amp;nbsp; FLEET has the following advantageous features compared with existing measurement techniques: (1) it excites naturally-present N2 so it can be used in N2 or air flows - not requiring additional gas or particle seeding; (2) both excitation and detection are in the visible spectral range, so special UV or IR windows are not required; (3) only a single laser and camera is required which simplifies setup and operation; (4) the technique has been shown to work over a large range of pressures and is therefore amenable to a wide range of speed regimes (subsonic to hypersonic); and (5) the technique can easily be extended to measure thousands of samples per second.&amp;nbsp; The technique is thus applicable to a much wider range of wind tunnels than any other velocity measurement technique currently being developed at NASA.&amp;nbsp; For comparison, one currently state-of-the-art technique, NO2 molecular tagging velocimetry, requires three lasers, requires seeding the flow with toxic NO2 gas, requires expensive UV-grade fused silica windows on two sides of the wind tunnel and is limited to about 10 measurements per second.&lt;/p&gt;
&lt;p&gt;Radiation exposure to living tissue generates free radicals through ionizing reaction such as photoelectric effect, Compton and Auger effects.&amp;nbsp; Radiation induced lung damage (pneumonitis/fibrosis) is the leading cause of death in persons acutely exposed to radiation when gastrointestinal and hematopoietic syndromes are successfully treated. Our preliminary study has shown that CNPs protect from radiobiological effects of photons on healthy tissue. Successful completion would lead to an effective and safe method for restoring normal tissue function and improving survival following acute radiation exposure.&lt;/p&gt;
&lt;p&gt;Crack initiation and propagation is a dominant failure mode for many materials and applications &amp;ndash; usually managed via damage tolerance approaches.&amp;quot;&amp;nbsp; NASA?s long-duration missions require material performance (including reliability and durability) far beyond what is possible today. Inspection and repair is extremely costly and may not even be possible.&amp;quot;&amp;nbsp; The goal here is to develop structural materials that arrest cracks while they are still at the microstructural length scale and well before they reach a critical state.&amp;nbsp; We will design, synthesize and characterize material microstructures that exploit the mechanisms of self-arrest to manage fatigue crack growth and exhibit vastly increased service life, eliminating durability as a design driver (i.e., develop ageless materials).&amp;quot;&amp;nbsp; The approach leverages a decade of work in Damage Science to address the problem of material design&amp;quot;&lt;/p&gt;
&lt;p&gt;Electric Propulsion (EP) is a rapidly developing technology frontier that opens up the degrees of freedom for aircraft design/integration.&amp;nbsp; Inherently EP wants to distribute across the airframe due to it&amp;#39;s scale-free nature, this lets the thrust be located for optimal drag. Electric motors are highly compact and reliable. The efficiency and power to weight of electric motors/controllers are relatively insensitive to scale (not true for internal combusion or Turbine engines). Distributed EP permits high degrees of coupling between the aerodynamics, propulsion, control, acoustics, and even the structure to enable large multi-disciplinary synergistic benefits.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Practical spinning solar sail architectures will be needed to meet low areal densities and large areas required for the most challenging science and exploration solar sail missions.&amp;nbsp; The heliogyro spinning solar sail is the most attractive high-performance spinning architecture, but TRL is very low and deployment and flight dynamics are impossible to validate on the ground.&amp;nbsp; A pathway towards an affordable flight demonstration of a practical heliogyro spinning solar sail will be required to realize the full potential of solar sailing for solar system exploration and science missions.&lt;/p&gt;
&lt;p&gt;Boron-nitride nanotubes (BNNTs) exhibit electroactive behavior in response to mechanical deformation, but the origin of this phenomenon is not well understood. Our goal is to explain how atomic scale structural changes produce macroscopically observable electrical behavior. We are developing and validating a new interatomic potential for use in molecular dynamics simulations aimed at systematically exploring the nature of the electo-mechanical coupling observed in this material.&lt;/p&gt;&lt;p&gt;Specific outcomes from this work will be a validated BN interatomic potential that incorporates the physical effects required to correctly represent the electroactive properties of BNNTs and a mechanistic understanding of how their atomic structure couples to an external electric field. Achieving this will permit the development of lightweight structural sensors/actuators for IVHM in extreme environments with previously unachievable combinations of strength, toughness, and thermal stability.&lt;/p&gt;
&lt;p&gt;
	Year 2 of project:&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	The project continues the development of a microgravity-compatible BRIC evaporation chamber.&lt;br /&gt;
	The current BRIC system is a low-fidelity system/component breadboard used to demonstrate the basic functionality of an &amp;quot;in-place&amp;quot; brine drying process.&amp;nbsp; Under the current BRIC IR&amp;amp;D project, significant progress has been made in the development of a microgravity-compatible BRIC evaporator design.&amp;nbsp; These advancements include a number of potential BRIC evaporator design concepts employing novel static phase separation approaches based on capillary and surface tension phenomenon.&amp;nbsp; These design concepts have been furthered through the design and development of sub-scale test articles and methods for testing these systems under conditions of microgravity.&amp;nbsp; Data collected through this test program has highlighted the need to further refine the design and validate the performance of a BRIC system for brine dewatering applications in microgravity.&lt;/p&gt;
&lt;p&gt;
	Year 1 of project:&lt;/p&gt;
&lt;p&gt;
	Data describing the physical properties and drying behavior of brines, including vapor pressure equilibria, emissivity, specific heat, surface tension, and cohesion/adhesion and tack were determined as a function of the brine drying process.&amp;nbsp; Brine is generated using a rotary evaporator (Buchi, model K100) from human donated urine, augmented to match characteristics of urine produced on the International Space Station (ISS).&amp;nbsp; Brine solids were produced using the pre-prototype BRIC system.&amp;nbsp; In addition, sampling of the gas effluent of the system was conducted in partnership with the Space and Life Sciences Toxicology Laboratory to address concerns regarding hazardous gases that may evolve during the drying of brine solutions.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Total Organic Carbon (TOC) analyzers function by converting (oxidizing) all organic compounds (contaminants) in the water sample to carbon dioxide gas (CO2), then separating and measuring the CO2 produced.&amp;nbsp; The data output is TOC concentration in ppm.&amp;nbsp; Total Inorganic Carbon (TIC) can also be measured in the same analysis.&amp;nbsp; Conventional TOC analyzers use at least 2 externally supplied &amp;ldquo;reagents,&amp;rdquo; a liquid buffer/oxidizer and a sweep gas to move the product CO2 to the detector.&amp;nbsp; We intend to eliminate all externally supplied consumables in this project. The MiniTOCA will use a preloaded long-life buffer, extremely small sample volumes (minimizes waste stored internally), and either purified ambient air as sweep gas or generate gas internally by electrolysis.&amp;nbsp; The MiniTOCA subsystems are developed and tested separately, then integrated.&amp;nbsp; Conventional plumbing and complex connections diminish in number dramatically by integrating the subsystems in creative ways.&amp;nbsp; This 2nd year effort focuses on the reactor and quantitative water sample injector plus integration, software and preliminary packaging.&amp;nbsp; Breadboarding to date indicates all the components will fit into a 1liter cube, excluding batteries.&amp;nbsp; The prototype system will be tested and debugged in the JSC Water &amp;amp; Food Lab using challenge solutions prepared in the Lab.&amp;nbsp; The 3rd year of funding will focus on eliminating any gravity dependencies, refining operational aspects, packaging and designs for a flight technology demonstration.&lt;/p&gt;
&lt;p&gt;The proposed technology reduces crew reliance of ground and paper procedure support in deep-space human spaceflight missions by providing real-time, in situ task guidance,&amp;nbsp;and reducing the training burden by providing all relevant information into the operator field of view. AR has the potential to assist crew in many nominal and off nominal operational procedures execution, thus enabling crew autonomous operation and reducing their dependency on ground support.&lt;/p&gt;&lt;p&gt;The marker-less AR system that minimizes tagging logistics and registration is especially attractive for space operations.&amp;nbsp; This technology uses a camera and image processing technique to create a &amp;ldquo;point cloud&amp;rdquo; map to register the real-world objects, which then enables the crew to get overlay information directly in the crew&amp;#39;s field of view through the AR glasses. Procedure steps and animated 3D overlays of the device being worked on can significantly minimize the maintenance operations difficulty.&lt;/p&gt;&lt;p&gt;The project is proposed as a multiyear effort.&amp;nbsp; Three AR prototypes were developed in year one to assess and to demonstrate the feasibility of the technology in the context of electronic procedures and maintenance operations.&amp;nbsp; The second year objectives are to enhance the vision processing capability and to improve robustness of the year one prototypes.&amp;nbsp; If successful, the third year will focus on assessing the feasibility to fly the proposed system as an ISS DTO.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;This project seeks to advance ground based tele-robotic capabilities with the development of natural feature target tracking technology with the use of machine vision. The machine vision technology will be applied to Mobile Servicing System (MSS) Ground Control on the ISS as a proof of concept for increasing efficiency and safety of operations.&amp;nbsp; The current MSS Ground Control systems rely on operator interpretation of visual cues which are sometimes nothing more than comparing the payload with surrounding structure. This technology has the potential to automate much of this operator interpretation providing safer and more efficient Ground Control operations. This project is led by JSC civil servants and scope to one year in length.&lt;/p&gt;
&lt;p style="margin-left:2.15pt;"&gt;
	With over 100,000,000 particles smaller than 1 cm in low earth orbit, it is critical that shielding will adequately protect from impacts of this size. &amp;nbsp;A 3SLGG is a validated method to accelerate small particles up to 10 km/s.&amp;nbsp; Enabling WSTF to simulate the average LEO velocity of 10 km/s will provide the means to validate ballistic limit equations used to design protective shields. &amp;nbsp;The first phase was accomplished using the 3SLGG code, which provided the optimal beginning geometric and pressure parameters. &amp;nbsp;The next phase will include fabrication of the components, development of procedures, safety/design reviews and build up of the launcher system.&lt;/p&gt;
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	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Candidate hydrazine alternatives have been developed for spacecraft propulsion. The U.S. Air Force AF-M315E and the Swedish ammonium dinitramide propellants have received the most attention, while ammonium dinitramide propellants are a possible contender. While greenness relates to environmentally benign and relative toxicity, neither of these propellants is completely &amp;ldquo;nontoxic&amp;rdquo; or completely safe; if their energetic nature was not inherent they would not be used as monopropellants. This is particularly important with ammonium dinitramide (ADN) and hydrazinum nitroformate (HNF) propellants, which ESA and the EU has favored while the U.S. Air Force has focused on AF-M315E and the U.S. Army has investigated hydroxylammonium nitrate/triethanolammonium nitrate (HAN/TEAN; XM-46) propellants.&amp;nbsp; The first phase of the project&amp;rsquo;s focus will be to evaluate detection and decontamination methods for these propellants.&amp;nbsp; The second phase examined candidate materials for use in AF-M315E propulsion systems. Pairs of representative alloys, passivated and native, were immersed in AF-M315E at 71 &amp;deg;C for 31 d, fluid samples were periodically characterized and post-test materials and fluids were finally characterized. Typical corrosion studies use only the total time of immersion; this study also obtained interim data points.&lt;/p&gt;
&lt;p&gt;Orbital debris in Low Earth Orbit (LEO) is an international problem that threatens the success of all future Low Earth Orbit (LEO) space and exploration activities.&amp;nbsp; Research indicated that removing large debris objects is the best means to reduce the overall hazard from orbital debris, since large debris is the creation engine for smaller, more numerous, fractionation objects. Based on an analysis of alternatives of various remediation methods, this project has implemented a testing environment consistent with the chosen approach, a tug-based method to actively capture and deorbit the debris.&amp;nbsp; However, this type of mission must consider that large debris bodies are derelict and without active controls, hence unable to hold a consistent attitude.&amp;nbsp; Worse yet, they are often tumbling at rates of up to 3 revolutions per minute, a rate dramatically higher than prior rendezvous and proximity operations state-of-the-art.&amp;nbsp;&lt;/p&gt;&lt;p&gt;Therefore, methods to test approach and capture methods, as well as sensor and guidance navigation and control concepts, were needed in order to retire the principle risks with this type of mission.&amp;nbsp; First in three degrees of freedom, and initially at lower rates, the developed testing environment will be used to mature the operational techniques as well as the sensor technologies necessary for this mission to be successful.&amp;nbsp; As maturity is accumulated, relative rates will be increased, and although out of the initial scope of the project, additional degrees of freedom, up to five and six DOF, will later be incorporated.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The approach to developing this tool are the following: to use SysML to model the instrumentation system, to develop a method to seamlessly transfer data from SysML to TEAMS to perform testability/observability analysis, to develop a multi-variate optimization technique to examine testability, observability, mass, and cost optimization, to transfer data from SysML to the optimization tool, and to perform the optimization.&lt;/p&gt;
&lt;p&gt;To date, navigation solutions are created by ground systems teams and then uploaded to vehicles operating beyond Earth orbit. However with the improvement of space-based optical cameras and the increase in computer processing power, it is now possible to develop a technology for on-board navigation state determination. This capability would improve the safety of crew by ensuring valid knowledge of vehicle state between updates from the ground, to support nominal and abort operations. This proposal will investigate on-board optical navigation in three ways: 1) identify algorithms that can be used to analyze video information to determine location of celestial objects, 2) develop a test environment that simulates the visible mission environment, and 3) conduct tests of these algorithms on a flight-like computer, implemented in Core Flight Software (CFS).&lt;/p&gt;
&lt;p&gt;
	The small size and low weight of these battery-free&lt;br /&gt;
	SAW tags enable long-range, long duration remote temperature sensing instruments as well as a relative navigation waypoint network. This project can eventually provide a unique scientific instrument to be flown on multiple robotic probes. Additional exploration technologies will be identified and assessed for their applicability for future surface, small body and planetary exploration (e.g. Naval Research Lab miniature microbial fuel cell, modulating retrroeflector, X-band switchable radio/radar).&lt;br /&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	This project will investigate and adapt aides which will increase the efficiency of ISS robotics ground control operations with the intent of creating more opportunities for ground-controlled robotic operations. The selection and adaption of an aide will initially focus on providing relative position feedback to the operator during close-proximity operations, like grasping a robotic interface for example, since this type of operation is&amp;nbsp; one of the most inefficient from a ground-operator perspective. This is to be a video-based system using Natural Feature Image Recognition (NFIR). The intent is to eventually use the same information to generate commands within the command system. This will benefit ISS operations and provide a testbed for future telerobotic exploration systems that will save time for both the crew and the ground.&lt;/p&gt;
&lt;p&gt;The prototype would be developed in cooperation with the Texas A&amp;amp;M University AggieSat Lab to fit available constraints in size, shape, power, and data interfaces.&amp;nbsp; This effort leverages development and testing from previous and current projects sponsored by the JSC Technology Working Group, including HIMS and DRAGONS.&amp;nbsp; Follow-on work would develop a flight article designed to collect calibrated data on the velocity and size of debris impacts when attached to a small satellite in low Earth orbit.&lt;/p&gt;
&lt;p&gt;This work will establish ultra-clean chemical purification and isotopic analysis of chromium and manganese in sub-milligram-sized astromaterial samples.&amp;nbsp; Manganese-chromium isotopic analysis can be used to determine the age of ancient (&amp;gt;4.5 billion year old) dust and rock fragments, as well as for mapping in space and time the distribution of primordial material in the protoplanetary disk, in particular during the early accretion period of asteroids.&amp;nbsp; This laboratory-based research will be coordinated with our microMill sampling facility and state-of-the art Triton thermal ionization mass spectrometer (TIMS).&amp;nbsp; This work will develop the high precision analysis processes of ultra small samples of the type that will be returned by robotic and, eventually, human exploration missions to asteroids.&amp;nbsp; We will also integrate microMill sampling, chemical purification, and TIMS analysis of small targeted regions of larger samples (e.g., core and/or rims of minerals contained in rocks returned from differentiated asteroids, the Moon, and/or possibly ancient rocks from Mars). At the completion of this multi-year project ARES scientists will have well-developed, calibrated, and fully-documented sets of: (1) low blank micro-dissolution vessels and (2) of micro-columns to efficiently purify Mn and Cr from future small returned samples, as well as an ultra-clean workspace to conduct these experiments.&amp;nbsp; In short, we propose to have all sample procedures and laboratory spaces prepared and tested prior to any future Mission-related sample allocation.&amp;nbsp; This work will strongly enhance the quality of science results obtained from the tiny particles expected to be returned by robotic, and eventually human, exploration missions.&lt;/p&gt;
&lt;p&gt;We propose to test a prototype water vapor sampling end-effector in the laboratory and in the field that&lt;br /&gt;will eventually be integrated with a small, infrared spectrometer developed through SBIR phase II funding for lunar, asteroid, or Martian exploration. The analyzer is capable of in-situ analysis of water- bearing materials on a millimeter scale providing high precision measurements of water abundance and isotopic composition. The high precision isotopic analysis will include D/H, 17O/16O, and 18O/16O. Water is central to NASA&amp;rsquo;s strategic goals for exploration of the solar system and high precision isotopic analysis, especially of 17O, provides a key tool in answering fundamental scientific questions about its origin and history. In addition, these measurements can serve as an important component of ISRU operations helping to identify, characterize, understand, and predict the occurrence of volatile deposits.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Recent findings indicate that frequent, short-term crew exposure to elevated CO2 levels combined with other physiological impacts of microgravity may lead to a number of detrimental effects, including loss of vision. To evaluate the risks associated with transient elevated CO2 levels and design effective countermeasures, doctors must have access to frequent CO2 measurements in the immediate vicinity of individual crew members along with simultaneous measurements of their location in the space environment.&amp;nbsp; To achieve this goal, a small, low-power, wearable system that integrates an accurate CO&lt;sub&gt;2&lt;/sub&gt; sensor with an ultra-wideband (UWB) radio capable of real-time location estimation and data communication is proposed.&amp;nbsp; This system would be worn by crew members and would automatically gather and transmit&amp;nbsp; sampled sensor data tagged with real-time, high-resolution location information.&amp;nbsp; Under the current proposed effort, a breadboard prototype of such a system will be developed.&amp;nbsp; Although the initial effort is targeted to CO&lt;sub&gt;2&lt;/sub&gt; monitoring, the concept is applicable to other types of sensors.&amp;nbsp; For the initial effort, existing EV Modular Instrumentation System (MIS) Wireless Sensor Network (WSN) hardware will be leveraged to integrate a low-power CO&lt;sub&gt;2&lt;/sub&gt; sensor with a commercially available UWB radio system with ranging capability.&amp;nbsp; In addition, potential for integration of this system with EV&amp;rsquo;s Electronic-textile System for the Evaluation of Wearable Technology (E-SEWT) will be evaluated.&lt;/p&gt;
&lt;p&gt;This is a planned three-year project to develop&amp;nbsp; extraterrestrial sample curation techniques and equipment to prepare for future human and robotic sample return missions to Mars, the Moon, asteroids, and comets as well as to improve techniques and equipment used in current curation operations.&amp;nbsp; The project focuses on sample curation with a high degree of organic cleanliness.&amp;nbsp; Specifically, during year 1 we developed a detailed understanding of historical organic contamination in the JSC Astromaterials Curation laboratories.&amp;nbsp; In year 2 we are monitoring current organic cleanliness and assessing cleaning techniques in the laboratories and a dedicated testbed.&amp;nbsp; In year 3 we plan to use the testbed to demonstrate methods and technology to reduce organic contamination in these laboratories.&lt;/p&gt;
&lt;p&gt;In FY12, this project removed the commercial-specific content from the Commercial Human-Systems Integration Design Processes (CHSIP), identified gaps in the documented design processes, and generated 5 new process chapters. The new chapters were based on human spaceflight (HSF) program needs and covered a large breadth of topics, from Legibility Evaluation to Design for Decompression Sickness Mitigation. In FY13, the approach is to conduct a Human Health and Performance (HH&amp;amp;P) review of the HSIP, and baseline the content for knowledge capture of HH&amp;amp;P processes and lessons learned, for training of new employees, and for use by current and future HSF programs.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The goal of this project is development of a passive radio-frequency identification (RFID) communication module, compliant with the EPC global class1, generation 2 air-interface standard, that can be interfaced easily with arbitrary sensors via the EV Modular Instrumentation System (MIS) hardware. Since RFID communication operates entirely using power transmitted from an RFID interrogator, this will give MIS the capability to transmit sensor data &amp;ldquo;for free&amp;rdquo;. Hence, the MIS power supply will be responsible only for data acquisition, which will substantially increase the lifetime of a battery-powered MIS node. For sufficiently low power sensors, it may be possible to power both communication and sensing using RF energy harvested from the interrogator (or through the addition of a second harvested source, such as solar). The RFID tags developed under this effort can be interrogated by any EPC global-compliant reader, such as the hand-held readers on ISS or future robotic free-flyers equipped with standard readers. Exploration vehicle structural monitoring (strain, vibration, etc.) and environmental monitoring (CO2, O2, etc.) are targeted as initial applications. The long-term goal is a small, completely passive RFID module with a plug-and-play, delay-tolerant network (DTN)-like sensor interface.&lt;/p&gt;&lt;p&gt;The major goals accomplished under this project are:&lt;/p&gt;&lt;p&gt;&amp;bull;A prototype open-source RFID communication module was designed, fabricated, and successfully tested by a senior design group at Rice University.&lt;/p&gt;&lt;p&gt;&amp;bull;A COTS device with the desired functionality was identified, acquired, tested, and successfully interfaced with MIS hardware at JSC.&lt;/p&gt;
&lt;p&gt;
	All aspects of nutrition are critical for crew health and optimal performance. Maintaining body, muscle, and bone mass are key challenges for astronauts, as are protecting against oxidative damage and cardiovascular deterioration. Dietary intake is a primary countermeasure for maintaining crew health. Currently, to monitor intake, crews complete a weekly Food Frequency Questionnaire (FFQ), in which they provide their best estimate of food items consumed each week. The FFQ is designed such that food items are grouped into 60-70 lines, and an algorithm is used to calculate average daily intake of 7 key nutrients (fluid, energy, protein, calcium, iron, sodium, potassium).&amp;nbsp; This grouping strategy allows crewmembers to complete the survey in 15 min/week.&amp;nbsp; This method works very well for some crewmembers, but not for others. The ISS Food Intake Tracker iPad app is intended to provide a viable, easier alternative.&lt;/p&gt;
&lt;p&gt;The FMEA Assistant guides the analyst through a set of questions about component attributes, including subsystem type, kinds of resources used, and types of outputs.&amp;nbsp; The chosen attributes narrow down the number of possible choices of failure modes that make sense for that component. &amp;nbsp;&amp;nbsp;The analyst need only consider a few small sets from the full list of common failure modes to&amp;nbsp;find the appropriate ones.&amp;nbsp; The dialog is dynamic, so that the choices of failure modes presented change if the analyst changes the attribute selections. The tool also has extended the use of standardization by offering short lists of common failure causes and effects for each failure mode.&amp;nbsp;&amp;nbsp; Two new features have recently been added: support for choosing hazards associated with identified failure modes and effects, and a library of standard components (e.g., valve, gauge, latch) with pre-selected failure modes.&amp;nbsp;&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;A successful proof of concept was performed in FY 2012 integrating the Envision tool for parametric estimates of vehicle mass and the Rapid Response Risk Assessment (R3A) tool for probabilistic risk analysis of vehicle systems. The initial work implemented the capability to assess a number of spacecraft systems, including Environmental Control and Life Support System (ECLSS), propulsion, and others; and demonstrated the integrated operation of the tools with the ability to quickly assess the impacts of system trade option selections.&lt;/p&gt;&lt;p&gt;Work remains to implement a complete vehicle architecture capability by adding and addressing the trade space of major systems and to develop a capability ready for use by envisioned NASA and JSC projects and organizations such as the Human Spaceflight Architecture Team (HAT).&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;MMOD toughened, smart thermal blankets&lt;/strong&gt;. The project was successful over the past two years in developing and demonstrating by test (hypervelocity impact and thermal vacuum tests) an MMOD toughened, smart thermal blanket concept that is adaptable to different levels of MMOD threat and/or reliability levels. This blanket includes integrated impact sensor technology to determine the location and extent of MMOD impact damage. &lt;strong&gt;Combined MMOD/radiation protection shields&lt;/strong&gt;. The project also has made considerable progress in developing improved MMOD and radiation shields that have so far shown better MMOD performance than the best ISS MMOD shields, while decreasing radiation dosage by 30&#37; from solar proton events (SPE). &lt;strong&gt;Self-sealing materials in MMOD protection&lt;/strong&gt;. In FY13, impact tests on alternative shielding concepts will be performed that incorporate self-sealing materials able to close or reduce the size of holes in pressure shells. Tests to-date indicate that combinations of ionomer polymers and reinforcing materials are successful at closing 0.25&amp;rdquo; diameter holes in aluminum pressure shells under 0.3 atmosphere delta-pressure. Additional impact tests using these and other materials (thermoplastic and elastomeric polymers) are planned in FY13 for up to 1 atmosphere delta-pressure.&lt;/p&gt;
&lt;p&gt;Hypervelocity testing of high and low density foam has been performed to bound the MM/OD shielding capability with our aluminum alloy.&amp;nbsp; Additionally,&amp;nbsp; mechanical testing at both densities has been performed&amp;nbsp; to understand the synergism of a focused, system designed structure.&amp;nbsp; Analytical models for structural and environmental response are being developed and correlated to test data.&amp;nbsp; As a result, an intermediate sandwich core density has been selected for further testing.&amp;nbsp; This resultant structure is being built into prototypes at component and full scale levels. The next phase includes maturing the mechanical testing of the selected metallic foam density (including physical modeling),&amp;nbsp; manufacturing formed multifunctional composite structural components into a Generation 3A MMSEV, and maturing the mathematical model to address the structural effect of an impermeability bladder embedded into the core.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Our DNA/RNA isolation and preparation device is a fluidic system with components including syringes and pistons, membranes of different capacities, reagents, valves, and a small pump. In Year 1 of the project, we constructed several self-enclosed prototypes for sample preparation, and demonstrated that the quality of the DNA/RNA samples isolated using our device is similar following the standard laboratory procedures. Year 2 of the project is devoted to the development of an automated system that can process multiple samples simultaneously. The project will be completed in Year 3 with the development of the software that controls the movement of the syringe plungers in a programmed manner for processing different biological samples.&lt;/p&gt;
&lt;p&gt;
	The ability to monitor microbial contamination remains a critical technique in the mitigation of risk to crew health and vehicle systems during human spaceflight missions. Current methods of bacterial and fungal monitoring on the International Space Station (ISS) depend on culturing of microorganisms during spaceflight and subsequent ground-based identification. This approach requires substantial crew time, uses consumables with short shelf lives, and prevents a rapid response to microbial contamination. To address these limitations for future missions beyond low-Earth orbit, a biosensor using gold nanoparticles is being developed for the rapid detection of medically significant microorganisms. For proof-of-concept, we have targeted the detection of Staphylococcus aureus, a common infectious agent that has been repeatedly isolated aboard the ISS. Gold nanoparticles were modified by the covalent attachment of an antibody that has a high binding affinity for a protein on the cell wall of S. aureus. Upon interaction with a sample containing S. aureus, binding between the nanoparticles and the bacteria occurred rapidly. A significant reduction in the red coloration of the colloidal nanoparticle suspension, and the formation of a large purple pellet was observed following a brief centrifugation step. Comparison of the absorbance spectra verified the visual observation, demonstrating that there was a significant reduction in the absorbance of the supernatants of reaction samples in which S. aureus was present. This biosensing system provides a rapid means to specifically detect only the targeted organism. Further development will potentially lead to a small, lightweight biosensor that can be easily adapted to detect other selected microorganisms in real-time, providing crews of future spaceflight missions a simple method to autonomously define potential infectious disease risks.&lt;/p&gt;
&lt;p&gt;In FY&amp;rsquo;13 we expanded our analysis of samples to include astromaterials and biological materials relevant to international space station (ISS) and human space flight (HSF). We are also in the process of integrating our existing UV laser photoionization source with the new VUV source to enable both to be operated simultaneously. By combining VUV photons with UV/Visible photons we can explore the use of novel two-photon (118.2 nm + 1064/532/355/266 nm) resonant and non-resonant ionization schemes. By timing the photons from both sources to arrive simultaneously in the ionization region of the ultra-L2MS instrument we can further the expanding of the range of detectable molecular species. Additionally by allowing a controlled delay between the arrival of photons from the two sources (time-delayed two-photon ionization) it may also be possible to provide structural information for certain molecular species that could not be provided by conventional mass spectrometry techniques.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;This proposal will complete testing of existing straight channel test articles with enhanced instrumentation.&amp;nbsp; Analytical work will focus on upgrades to the in-house modeling tool Regeneratively-Cooled Combustor Equilibrium Tool (RCCET-M) to allow modeling of 2-D heat transfer and dynamic boiling instability.&lt;/p&gt;
&lt;p&gt;This proposed technology uses nitrogen or helium gas and water to prevent structural damage that could lead to loss of vehicle and loss of crew caused by high temperature plasma ingestion through an MMOD impacted damage in the TPS.&amp;nbsp; This results in &amp;ldquo;enhanced safety and probability of mission success for Entry, Descent, and Landing (EDL) phases of atmospheric flight.&amp;rdquo;&lt;br /&gt;This technology uses heat flux, temperature, and pressure sensors from the Fault Detection Isolation and Recovery (FDIR) system to detect high temperature plasma ingestion. Thus, this system integrates gaseous nitrogen and water from the Environment Control and Life Support System (ECLSS) and the sensors from FDIR systems to automatically activate when necessary to mitigate the potential catastrophic hazard.&lt;/p&gt;
&lt;p&gt;A predictive tool with tight coupling of the fluid and thermal physics will give insights into the conservatism of the uncoupled design process and could lead to margin reduction and consequently reduced heat shield mass. This project seeks to couple the CHarring Ablator Response (CHAR) code and the Fully Implicit Navier-Stokes (FIN-S) code with finite-rate models governing the gas-surface interactions and surface mass loss.&amp;nbsp; Loose coupling has already been demonstrated between the codes for non-ablating materials, which helped identify and solve potential computer science and physical modeling issues. Additionally, the development team has already shown an ability to implement a multi-physics simulation framework as they have recently coupled thermal and structural physics modules within the CHAR code. The bulk of the work focuses on modeling the energy flux terms at the gas-surface interface. The current design approach requires gross assumptions or even neglecting terms in either the CFD or AMR analyses.&lt;/p&gt;&lt;p&gt;Progress to date has included the integration of the software components into one executable that facilitates information exchange between the fluid and ablation physics.&amp;nbsp; The software has been demonstrated on both two and three dimensional ablation problems.&amp;nbsp; On going efforts include verification and validation of the new multi-physics software tool.&lt;/p&gt;
&lt;p&gt;This project has developed a set of tactile display garments that will be used to evaluate various tactile display methodologies. The garments include two sleeves and a belt that are designed for easy don/doff to facilitate research with multiple users. Fifteen small vibrating motors are integrated into the garments and are controlled wirelessly via a custom desktop control interface.&lt;/p&gt;
&lt;p&gt;This project investigates the effectiveness of using an avatar robotic platform as a crew assistant and a family member substitute. This type of avatar robot is particularly useful for maintaining crew behavioral health during long-term crew isolation. An avatar robot is both a physical and graphical representation of a person at a remote location and acts as a surrogate for that person.&amp;nbsp; The teleoperated avatar robot can interact with its environment on behalf of the person not present, thus providing physical and psychological assistance to others. The robot offers real-time motion control as well as speech and video communication with the people and environment at the remote site.&amp;nbsp; It can be equipped with remotely controlled manipulator arms to carry out tasks.&lt;/p&gt;&lt;p&gt;Such a platform can be deployed on the ISS and other future near-Earth habitats, enabling the ground crew to assist the onboard crew on tasks. For facilitating crew behavioral health, the robot can be controlled by, for example, a crew family member and thus can act as a surrogate for the family member.&amp;nbsp; Similiarly, the crew can also control the robot at his/her home to provide closer interactions with his/her family members.&lt;/p&gt;&lt;p&gt;Currently, the impact of such a system to the crew&amp;rsquo;s behavioral health is unknown.&amp;nbsp; The proposal avatar robot platform can also be used to develop an ideal human/robot control/command interface; effectively controlling/commanding such a robot with multi-modal parallel outputs still requires much research. We will develop an avatar robot platform and perform preliminary evaluations to assess its potential benefits as a remote human surrogate for space-related applications.&lt;/p&gt;
&lt;p&gt;Natural User Interface (NUI) is a term used to describe a number of technologies such as speech recognition, multi-touch, and kinetic interfaces. Gesture and voice control are two exciting computer input modalities for the NUI. Some believe that NUI is the next step forward from the traditional graphical user interface (GUI), which employs a mouse and keyboard as the primary means of input. The goal of NUI is to develop interfaces that do not have a steep learning curve and the interactions with these interfaces are &amp;ldquo;natural&amp;rdquo; and intuitive to the user.&lt;/p&gt;&lt;p&gt;One disadvantage of current GUIs is that they require the users to be physically near an input device in order to interact with the system. With the NUI, however, through using voice and gesture commands, the user is able to interact with the system &lt;em&gt;anywhere&lt;/em&gt; they want within the defined work environment. Such &amp;ldquo;Interface Anywhere&amp;rdquo; gesture ability is achievable using infrared technology. The voice recognition portion is achievable through array microphones and Kinect software. Our NUI system of choice for this proof of concept is the Microsoft Kinect sensor. The heart of the system and what makes gesture recognition possible is the Kinect&amp;rsquo;s skeleton tracking ability. The Kinect contains an infrared projector and receiver, a normal RGB camera, and an array of four microphones. The system tracks multiple users in x-, y-, and z-space. Based on the depth information, the Kinect generates a skeleton using joint position.&lt;/p&gt;
&lt;p&gt;a)&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp; Portable digital devices such as the iPad provide lightweight, powerful, and convenient methods of communication, and there are countless potential applications for use of these personal devices in spaceflight environments.&amp;nbsp; However, many of these devices utilize capacitive touchscreens that do not work well with existing suit architecture, limiting their potential use by crew when suited and gloved in intra-vehicular activity (IVA) scenarios, such as during launch, ascent, entry, and docking scenarios.&amp;nbsp; However, there are commercially available gloves for driving and recreation that incorporate capacitive capability to allow their use with capacitive touchscreens.&amp;nbsp; Our goal with this ICA is to create a basic launch/entry/ascent suit glove prototype (based on an ACES or similar suit glove) that is functional with portable touch-screen devices such as the iPad, leveraging the concepts included in the commercial off the shelf (COTS) glove hardware.&amp;nbsp; Our prototype glove will then be run through a simple user test to evaluate its functionality and usability.&lt;/p&gt;
&lt;p&gt;In spite of our best efforts to minimize the amount of disposable supplies (and the associated packaging) used during space missions, the accumulation of solid wastes is an inevitable consequence of mission activity. That waste will occupy precious cargo or living space within the habitat unless it is properly managed. Converting solid wastes to an energy source presents a potential solution to this problem.&lt;/p&gt;
&lt;p&gt;Regenerative fuel cell systems often include a dedicated electrolysis module with solar photovoltaic (PV) panels packaged as a subsystem of the larger energy storage system.&amp;nbsp; The voltage-current (V-I) performance curves associated with the system modules must be compatible&amp;ndash; this often necessitates the use of complex electronic power control elements (DC-DC converters, DC-AC inverters, etc.).&amp;nbsp; This proposal will investigate a power-following integration option for solar PV modules into DC base-power systems for dedicated electrolysis module operations without the need for DC power interface elements.&lt;/p&gt;
&lt;p&gt;The intent of this particular project was&amp;nbsp;to perform the following:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Provide a breathing capability to be integrated into existing EC5 Ventilation Lab Suited Manikin Test Apparatus (SMTA).&amp;nbsp;&lt;/li&gt;&lt;li&gt;Evaluate flow controllers and ancillary equipment needed to provide breathing function including proper CO&lt;sub&gt;2&lt;/sub&gt; and humidity levels varying appropriately with simulated metabolic rate profiles.&lt;/li&gt;&lt;li&gt;The SMTA will be upgraded to include the fully capable breathing apparatus components that will be sufficient to simulate human breathing providing the capability to rapidly explore the range of human metabolic activity expected during Extravehicular Activity (EVA).&amp;nbsp;&amp;nbsp;&amp;nbsp;&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;Testing performed with the SMTA will benefit development efforts including Advanced Exploration Systems (AES) Advanced Extravehicular Mobility Unit (AEMU) Helmet and Portable Life Support System (PLSS) development and Space Technology Mission Directorate Rapid Cycling Amine development.&amp;nbsp;&lt;/p&gt;&lt;p&gt;Future upgrades to the SMTA could include the capability to include various helmet designs, human head geometries and positions, and ventilation inlet configurations.&amp;nbsp; Moreover, the test apparatus will be directly applicable to validating future suit air revitalization hardware and flow components as new technologies become available.&lt;/p&gt;
&lt;p&gt;
	Spacesuit mobility has been historically difficult to define and therefore, difficult to write requirements for.&amp;nbsp; Most previous efforts have concentrated on establishing metrics for isolated joints &amp;ndash; often multiple movements for each joint &amp;ndash; and characterizing the range of motion of that joint &amp;ndash; as well as the corresponding joint torque through said range of motion.&amp;nbsp; However, there have been multiple issues with this approach:&amp;nbsp; First, it has been shown through multiple tests at JSC that joint torque data lacks repeatability, even with the same test setup and subject; Second, a suit can often meet defined mobility requirements yet exhibit lackluster or anomalous mobility behavior (or vice versa); Third, defining mobility at the isolated joint level does not capture the mobility of the comprehensive suit system in real application, with multiple joints often working in harmony or in discord.&amp;nbsp; Lastly, there lacks a standardized testing protocol with which JSC and suit contractors can assess suited mobility in a repeatable and predictable manner.&amp;nbsp; The proposal contained herein aims to mitigate all of these problems through investigating a new method of suited mobility characterization: by measuring the relative metabolic cost associated with performing a series of functional tasks as compared to performing those same tasks in a shirtsleeve environment.&lt;/p&gt;
&lt;p&gt;
	On a previous ICA, a test correlated excel based software tool was developed using the innovative Stress?Energy method to better model impact attenuation using foam. This pioneering tool was used to design packaging foam for impact attenuation of ISS flight hardware during ground shipment and of sensitive avionics in Orion parachute landing tests.&amp;nbsp; The Orion project has reported no avionic damage during drop tests since the implementation of foam attenuation. This tool was limited to modeling flat foam pieces of uniform section with hardware center of gravity (CG) centered over the foam. However, the hardware being protected were not necessarily flat and many assumptions need to be made that affect accuracy of the &amp;lsquo;G&amp;rsquo; load and foam compression estimations.&lt;/p&gt;
&lt;p&gt;
	Foams may be modeled using a commercial nonlinear finite element codes available at JSC such as MSC/Marc. It is proposed that results from the extensive testing done to develop the aforementioned ICA funded excel tool, now be used to develop accurate MSC/Marc material models and establish a methodology to convert test results into material models. This will enable the rapid design of foam configurations cut to match the irregular shaped hardware to be protected. Foam may be cut in pyramidical shapes to provide flexibility in designing load reduction curves to match hardware attenuation needs. Foam sandwiches may also be designed containing layers of different foam types. Attenuating Mars/Earth landing impact loads are considered critical for mission success and this technology will considerably reduce risk.&lt;/p&gt;
&lt;p&gt;The need for reliable, high capacity, radiation tolerant nonvolatile memory exists in many Human space flight applications. Most projects rely on COTS hardware for a data storage system with very little assurance of radiation performance. The goal of this idea is to develop a high capacity nonvolatile memory system that is radiation tolerant. The concept uses commercially available nand-flash devices that are built with certain radiation immunity. To enhance radiation performance this concept incorporates error detection and correction. The concept is based on technology already explored by the Advanced Space Suit project. The purpose is to complete the work already started by the Advanced Space Suit project using available components. The first phase will prototype a design of the nand-flash memory array board interfaced to the error detection and correction algorithm implemented on an FPGA development board. Radiation testing will be performed by the JSC EV-5 radiation group.&lt;/p&gt;
&lt;p&gt;Resistive crew exercise equipment for Orion and other exploration spacecraft will be severely impacted by space constraints in both storage and use. Development of a compact, high variable torque rotary damper will facilitate the design of exercise equipment.&amp;nbsp; Rotary motion is the most direct when applied to human joints, such as knees, elbows, hips and ankles. On a prior ICA funded project, linear magneto-rheologic dampers were used on an exercise device. Converting joint rotary motion into linear motion on the damper required additional mechanisms with weight penalties. Once this compact rotary MR damper is developed, it may be integrated with the Orion Crew Seat to be used as a resistive exercise device as well as a launch/landing load damper.&amp;nbsp;&amp;nbsp; This also allows the seat to have dual use as a seat for launch/landing and as an exercise device.&lt;/p&gt;
&lt;p&gt;Two-phase heat rejection offers vast potential in reducing the thermal control footprint of vehicles and equipment in terms of mass, volume, and parasitic power loss. This potential follows from the latent heat associated with phase change: in order to remove the same heat as a single phase water loop having a 20C temperature rise, a two-phase loop needs only 5&#37; the flow rate, and consequently 3 orders of magnitude lesser pumping power, while simultaneously providing a constant heat rejection temperature.&lt;br /&gt;A key issue in consideration of two-phase, however, is predicting behavior in partial and micro-gravity environments. Recent research indicates that the performance of forced boiling in constrained channels, e.g. micro-channels or micro- heat exchangers, is not affected by the presence or lack of gravity. This is a consequence of a characteristic length scale small enough that surface tension forces dominate flow behavior rather than buoyancy forces which dominate at conventional scales. This project proposes to demonstrate a pumped two-phase cooling loop, e.g. one that collects heat from heat sources through forced micro-channel boiling, mitigating unknowns of microgravity boiling, and does not employ a compressed vapor phase.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Spacecraft designed for missions beyond low earth orbit (LEO) face a difficult thermal control challenge: they are required to reject a high heat load to warm orbital environments and a low heat load to cold transit environments, necessitating a quite high turn-down ratio. This difficult challenge can be transformed into a tractable design problem for arbitrarily high turn-down ratios through the use of shape memory alloys, materials that exhibit a temperature dependent phase change such that they can be easily deformed below the transition and recover a predefined shape above the transition. In fact, shape memory alloys can be trained to behave in a two-way manner so that it takes one shape above and another below the transition temperature. Such materials make possible a passively deployed heat rejection device which adjusts vehicle and environment loads based on its operating temperature alone. This project seeks to train a shape memory material and evaluate its behavior.&lt;/p&gt;
&lt;p&gt;
	This project trained a shape memory material to behave in a two-way manner and evaluated the capability of the two-way shape memory effect. A literature review identified an optimum training method involving alternating constrained and unconstrained thermal cycles. The effect of two bending strain rates were investigated through training rigs of differing radii, both trained in parallel. It was identified that in both cases cold working of the material results in some deformation to the austinite shape. This cold work deformation can be addressed through careful design of the hot set shape of the material.The results indicate that the greatest delta between austinite and martensite shapes is obtained through the lesser training strain (large radius rig). Projection of the results of two-way training of the material indicate that sufficient deformation can be trained to successfully employ in a full sized heat rejection device.&lt;/p&gt;
&lt;p&gt;Project will procure available graphite foam products in small quantities, perform testing, and build simple prototype designs. Several specific applications have been identified in thermal management systems, energy storage, and multifunctional structures that will require continued collaborative engineering between divisions to develop.&amp;nbsp; Working groups are being established to pursue small efforts in each area.&amp;nbsp; Materials processing on as-received foams to enable engineering designs as well as techniques to produce foams with specific desirable properties are being studied.&lt;/p&gt;
&lt;p&gt;NASA&amp;rsquo;s mission operations concept has evolved over the past half century but it relies on extensive ground support for both nominal and off-nominal operations. Next-gen missions will require decreased Earth-based support due to the increased communication time lag. NASA&amp;rsquo;s vision of manned spaceflight into deep space cannot be realized by projecting the current mission ops concept forward. A &amp;ldquo;Siri-like&amp;rdquo; crew assistant will provide support when/where/as needed, understand the Crew communication protocols, have access and knowledge about the crew timeline and procedures, enable the crew to get just-in-time training refreshers, be capable of communicating with spacecraft systems, get the telemetry of interest to understand the current status and upcoming tasks that the astronaut is involved in, and be the communication hub between the astronaut and the ground during specific missions phases.&amp;nbsp;&lt;/p&gt;&lt;p&gt;The objective of this project is to capture in a report an assessment of the possibility to adapt Siri-like technology to crew support, and to develop a limited prototype of the concept.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Utilizing resin infusion to rigidize an inflatable structure and form fiber-reinforced composites on-orbit is a novel concept that builds on current NASA technology in expandable structures.&amp;nbsp; The current effort to design and build a prototype has sucessfully demonstrated a proof of concept that the technology is viable using current state-of-the art materials and manufacturing techniques.&amp;nbsp; A cylinder shaped object with round end caps was manufactured as a simple article, but domed shapes are possible and expected to be the most efficient although more complex to design and build.&amp;nbsp; A braided carbon fiber fabric material of two ply thickness was utilized in the prototype to provide a thin and optimally reinforced structure.&amp;nbsp; The fabric was contained on two sides with laminated sheet polymer to form a vacuum bag attached at both end caps. Vacuum ports and resin fill ports were located at opposite ends and routed to the fabric cavity between the two polymer sheets.&amp;nbsp; The cavity was evacuated and filled with resin that cured to form a rigid composite structure cylinder.&amp;nbsp; It is planned to perform a pressure test of the cylinder and produce a preliminary design of a larger dome-ended structure for proposed future work. A conceptual design for the mechanical system required to provide the internal pressure, vacuum resin trap, and resin mixing and filling will also be presented.&lt;/p&gt;
&lt;p&gt;Inflatable structures will require low permeable bladder to metallic seal interface.&amp;nbsp; Cold flow of bladder materials over time is not acceptable for long term missions where materials cannot be easily inspected or replaced.&amp;nbsp; Reliable seal interfaces are required.&lt;br /&gt;&amp;nbsp;Inflatable habitats can provide the volume necessary for space colonization at a lower cost than traditional habitats. Sealing bladder materials capable of deploying at cold temperatures is essential for deep space missions and likely LOE missions due to operational constraints&lt;/p&gt;
&lt;p&gt;The work focused on testing the Li-ion supercapacitors to confirm their performance and safety.&amp;nbsp; The li-ion supercaps were found to be safe under several off-nominal conditions such as overcharge, overdischarge into reversal, external short and simulated internal short.&amp;nbsp; The li-ion supercaps were found to hold charge for the three month period tested and showed insignificant loss in capacity after that hold period.&amp;nbsp; The li-ion supercaps were found to have the capability to accept charge quickly from a power supply.&amp;nbsp; The testing to provide controlled current from the supercapacitors to the battery was not completed due to lack of personnel to carry out the testing.&amp;nbsp; With the help of an intern this Fall, that work will be completed.&lt;/p&gt;
&lt;p&gt;Goals of the DSH Testbed include:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Function as a habitat systems integrator and technology pull across many domains&lt;/li&gt;&lt;li&gt;Develop and integrate software-based models of habitat systems with system to system interdependencies&lt;/li&gt;&lt;li&gt;Enable maturation of select habitat systems&lt;/li&gt;&lt;li&gt;Integration of physical hardware where available&lt;/li&gt;&lt;li&gt;Distributed testing to link to other facilities&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;The DSH Testbed provides a place to build the instance of the DSH vehicle, and as a result provide integration testing of habitat subsystems and technologies in a vehicle-like context.&amp;nbsp; Some of these technologies include:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;WSN&lt;/li&gt;&lt;li&gt;Power&lt;/li&gt;&lt;li&gt;Avionics&lt;/li&gt;&lt;li&gt;Software&lt;/li&gt;&lt;li&gt;Impact Detection&lt;/li&gt;&lt;li&gt;Comm&lt;/li&gt;&lt;li&gt;Crew Systems (Displays, TRWS, programmable lighting)&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;Testing in an incremental fashion, subsystems can be added on to the core architecture, modularly removed and replaced, and finally matured.&amp;nbsp; Subsystems also do not have to be physically present in order to be included in the testbed.&amp;nbsp; The DSH Testbed is able to perform a combination of local and distributed connectivity to hardware and software to complete vehicle integration.&amp;nbsp; Finally, subsystems can be varying maturity levels, and even exist as simulations.&amp;nbsp; The DSH Testbed is able to host subsystem models and simulations and stress them in the integrated habitat context.&lt;/p&gt;
&lt;p&gt;
	This project aims to leverage near-term high-temperature superconducting technologies to assess applicability of magnetic shielding for protecting against exposure from Solar Proton Events (SPEs) and dose reduction for Galactic Cosmic Radiation (GCR) utilizing HTS magnet technology concepts. Shield design can have substantially lower mass/power requirements than previously thought. Modeling efforts will include: (1) Modeling of realistic magnetic fields (Halbach array) utilizing full-scale finite-element methods that include fringing fields; (2) leveraging of recent plasma trapping results (Rutherford/Appleton Laboratory); (3) and if time permits, a habitat model will be included as parasitic shielding. Testing will be conducted with a magnet array for plasma trapping facilitated at Ad Astra utilizing current Space Act Agreements. The study will evaluate shorter duration missions from a power, mass, flux reduction perspective and provide an active and passive shielding mass comparison.&lt;/p&gt;
&lt;p&gt;Phased array ultrasonic testing (PAUT) instruments and array eddy current testing instruments were tested on hypervelocity impact damaged aluminum plates simulating the ISS pressure wall. Ultrasonic techniques were most successful in assessing the back side damage when a&amp;nbsp;repair seal plate covers the damage. The ultrasonic instrument would be selected for implementation on ISS.&lt;/p&gt;
&lt;p&gt;
	Telepresence sessions between the crew, family members and medical doctors require visual and acoustic privacy.&amp;nbsp; This environment is best achieved in the individual crew quarters.&amp;nbsp; A prototype crew quarters was developed and built that would provide both privacy and a safe haven from which to conduct operational activities during solar radiation events.&amp;nbsp;&amp;nbsp; High school and college intern students participated in the design and construction of the crew quarters.&amp;nbsp; 3D video displays and multi-dimension audio systems were evaluated to attempt to achieve a realistic recreation of Earth events.&amp;nbsp; Indirect Light Emitting Diode (LED) lighting was installed to simulate a 24-hour circadian rhythm cycle.&lt;/p&gt;
&lt;p&gt;
	A technology with game-changing potential for crew to space system interaction will be selected to develop using the HSI Methodology created through the efforts of the HSI Methodology JSC IR&amp;amp;D FTE allocation,&amp;nbsp; HSI WG (Working Group), and HSI ERG (Employee Resource Group). The integrated Power, Avionics and Software (iPAS) Flight Deck of the Future (F.F) Testbed core capability will be completed through this project&amp;nbsp; and used for testing. Through iterative Human in the Loop (HITL) testing and demonstration of the technology, using the proposed HSI methodology, the team will validate the methodology. The F.F testbed, in JSC Building 29, Lab 233, will provide core testing systems, including partial space-system mockups, test consoles, and data collection systems.&amp;nbsp; Collaboration with a variety of key disciplines will provide the expertise needed to plan and execute the HITL test.&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Implement in FCT avionics and attitude control architecture and software that enables order of magnitude increase in control capability for next-generation formation flying technology demonstrations; Demonstrate full 6DOF control in the FCT for the first time; Demonstrate Proba-3 formation flying sensors and software that achieves 2 orders of magnitude higher performance than demonstrated capability.&lt;/p&gt;
&lt;p&gt;Evaluate Current State of the Art; Define Critical Performance Requirements; Select Components; Smart Initiator or Smart Connector; Perform Detailed Cost/Benefit Analysis; Develop System Architecture; Build Prototype System; Qualify Prototype System to TRL 6; Develop Full Qualification Plan for implementation on JPL Flight Project.&lt;/p&gt;
&lt;p&gt;Develop control and planning algorithms for a science-driven spacecraft/rover hybrid, such that the rover is able to autonomously reach designated targets and point instruments traverse performance meets science objectives of 20-30&#37; of traverse distance.&lt;/p&gt;
&lt;p&gt;Perform trade studies over folded aperture optics to specify design parameters - diameter, effective aperture, sensitivity, field of view; Model, design, fabricate and test folded optics to demonstrate sufficient image quality for detecting stars; Identify components - imager and processor platform to obtain system level parameters (weight, volume, power, cost); Night sky test of folded optic to demonstrate star visibility.&lt;/p&gt;
&lt;p&gt;To demonstrate (benchtop experiment) a DPSK receiver with a free-space interferometer, showing that fiber-optic coupling, associated adaptive optics, and optical preamplification can be avoided, with potential large cost savings; To rigorously quantify the performance (capacity and photon-budget) tradeoff between conventional (adaptive optics + optical preamplification) systems and our proposed free-space photon-counting-array approach; To develop extensions to orthogonal phase-modulated signaling over multiple symbols and associated photon-counting receiver structures, which enable approaching the photon efficiency of high-order pulse position modulation.&lt;/p&gt;
&lt;p&gt;Demonstrate micro clock based on trapped Hg ions with more than 10x size reduction and power; Fractional frequency stability at parts per 1014 level, adequate for all deep space 1-way navigation.&lt;/p&gt;
&lt;p&gt;Develop and demonstrate a software architecture, initially based on GPU&amp;rsquo;s but expandable to multiple CPU platforms, to provide optical raytraces with more than 232 independent rays (current capability is 224).&lt;br /&gt;The new software architecture will use GPU programming techniques developed for the Palomar P3K adaptive optics system (world-record holder for number of actuators and speed).&lt;br /&gt;Systems like TMT, CCAT, ATLAST will require this large number of rays to accurately model and verify their system performance&lt;br /&gt;A demonstration connecting existing single-threaded tools (MACOS) to SIERRA has been done by Lee Peterson and Scott Basinger and proven to be a powerful new tool for truly integrated modeling.&lt;/p&gt;
&lt;p&gt;Provide fast, new capability for Loose SmallSat Constellation with solar sail and impulsive propulsion to nonlinear heliocentric orbits, high inclination, low energy transfer (see tubes). These include orbits around L3, 4, 5, NEO rendezvous (e.g. Earth Trojans), capture, sample return &amp;amp; for space weather monitoring.&lt;/p&gt;
&lt;p&gt;Provide discharge chamber and grid modeling for the new T6 based on JPL expertise on ion thruster performance and life; Enable/guide the T6 upgrade development to satisfy NASA life requirements.&lt;/p&gt;
&lt;p&gt;Develop ultra-low-power, wide-temperature (-150&amp;deg; C to +250 &amp;deg; C), digital System-on-a-Chip (SOC) ASIC technology in a high resolution, inherently rad-hard IBM Silicon-on-Insulator (SOI) CMOS process to enable next-generation flight electronics.&amp;nbsp; Demonstrate main flight-system electronics (flight processor, high- and low-speed instrument interfaces) in a chip containing a Cortex-M0 microprocessor that has been synthesized using a custom wide-temperature digital logic library developed in the same high resolution IBM SOI CMOS process.&lt;/p&gt;
&lt;p&gt;We will develop a power conversion solution that will increase end-to-end efficiency to 80&#37; or more compared to the 30&#37;-50&#37; efficiency typically obtained through use of Commercial Off The Shelf (COTS) converters and linear regulators.&amp;nbsp; This initiative will address the strategy and capabilities required for optimal spacecraft power system design by developing an end-to-end power conversion solution.&amp;nbsp; The specific goal is to improve the efficiency and reliability of the power conversion process from the power bus to the end user at the point of load.&lt;/p&gt;
&lt;p&gt;The primary objective is to mature an existing TRL 5 product that is designed for Earth applications into a fully designed and tested micro-transceiver useable on space-based extreme MEV challenged platforms. A secondary objective is to demonstrate interoperability between this micro-transceiver and next-generation NASA communications assets: specifically the &amp;quot;Communications, Navigation and Networking ReConfigurable Testbed (CoNNeCT)/Space Communications and Navigation (SCaN) Testbed&amp;quot; scheduled to be deployed aboard the International Space Station (ISS). The demonstration will be a ground (Earth) to Space (ISS) link demonstration.&lt;/p&gt;
&lt;p&gt;The primary goal is to provide direction of the Low Cost Lander proposal elements and control of the development space. It would evaluate the proposed technologies and their requirements / constraints, how they address the lander requirements, and how they fit with potential design concepts and overall cost. It would also bring together the functional experts for those areas not currently identified as needing funding for technology development. Each area would support and evaluate all other areas to ensure that information flow is unconstrained and transparent &amp;ndash; all challenges are shared challenges.&lt;/p&gt;
&lt;p&gt;The primary focus of this activity will be to outline a preliminary mechanical design for this conforming lander. Salient issues to be worked include (1) determining how to minimize rebound at landing incorporating hinges that use of torsion springs and a pawl ratchet system to attenuate the impact energy, (2) addressing terrain contours that would not necessarily exercise the hinge attenuator by utilizing low strength crushables or energy absorbing devices attached to the backs of each lander segment and (3) minimizing total lander mass through optimal integration of considerations (1) and (2).&lt;/p&gt;
&lt;p&gt;The goals of the proposed work are to Investigate the film thickness (10&amp;ndash;50 nm), substrate material (c-plane sapphire, MgO), and temperature (20-35 K) dependencies of the IF bandwidth in order to understand its upper limit; Investigate the operation of mixer devices of different lateral size (0.2-5 &amp;mu;m2) and establish the minimum size limit not leading to the degradation of the microdevice characteristics (TC, critical current, resistivity); Validate the THz operation of quasioptical MgB2 mixers through measurements of the noise temperature, IF bandwidth (&amp;Delta;fIF), and required LO power at 0.6 THz, 1.5 THz, and 2.5 THz. The targets are: TM &amp;le; 1000K, PLO &amp;asymp;10 &amp;mu;W, &amp;Delta;fIF &amp;asymp; 20 GHz.&lt;/p&gt;
&lt;p&gt;The proposed concept is to explore the use of Amorphous Metals (AMs) and Amorphous Metal Composites (AMCs) (fabricated entirely at JPL) for use as gears and bearing at both ambient and cryogenic temperatures. The goal is to exploit the advantageous mechanical properties of the AM&amp;rsquo;s and AMC&amp;rsquo;s (strength, hardness, low-density, toughness) and demonstrate that they outperform conventionally used gearbox materials. Previous studies have shown that ceramic gears can provide far better wear performance than metal gears, however they are traditionally avoided because they are prone to brittle failure due to their low fracture toughness.&lt;/p&gt;
&lt;p&gt;Develop key technologies for capturing and returning a small asteroid and returning it to near the Moon.&lt;/p&gt;
&lt;p&gt;Develop techniques for rapidly designing many-revolution, electric-propulsion, spiralling trajectories, including the effects of shadowing, gravity harmonics, and possibly impulsive manoeuvres, aerodynamic effects and gravity assists.&lt;/p&gt;
&lt;p&gt;Develop autonomous rapid response to science observations in missions targeting small bodies in fly-by mode where observing and reaction time is precious.&lt;/p&gt;
&lt;p&gt;In the proposed effort, we will demonstrate the feasibility of SMA-based actuation system by designing and fabricating a prototype sub-component of a locking mechanism for automatic cryogenic coupling transfer system. The prototype will incorporate a semi-automatic locking/unlocking device, where the locking function can be accomplished automatically during docking (without a user/program input), and the unlocking function can be executed by an external command once undocking was initiated. Near-equiatomic NiTi shape memory alloys (SMAs) will be used as the sensing and actuating elements, but since the coupler needs to operate at cryogenic temperatures, effort will be directed towards developing and characterizing new sub-zero (&amp;lt; 0 &amp;deg;C) ternary NiTiFe SMA for this purpose.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Develop autonomous target selection in missions targeting small bodies in fly-by mode where observing and reaction time is precious.&lt;/p&gt;
&lt;p&gt;To determine a percent freeze-out between liquid water and solid ice will add an important dimension to the cloud characterization. This Raman technique might also be able to distinguish the temperature of the particles in PSL. If successful, it could be permanently and non-intrusively mounted in the recently developed &amp;ldquo;tomography duct&amp;rdquo; section and add much needed information documenting each ice crystal spray, including frozen shut or frozen open nozzles.&lt;/p&gt;
&lt;p&gt;The objective of this proposal is to further define the potential for plasma treatment technology, developed by the NASA Glenn Research Center (GRC) to modify and enhance the wetting characteristics of water management surfaces. If successful, such enhancements will lead to more robust operation and reduced system complexity. Methods which promote both hydrophilic and hydrophobic character will be explored.&lt;/p&gt;
&lt;p&gt;Develop an alkaline exchange membrane (AEM)for use as a polymer electrolyte in both fuel cell and electrolyzer systems.&amp;nbsp; The ultimate goal in AEM development is to fabricate fuel cell systems required for future human space missions.&lt;/p&gt;
&lt;p&gt;A key challenge is that ice properties at the temperatures that exist on Europa are not well characterized. Our previous studies have shown that hardness as well as dynamic strength of ice increases rapidly with decreasing temperature. Specifically, current models for dynamic mechanical behavior of ice including fracture and fragmentation have difficulty in handling the extreme low temperature regime, because of the coupling between massive failure processes, strength, energetics and dynamics. We propose to address this regime: understanding this regime will enable development of robust and predictive penetration models for deep ice, that will enable the design of a penetrator.&lt;/p&gt;
&lt;p&gt;A study was done to examine low-temperature effects and radiation damage properties of bipolar integrated circuits.&amp;nbsp;&amp;nbsp; Anticipated benefits:&amp;nbsp; useful in missions with electronics that operate at low temperature. This task developed analytical methods for low temperature performance.&amp;nbsp;&amp;nbsp; Bandgap narrowing was shown to be the underlying reason for the large decrease in npn transistor gain at low temperature. Furthermore, we have developed analytical methods for radiation damage in combination with low temperature.&amp;nbsp; This model reproduces our experimental results of temperature dependent radiation damage yields. This work has shown that operating bipolar circuits at reduced temperature can improve radiation tolerance.&amp;nbsp;&amp;nbsp; Deliverable:&amp;nbsp; report.&lt;/p&gt;
&lt;p&gt;SWCam is CCAT&amp;rsquo;s short-wavelength camera.&amp;nbsp; It will image at 350 &amp;mu;m, possibly also 450 and 200 &amp;mu;m.&amp;nbsp; Photons are absorbed directly in the TiN inductor which, together with the interdigitated capacitor, forms the KID resonator.&amp;nbsp; A 432-pixel prototype array has been demonstrated at the Caltech Submillimeter Observatory (CSO), showing good yield and reasonable systematics.&amp;nbsp; During this year we plan to deliver a second-generation array with increased response to improve sensitivity.&amp;nbsp; This will be obtained with a smaller inductor, which is coupled with an array of lenses.&amp;nbsp;&amp;nbsp; We expect to demonstrate photon-noise-limited performance demonstrated at realistic sky loadings for CCAT (&amp;lt;50 pW per pixel).&amp;nbsp; A second deliverable is a demonstration array which operates in a different band, either 200 &amp;mu;m,&amp;nbsp; 450 &amp;mu;m, or 850 &amp;mu;m, as SWCam.&lt;/p&gt;&lt;p&gt;LWCam is CCAT&amp;rsquo;s long-wavelength camera.&amp;nbsp; It will image at 750 &amp;mu;m, 860 &amp;mu;m, 1.1 mm, 1.3 mm, 2.0 mm, and 3.3 mm, with a total of ~50,000 detectors.&amp;nbsp; The multi-color information provides discriminating power for dusty galaxies, galaxy clusters (as probed with the Sunyaev-Zeldovich (S-Z) effect), and star-formation regions.&amp;nbsp; It uses multi-scale phase-array antennas which are coupled via transmission lines to on-chip bandpass filters and the TiN KIDs. Deliverables this year include a full LW Cam prototype chip with 3-scale antenna, demonstrating good efficiency, beamshape, and sensitivity.&lt;/p&gt;
&lt;p&gt;Develop and test transition edge sensor (TES) bolometer arrays for precision polarimetry of cosmic microwave background (CMB).&amp;nbsp; Verify that critical antenna performance requirements, especially beam squint and cross-polarization are met.&lt;/p&gt;
&lt;p&gt;Assemble catalog of multi-wavelength data on evolved disks around relatively young stars, and information about models for such debris disks.&lt;/p&gt;
&lt;p&gt;Develop Zernike phase-contrast wavefront sensor for alignment of segmented telescopes using external light sources.&lt;/p&gt;
&lt;p&gt;Develop a state-of-the-art pulsar timing processor to be installed at the DSN to demonstrate precision pulsar timing capability along with a novel signal processing technique to remove the effects of the interstellar medium, thereby allowing us to reach the 100 nsec timing precision necessary for the detection of GW.&lt;/p&gt;
&lt;p&gt;This task will research and deliver solutions to 4 BIGDATA technology areas: (1) Rapid Science Algorithm Integration -- automatically and efficiently integrating IDL, Python, Matlab, etc. algorithms in the U.S. National Climate Assessment and into projects using the Common Astronomical Software Applications (CASA) software from NRAO; (2) data movement - exploring the tradeoffs between the architectural propertie and scalability properties of 4-5 modern data movement technologies under realistic scenarios for the U.S. NCAs and for the SKA; (3) cloud computing - for processing and for storage of Earth and astronomical data; (4) automatic and rapid data/metadata extraction from file formats - the use and application of technologies for automatically extracting text and metadata from science data formats.&lt;/p&gt;
&lt;p&gt;iPAS will develop several important technologies required to support system design and integration as well as space technology maturation. These services include:&lt;/p&gt;&lt;ol&gt;&lt;li&gt;A Test Orchestration scripting language called mREST that allows test conductors to monitor and control equipment from any web-enabled device.&lt;/li&gt;&lt;li&gt;A flexible data network architecture that allows technology teams to test in isolation, but enables cross-system integration when needed. This capability is tied to test orchestration and simulation, allowing mission parameters to support network management (for instance, attaching avionics systems together at docking).&lt;/li&gt;&lt;li&gt;Development of SysML models of components, and sponsoring the development of MagicDraw plug-ins. Products produced from the models include interface control specifications, telemetry dictionaries, and test specifications using Automated Test Markup Language (ATML).&lt;/li&gt;&lt;li&gt;A multi-center data network capable of supporting both integrated data exchange as well as test monitoring for remote engineers and labs.&lt;/li&gt;&lt;/ol&gt;
&lt;p&gt;
	Design, build, and test a 5,000 lbf thrust regeneratively cooled combustion chamber at JSC for a low pressure liquid oxygen/methane engine. The engine demonstrates its effectiveness by continuous steady state operation without catastrophic damage to the combustion chamber.&lt;/p&gt;
&lt;p&gt;
	This project will advance in three phases:&amp;nbsp; 1)&amp;nbsp; The addition of a regeneratively cooled test section to an existing pressure fed LOX/Methane engine.&amp;nbsp; This &amp;quot;partial regen&amp;quot; engine will be hot fire tested and thereby used to validate a multiphase regen cooling model. &amp;nbsp; 2) The development of a tube forming technique to construct a low cost full-size regeneratively cooled combustion chamber. &amp;nbsp; 3)&amp;nbsp; Using the results of #1 and 2, create a full scale regeneratively cooled combustion chamber (open loop cooling) for an existing 5,000 lbf subcritical liquid oxygen/methane rocket engine with variable chamber heat load capability.&amp;nbsp;&amp;nbsp; This full scale engine will be hot fire tested to demonstrate performance.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The Core Flight Software (CFS) system developed by Goddard Space Flight Center, through experience on Morpheus, has proven to be a quality product and a viable candidate for institutional software reuse on a broad range of NASA spaceflight projects, including in the near term MMSEV, HDU, spacesuits, downmass capsule, and OCO-3. The productivity and success seen with it can be extrapolated into tremendous savings if applied to human spaceflight software, but diligence needs to be done in assessing its use for large human-rated systems. If deemed viable, the potential exists to reform the state of practice in building human spacecraft software systems by capitalizing upon reuse and realizing a great potential for cost, schedule, and risk reduction.&lt;/p&gt;
&lt;p&gt;The Flight Deck of the Future (F.F) will integrate interdisciplinary talent to design innovative, integrated human interfaces for the next generation of human spaceflight. Two research areas that are ripe for development and vetting through the F.F are Virtual Windows and Electronic Textiles (e-textile):&lt;/p&gt;&lt;p&gt;&amp;nbsp; - Virtual Windows can significantly improve external visibility&amp;nbsp; thereby greatly enhancing&amp;nbsp;crew situational awareness, performance, and psychological health. This project includes integration of tiled displays, scene-stitching software, multiple cameras with real-time video imagery, and various camera control methods.&lt;/p&gt;&lt;p&gt;&amp;nbsp; - By putting interfaces on the body, wearable technology enables rapid access to information and controls, continuous physiological monitoring, and alarms for dangerous environmental conditions. This project includes design and development of an e-textile garment with integrated power, data network, and wireless communications.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Develop&amp;nbsp; a robotic sample handling/ manipulator system for the GeoLab glovebox. This work leverages from earlier GeoLab work and a 2012 collaboration with a University of Bridgeport project (Zheng Li, 2012 X-Hab challenge winner) to build a microgravity sample holder for the glovebox.&amp;nbsp; The GeoLab team is providing inputs to the Bridgeport&amp;nbsp; design; this proposal extends the Bridgeport product for full glovebox operations. It includes a translation track for increasing the DOF and whole-glovebox operations and software development for remote control of sample&amp;nbsp; handling, facilitating remotely controlled analysis and leveraging astronaut resources.&lt;br /&gt;Tests performed during Desert RATS in 2011 and 2012 provided recommendations for increased robotic operations inside the GeoLab. Furthermore, the need for handling samples in a reduced gravity setting extends the operational concepts for&amp;nbsp; preliminary examination of&amp;nbsp; samples inside a space-based laboratory. We will develop and&amp;nbsp; integrate the GeoLab translation track in parallel with the U.&amp;nbsp; Bridgeport project, and feed requirements to the Bridgeport team to&amp;nbsp; ensure seamless integration.&amp;nbsp; We continue our collaborations with the DSH software development team to build controls for the&amp;nbsp; manipulator.&amp;nbsp; The system will be tested as part of the summer 2012 DSH operations, and operational outcomes to be compared with earlier human-tended tests.&lt;/p&gt;
&lt;p&gt;The project consists of the design, fabrication and testing of two science platforms. &amp;nbsp;The first is a portable Robonaut-compatible science &amp;ldquo;toolbox&amp;rdquo; that will function as a self-contained, first generation modular science system. &amp;nbsp;The second is a larger robot-towed six-wheeled platform that will also demonstrate remote-controlled robotic science. &amp;nbsp;Both of these systems will function as science pre-cursors allowing a large amount of area to be investigated prior to crew arrival and allowing more optimized human exploration time. &amp;nbsp;In addition, both platforms will be evolved in later generations to provide modular, self-contained science platforms that can fly actual science missions to the Moon, Mars, and NEOs.&lt;/p&gt;
&lt;p&gt;
	This is a one-year project to apply a GIS analysis tool to new orbital data for lunar resource assessment and martian habitability identification.&amp;nbsp; We used ArcGIS, the state-of-the-art software for mapping, integrating, and analysis of spatial data. We focused on the assessment of several regional lunar pyroclastic deposits and habitability analysis in the Chryse-Acidalia portion of the martian lowlands.&amp;nbsp; This work expands upon a previous 3-year project enabled through IRD funds.&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	As a direct result of this project three scientific papers have been published:&lt;/p&gt;
&lt;p&gt;
	Allen, C.C., Greenhagen, B.T., Donaldson Hanna, K.L., and Paige, D.P. (2012) Analysis of lunar pyroclastic deposit FeO abundances by LRO Diviner, &lt;em&gt;Journal of Geophysical Research, 117&lt;/em&gt;, E00H28, doi:10.1029/2011JE003982.&lt;/p&gt;
&lt;p&gt;
	Oehler, D.Z. and Allen, C.C. (2012) Giant polygons and mounds in the lowlands of Mars: signatures of an ancient ocean ?, &lt;em&gt;Astrobiology&lt;/em&gt;, 12, 1-15.&lt;/p&gt;
&lt;p&gt;
	Oehler, D.Z. and Allen, C.C.&amp;nbsp; (2012)&amp;nbsp; Focusing the search for biosignatures on Mars:&amp;nbsp; Facies prediction with an example from Acidalia Planitia, in &lt;em&gt;Sedimentary Geology of Mars&lt;/em&gt; (J.P. Grotzinger and R.E. Milliken, eds.),&lt;em&gt; SEPM Special Publication No. 102&lt;/em&gt;, 183-194.&lt;/p&gt;
&lt;p&gt;
	Environmental regulation will force current baseline&amp;nbsp; precision cleaning solvent (AK-225) to be phased out starting 2015. We plan to develop&amp;nbsp; a new solvent or solvent blend that will replace the current baseline solvent ( AK225). The Plan is to test at least&amp;nbsp; 3 solvent blends for cleaning efficiency on coupons exposed to known contaminants. The project has already created a test process that can tie results back to work done in the 1990&amp;rsquo;s. We will use this data to support the Precision Cleaning and Contamination Control&amp;nbsp; (PC3) efforts over the next few&amp;nbsp; years.&lt;/p&gt;
&lt;p&gt;Spaceflight results in adverse health effects on the human body.&amp;nbsp;&amp;nbsp; These effects may result in increased clinical risk to crewmembers participating in exploration-class deep-space missions.&amp;nbsp; For clinical monitoring of astronauts and for in-flight biomedical research, laboratory instruments must be designed which function in the spaceflight environment.&amp;nbsp;&amp;nbsp; &amp;nbsp;Currently there is no instrument capable of generating a white blood cell (WBC) count and differential during spaceflight, even though this is an existing National Aeronautics and Space Administration (NASA) medical requirement.&amp;nbsp; We evaluated a new commercial analyzer in the context of spaceflight requirements and compatibility with the zero gravity environment.&amp;nbsp; Reduced gravity analysis was performed during terrestrial parabolic flight. The analyzer was found to uniquely meet the basic requirements for spaceflight and should be appropriate for measuring WBC parameters onboard the International Space Station.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The dry-electrode harness is composed of a variety of components.&amp;nbsp; The harness interfaces with the human via a commercial-off-the-shelf (COTS) FDA cleared dry electrode that has been woven in place to a custom designed harness that guarantees correct placement of electrodes to support a diagnostic quality 12-lead ECG.&amp;nbsp; The electrodes themselves are connected to a small, battery powered, COTS ECG system that wireless transmits data to a custom developed software application that receives and processes the data.&lt;/p&gt;&lt;p&gt;The dry electrodes replace the more traditional wet-prep electrodes that are single use devices with a specific expiration date.&amp;nbsp; The dry electrodes are multi-use devices and do not have an expiration date.&amp;nbsp; The custom harness essentially automates the process of lead placement which eliminates the &amp;ldquo;spaghetti&amp;rdquo; effect that often accompanies traditional ECG data collection and prevents the common clinical problem of lead wire misplacements and reversals.&amp;nbsp; By embedding dry electrodes and wires into the harness, don/doff times are significantly decreased while maintaining a high level of data integrity.&amp;nbsp; Finally, the custom software application simplifies and &amp;nbsp;streamlines the data collection process making the forwarding of ECG data a much easier process.&lt;/p&gt;
&lt;p&gt;Demonstrate use of Microsoft Kinect infrared cameras in the application of passive data collection during human-in- the-loop (HITL) tests. Low-cost COTS cameras are used, modifying free open source software, to demonstrate the collection of data to create real-time, high-resolution 3D computer models of humans and vehicles in operational test environments.&lt;/p&gt;
&lt;p&gt;The Human-Robot Interaction Reconfigurable Test Environment (HRI-RTE) integrates a grid-based, reconfigurable test arena and an operator workstation with state-of-the-art displays and controls for commanding small, multi-purpose robots. It will be used to investigate advanced methods of commanding robots, innovative display concepts, improved camera views, methods of feedback to operators for teleoperation, and mitigations for time delays. The reconfigurability of the test environment will be validated by test scenarios that focus on human-robot system performance across a range of HRI technologies, tasks, metrics, and environmental scenarios. The project&amp;rsquo;s focus is on the human interface to the robotic system rather than on robot design.&lt;/p&gt;
&lt;p&gt;Detection of toxic vapors from aerospace fluids such as propellants is vital to the protection of those working in and around spacecraft.&amp;nbsp; Chemical reaction based sensors relying on changes in color, electrical or thermal properties have the potential to be extremely sensitive. One of the limiting factors to the sensitivity of these devices is the nature of the substrate which contains the active agent. New substrates can be coupled with, and tailored to, new and existing detection chemistries for increased sensitivity.&amp;nbsp; Aerogels and porous low density ceramics may have promise of increasing sensitivity of chemical detection. Aerogels in particular hold promise because the detection chemistry is in three dimensions giving an increased optical path length resulting in increased sensitivity and increased dynamic range.&amp;nbsp; Alternative indicator chemistries such as tetrabromoaurate will be evaluated with these new substrates.&lt;/p&gt;
&lt;p&gt;The spectrum of a light affects crew health.&amp;nbsp; This solution does not require power or a calibration cycle. The premise is that an optical solution is sufficient to document spectra for light sources such as those on ISS.&lt;/p&gt;&lt;p&gt;This innovation would like to research the viability of spectral characterization of a light source without the use of photometric devices like spectrophotometers.&amp;nbsp; The spectral characteristics of a light source are an important component to the design and maintenance of a lighting environment where habitability and workmanship issues are tied to color. Color is important for tasks like litmus strip color matching, and crew health issues in controlling Circadian Rhythm.&amp;nbsp; Currently, the International Space Station does not have on-board sensors to measure the spectrum of the lighting environment.&amp;nbsp;&amp;nbsp;&lt;/p&gt;&lt;p&gt;Assuming a successful completion of this study, additional proposals will be made for formal development of a test kit to be used for ground support and on-orbit color characterization of lighting environments.&lt;/p&gt;
&lt;p&gt;
	Speech recognition technology is relatively mature.&amp;nbsp; In spite of this it is not always accurate. Greater accuracy occurs when the speech is constrained by the context of the application. For instance, when using Siri to interact with an iPhone, there are a limited number of topics and interactions available. Gesture recognition is a newer technology, but is becoming viable, particularly with the advent of the Microsoft Kinect. Gesture recognition provides additional context for speech recognition; speech provides context for gestures. Integrating both would provide a much more robust environment for human computer interaction.&lt;/p&gt;
&lt;p&gt;
	Survey of the technical field was accomplished. Basic software and hardware, including microphones, cameras and 3D depth sensors was procured.&lt;/p&gt;
&lt;p&gt;
	Basic equipment functionality has been demonstrated. Groundwork has been laid for continued efforts.&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Windows in habitable modules represent significant design and operations impacts to future spacecraft, yet viewing requirements, both electronic and passive, continue to mature.&amp;nbsp;&amp;nbsp; With longer missions over greater distances, it becomes harder to accommodate both size and modularity of viewing.&amp;nbsp; The Hybrid Window Portal would allow easier design, more locations for direct viewing,&amp;nbsp; and easier maintenance and represent less of an impact to a vehicle&amp;#39;s structural integrity than traditional windows, and applies to aluminum, composite and inflatable structures.&amp;nbsp; This project intends to build on an on-going IR&amp;amp;D effort and a 2011 ICA investigation of virtual window technology, and will explore options to provide adequate viewing and sensing through arrangements of multiple, small portals that can accommodate cameras and sensors.&amp;nbsp; Smaller portals accommodate more cameras and sensors than ever before, and offer different pointing directions so optimum viewing angles can be selected, while an integrated view (Mosaic Video) provides perspective.&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The space suit is arguably the most intimate piece of space flight hardware yet we know surprisingly little about the interactions between the astronaut and this machine.&amp;nbsp; Current EVA mobility studies only allow for comparisons of how the suit moves when actuated by a human and how the human moves when unsuited. Over decades, engineering and science teams have attempted to bridge this gap using tools from live x-rays to shape tape to pressure sensors but none of these technologies have proved to be both safe and reliable. However, there are now new wireless inertial measurement units (IMUs) that are small enough to be worn in pockets of the space suit undergarments to provide real-time data on the postures and joint angles assumed by the suited test subject as they conduct simulated EVA tasks.&amp;nbsp;&amp;nbsp; Thus the proposed development is to use the new IMUs with the data collection system that can synch across 32 human worn sensors and simultaneously link to the Vicon MX data collected from externally mounted suit reflectors.&amp;nbsp; Initially, success of this project will be measured by the ability to transmit the wireless signals through the pressurized suit without significant loss of signal or distortion and the development of software code to accurately describe the motion of joint segments during simulated EVA tasks.&amp;nbsp; Follow on efforts will provide the first time linked data sets for internal and external movements during suited mobility assessments.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	Energy consumption and cost are a continuing issue in the world, including JSC Buildings.&amp;nbsp; New technologies and designs in the commercial world have made available LED lighting tubes that can be easily retrofitted/replaced into standard fluorescent rod light fixtures found commonly in JSC offices/buildings.&amp;nbsp; While the upfront cost of the hardware exceeds standard fluorescent rods (by 2 to 4 times), the energy savings is quoted as up to 50&#37; or more.&amp;nbsp; The retrofit time/complexity is minimal, in that the ballast must be removed or bypassed, but the rods then fit into existing fixtures. The proposal is to evaluate and test at least two COTS versions of LED light rods, in a typical office area, for the factors of overall lighting quality, energy savings, labor time/cost for retrofit, and delta in maintenance required based on quoted hardware life expectancy vs. typical cost for repair/replacement of fluorescent&amp;nbsp; fixtures.&lt;/p&gt;
&lt;p&gt;
	This project completed retrofit of three typical office areas in Bldg. 7 with prototype LED rods from two vendors.&amp;nbsp; The measured savings in operating power was approximately 73&#37;, which did not include the savings for air conditioning from removal or bypass of the hot ballast.&amp;nbsp; The measured quality of the lighting (in Foot Candles at varying distance) was greater with the LED bulbs, without consideration to the fixture covering.&amp;nbsp; Retrofit was demonstrated as simple to implement.&amp;nbsp; The benefits of this technology are significant, and further study to implement this new technology into laboratories and other areas of JSC is recommended.&lt;/p&gt;
&lt;div style="margin-left: 0.5in"&gt;
	&amp;nbsp;&lt;/div&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;
	A magneto-Rheological (MR) fluid based exoskeleton leg demonstrator was developed to help long duration exploration mission crews obtain exercise with entertainment during flight and at their destination.&lt;/p&gt;
&lt;p&gt;
	A novel exercise and recreation device is proposed that can provide physical and mental health preservation benefits during long duration deep space exploration missions. A prototype based on MR dampers was built to demonstrate the technology. However, this will need to be modified to drive forces through major leg bones and muscles to realize medical benefits and present to NASA exercise scientists for evaluation. Very light weight, compact exercise devices are considered a necessity for long duration space flight missions. Existing ISS countermeasures are not only functional limited, but also bulky, complex and require high maintenance. The proposed MR exoskeleton is light weight, compact sized, and capable of providing concentric and eccentric exercises. With the integration of Microsoft XBox Kinnect, the exoskeleton will have full range of flexibility-personalized exercise profile, data tracking, down-linking, and recreation activities: immersive video games and aquatic exercises.&lt;/p&gt;
&lt;p&gt;
	Demonstrate the inside-out manufacturing process by manufacturing a complex shaped composite structure with imbedded wiring and fluid handling without the use of a tooling form. Utilize the core as the tool and build parts from the inside-out, placing utilities before composite structure.&lt;/p&gt;
&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;FAAST is an R/C helicopter platform that is being developed by the Aeroscience and Flight Mechanics Division (EG) as a low-cost, low-risk, hands-on way for engineers to test autonomous and automated (A&amp;amp;A) system architectures, algorithms, and sensors.&amp;nbsp; It is also envisioned as a platform for building trust in A&amp;amp;A systems among key stakeholders such as program/project management, crew members, and operators.&lt;/p&gt;&lt;p&gt;Trust is the greatest obstacle to implementing greater autonomy and automation (A&amp;amp;A) in the human spaceflight program. The Future Autonomous and Automated Systems Testbed (FAAST) is an R/C helicopter-based system being developed by the Aeroscience and Flight Mechanics Division (EG) as a low-cost, low-risk, hands-on way for customers (program management, crew, and operators) to become familiar with and build trust in A&amp;amp;A systems, and as a platform for engineers to quickly and cheaply test A&amp;amp;A architectures and algorithms.&amp;nbsp; An early goal of this project is the development of an autonomous GN&amp;amp;C system, a key component of which is access to suitable sensor hardware. In this project we requested funds to procure navigation sensors (e.g. MEMS IMU, GPS receiver, LIDAR, etc.) in support of this effort.&lt;/p&gt;&lt;p&gt;We researched and procured navigation sensors (e.g. MEMS IMU, GPS receiver, LIDAR, etc.) and integrated them into the helicopter platform, with the objective of performance suitable for autonomous waypoint navigation. The intended product of this activity is the development of a prototype navigation system that will form the navigation backbone of FAAST. Upon completion of this project&amp;#39;s work, FAAST will have a functioning navigation system suitable for enabling future A&amp;amp;A research objectives, including autonomous rendezvous and docking, and autonomous take-off and landing.&lt;/p&gt;
&lt;p&gt;The Space Food Systems Laboratory&amp;#39;s (SFSL) current Bulk Overwrap Bag (BOB) package, while simple and effective, leaves room for improvement. Currently, BOBs are sized&amp;nbsp;to fit in Cargo Transfer Bags (CTB). On orbit, however, the pantry setup utilizes several Collapsible US Food Containers (CUFC). In addition, the entirety of the menu must be overwrapped with an aluminum laminate package in order to meet the oxygen and water vapor permeability requirements of an 18 month shelf life requirement. The development of a Phase II BOB could alleviate several or all of these issues in a cost, mass, and volume sensitive manner by changing the size and shape of the BOB as well as potentially finding an alternative material with sufficient barrier properties to eliminate the secondary overwraps.&lt;/p&gt;
&lt;p&gt;Gesture commanding can be applied and evaluated with NASA robot systems. Application of this input modality can improve the way crewmembers interact with robots during EVA.&lt;/p&gt;&lt;p&gt;Gestures commands allow a human operator to directly interact with a robot without the use of intermediary hand controllers.&amp;nbsp; There are two main types of hand gesture interfaces: data glove-based devices and computer vision techniques. Data glove-based devices are worn by the human and capture hand movements through embedded sensors. Computer vision techniques interpret hand movements by using the video feed from cameras. There is a need to assess the feasibility of using both approaches when the person commanding a robot is wearing EVA gloves. This is because EVA gloves can restrict movements of the hand and affect gesture recognition accuracy and recognition speed.&lt;/p&gt;
&lt;p&gt;Develop an algorithm to model foam compression during impact and implement as an easy to use excel based shipping foam design tool.&lt;/p&gt;&lt;p&gt;Refine methodology of calculating foam compression using the innovative Stress-Energy testing method which drastically increases flexibility of data collected by normalizing data with respect to drop height and foam volume. Foam compression is critical in cases where a protrusion exists which should not contact the bottom of the container. There are benefits of using multiple foam types or sandwiched foam packaging. Tests were conducted to confirm the theory for how to combine foams as well as add the function to the existing tool. Calculations for sandwiched foams along with the addition of flight foams to the data base provides tools required for engineers to properly design foam packaging when multiple foams would be beneficial. This provides the option to pack hardware for flight then ship hardware to launch facility.&lt;/p&gt;
&lt;p&gt;Oxygen is an essential treatment for several life-threatening conditions including pneumonia, the single biggest cause of death in children less than five years of age.&amp;nbsp; Developing countries frequently lack access to the bottled, cryogenically formed oxygen used in Houston hospitals.&amp;nbsp; Oxygen generators that use Pressure Swing Adsorption (PSA) methods are prone to system failure: one study reports that 20 out of 20 PSA units donated to a hospital in Gambia were inoperable after 6 weeks of use.&amp;nbsp; There is a new oxygen concentrator technology that uses electrolytic oxygen transfer through a strong, ceramic, monolithic wafer.&amp;nbsp; The system is capable of producing high purity (&amp;gt;99.9&#37;) pressurized (200 psig) oxygen without a mechanical compressor.&amp;nbsp; Because it is a solid state device, it shows good promise for reliable performance in demanding conditions.&amp;nbsp; One unit has operated in a military field hospital in Afghanistan - powered by a diesel generator, it has operated 24/7 for 14 months with no shut-downs or failures.&amp;nbsp; The technology is new: there are fewer than 12 ceramic oxygen concentrator units with this design in existence.&amp;nbsp; NASA has three units.&amp;nbsp; No ceramic oxygen concentrator (with the monolithic wafer design) has ever been powered by a solar power source.&amp;nbsp; A ceramic oxygen concentrator, powered by a solar panel, has the possibility of safely and reliabily delivering high purity, high pressure oxygen in demanding environments (like hospitals in developing countries or space exploration vehicles) - to date, nobody has developed or tested a ceramic oxygen concentrator that is powered by solar panels.&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Crewmembers undergo strenuous suited training for EVA missions. Frequent exposure to such activities can eventually lead to Cumulative Trauma Disorders/Injuries and reduced performance (results which are already well documented for the EVA suit). Engineering data such as dynamic fit, mobility and human-suit contact measurements within the suit are currently difficult to obtain, but is sorely needed to enable designers to make the necessary changes to current designs and optimize future designs. Physical performance and human-suit interaction data are thus essential to shed new insight into what is happening inside the HUT.&amp;nbsp; Relevant and currently hard to obtain human interaction data inside the suit should enable NASA to build a 21st century suit.&lt;/p&gt;&lt;p&gt;A transparent EVA-type suit HUT with adjustable components was designed and manufactured. The transparent HUT can be attached to an adjustable-height stand, or worn directly on the body with a restraining harness to keep the transparent HUT&amp;rsquo;s relative position the same as an actual HUT when worn.&amp;nbsp;The transparent HUT was designed to weigh a mere fraction of the actual HUT and therefore facilitate functional testing.&amp;nbsp;&lt;/p&gt;&lt;p&gt;A brief pilot study showed that the HUT did indeed fit the subject similarly to an actual EMU HUT, with restrictive internal volume and mobility, and that it greatly improved the ability to gather internal volumetric and interference data and allowed visual/video inspection of internal interfaces.&lt;/p&gt;
&lt;p&gt;The project was completed via a multi-division collaboration within JSC and university partnerships. A number of device concepts were developed and tested that utilize a conductive material directly embedded/adhered to the restraint layer strap. The material has a natural electrical resistance, and as it is stretched (along with the strap) the resistance in the device will change. This resistance change can be monitored and correlated to a change in the strap load.&lt;/p&gt;
&lt;p&gt;
	Current water quality monitors aboard the International Space Station (ISS) are specialized and provide limited data. The Colorimetric Water Quality Monitor Kit (CWQMK) and the Total Organic Carbon Analyzer (TOCA) are used to measure biocide concentrations and the total organic carbon load, respectively.&amp;nbsp; While each of these instruments provides important analytical information, they lack the ability to fully characterize the organic and inorganic compounds present in the ISS water systems.&amp;nbsp; Identification of individual compounds requires the return of ISS archival samples that are analyzed in ground laboratories.&lt;/p&gt;
&lt;p&gt;
	A survey of the other environmental monitoring hardware used on the ISS reveals that air quality monitors have advanced further toward the end goal of providing real-time, compound-specific information that can be used by the crew. As many of the organic compounds on the target lists for air and water quality monitoring are identical, evaluating the current air quality monitoring technologies is a logical first step toward development of a water quality platform that can characterize the organic load in spacecraft water systems. The initial phase of this effort is focused on ion mobility spectrometry (IMS). IMS technology was previously used in the ISS Volatile Organic Analyzer (VOA), and it is employed for numerous terrestrial applications, such as the detection of a variety of large analytes in aqueous solution. It also is widely field-deployed by the Department of Homeland Security for explosives detection.&lt;/p&gt;
&lt;p&gt;
	Our approach couples IMS with electrospray ionization (ESI) to ionize and detect target analytes in water samples. The successful completion of this work could potentially allow for the analysis of both air and water samples using a single instrument.&lt;/p&gt;
&lt;p&gt;
	As a result of technological breakthroughs, research and applications in the Terahertz (THz) radiation system are experiencing explosive growth. The non-ionizing and penetrative nature of THz radiation makes it promising for detection in the medical imaging applications. The THz image can be identified as markers of malignant tissues.&lt;/p&gt;
&lt;p&gt;
	Because the requirements for THz instruments are very ambitious, there is a need for new nano-antenna configurations, and for refining existing configurations and technologies for top performance. In this study, we will investigate various THz nano-antennas to improve the performance of the nano-antenna with innovative designs. The objective of this study is to highlight current and emerging research in the THz nano-antenna fields, as well as applications of this technology.&lt;/p&gt;
&lt;p&gt;Exercise equipment for on-orbit or very low gravity use has been developed using springs or motors to provide a constant force for resistive exercise.&amp;nbsp; These systems do not, however, fully mimic the free-weight ground equipment that they are replacing as they do not have inertia.&amp;nbsp; It is the intent of this project to produce a prototype variable inertia device which can be integrated with resistive equipment in development to produce the &amp;#39;missing&amp;#39; inertia component.&lt;/p&gt;
Field emission electric propulsion (FEEP) thrusters have gained
considerable attention for spacecrafts disturbance compensation because
of excellent characteristics.  The application of current FEEP has been
slow in developing mainly caused by high specific power, which limit the
milli-Newton thruster development due to insufficient onboard power.
Dramatic field improvement from nanometer carbon nanotubes (CNTs) is a
big advantage to increase the FEEP thrust more than 10 times under
constant specific impulse (power).  Phase I study showed a lower power
consumption of 0.027 W/?YN from the CNT based ion source, comparing with
the power consumption of 0.063 W/?YN from the traditional thruster.  The
CNT based FEEP ion source will be developed innovative in several
aspects: integration of CNTs into the ion emission anode, buildup of the
edge anode structure by the combination of the metal tip emitter and the
slit emitter, and construction of a edge anode array capable of
selective operation of different thrust unit. The power consumption of
for ion thrust is expected to be reduced by a factor of 5 and more. The
application of the room temperature carbon nanotube field emission
electron neutralizer will further reduce the total power input to the
ion engine.
A mobile-deployable, submersible multi-depth, simultaneous, spectro-radiometer system (AquaTree) was designed under phase-I, and key elements were tested in the ocean.  Detailed modeling and design analysis were conducted to optimize the sensor system for the extremely wide dynamic range of the radiation field from above the surface down to 10 m below.  Under Phase-II a full system will be assembled, including (i) two fiber fed spectrometers with TE cooled cameras to provide long integration time and broad dynamic range, (ii) fiber optics based radiance and irradiance collectors that feed into the spectrometers, (iii) the spectrometers housed in a watertight enclosure with multiple fiber and electrical feedthrough connectors.  Control will be from a computer on board a ship located up to 300 m away to avoid shading.
The system will be deployed at sea.  Simultaneous validation will be conducted using other commercial radiation measuring devices and profilers, and water sampling and analysis; coordination with overhead assets (MERIS, MODIS) will provide additional measurements for complete validation of the AquaTree performance and closure for the radiative transfer modeling.  
The proposed work is synergistic and complementary to other oceanic research work at OKSI; including the AquaScanUVNIR-micro, an airborne hyperspectral scanner.  Both the AquaScan and AquaTree cover the 350-1000 nm spectral range.  The AquaScan will be flying in on manned platform and also on NASA UAV in support of ocean color, benthic diversity, biomass, and productivity of seagrass and coral reef biomes research.  Another project is exploring a low-cost space access for a HyperScan-micro on board a CubeSat.  Hyperspectral measurements over a long horizontal path are also conducted by OKSI to extract littoral aerosols properties.
Volcanic ash is a significant hazard to aircraft engine and electronics and has caused damage to unwary aircraft and disrupted air travel for thousands of travelers, costing millions of dollars. Michigan Aerospace Corporation (MAC) proposes to demonstrate the concept feasibility of a Raman Light Detection and Ranging (LIDAR) system to obtain real-time information from volcanic ash clouds, to be named VADER (Volcanic Ash DEtection Raman LIDAR). The instrument will be designed to operate from an airborne platform, and as such, will be compact and light weight. This approach benefits from returning real-time measurements, in contrast to sampling methods (impactors) that require post-mission analysis. This project will utilize MAC's extensive heritage of rugged LIDAR system design and construction.
Deployable Space Systems, Inc. (DSS), and Space Systems Loral as a key subcontractor and potential commercial infusion partner, will focus the proposed SBIR Phase 2 program on the TRL 5/6 technology maturation / development of an affordable, lightweight, high power, maximum performance solar array specifically configured to next-generation high power geostationary-earth-orbit commercial mission requirements, and in support of future NASA missions.  DSS's recently completed NASA SBIR Phase 1 program has established a TRL 3/4 classification for an innovative affordable maximum performance solar array as applied to a multitude of NASA and commercial missions.  Significant concept feasibility, design/analysis, trade study/evaluation, and proof-of-concept hardware build/test efforts executed during the Phase 1 program have validated the proposed technology as a potentially revolutionary photovoltaic flexible blanket solar array system that provides enabling performance in terms of:  High specific power / lightweight (up to 200 W/kg BOL at the array level with ZTJ PV), compact stowage volume (&gt;60-80 kW/m3 BOL), high deployed strength and stiffness, mechanical and electrical simplicity, high reliability, high modularity, rapid production capability, high platform flexibility and applicability to many missions, and ultra-affordability (&gt;24&#37; recurring cost savings at a minimum).  Building off the success of the recently completed Phase 1 program, the proposed Phase 2 follow-on program will significantly increase technology readiness to TRL 5/6, ready it for an end-user qualification program, and drastically accelerate commercial infusion.
High-temperature passive wireless surface acoustic wave (SAW) sensors are highly desirable for improving safety and efficiency in aviation and space vehicles. This proposal addresses the growth and processing of a new class of high temperature material into acceptable SAW wafers, the production of SAW temperature sensors, and the integration of the SAW and thin film antenna (SAWtenna).  
The project will provide a new, unique material grown in the US (no other US manufacturer is known, produce high temperature, radiation hard, solid state, passive wireless sensors for use in harsh environments. In this project, we will:

1) Develop a crystal material for SAW wafers suitable for high-temperature SAW fabrication.
2) Design orthogonally frequency coded OFC (up to 1000 degrees C) SAW temperature sensors .
3) Integrate the SAW and antenna onto the wafer such that there are no external connections. 
	   
In Phase I the capability for the production of LGT crystals was established and 2in diameter boules were grown. The crystals were processed into SAW wafers and confirmed to be of excellent quality, as evidenced from SAW parameters extraction.  A thin film process using simple metallization demonstrated extended device operation at 700 oC and short-term operation at 800 oC. Phase I demonstrated the feasibility of high-temperature SAW devices, and a clear path in the Phase II effort for 1000 oC device operation. During Phase II, we will explore variations of the metallization and encapsulation, which will extend device life.  SAW OFC high temperature sensors, operating in the 915 ISM band, will operate simultaneously over temperature and will be delivered to NASA.  
Phase II will develop a fully integrated sensor antenna and upscale the crystal growth for 3-4in SAW wafers. Probability for Phase III commercialization of both the wireless SAW sensors and SAW wafers is very high.
The key innovation of this effort is the development of future traffic demand for Uninhabited Aerial Systems (UAS) given the various missions they intend to fly, and thereafter populating a data warehouse with these projected flights that can be marketed to the aviation community.  We propose developing one flight demand set for each of twenty-five future years from the 2015 through 2040, incorporating nineteen of the proposed UAS missions (sixteen to be developed during Phase II and three already completed from the Phase I activity, for a total of 19 missions * 25 years = 475 demand sets available at the conclusion of the project).  In developing these demand sets, we are capitalizing on new technologies prototyped and demonstrated in Phase I of this project, in which our team demonstrated that credible flight demand sets for UAS missions can be developed using a combination of socioeconomic modeling combined with techniques derived from the activity-based modeling community.
NASA is interested in advancing green technology research for achieving sustainable and environmentally friendly energy sources. Thermo-electric power generation (TEPG) has exceptionally rich potential to fulfill this need. A TEPG module requires (1) material that can provide high figure of merit while still providing efficient heat control; (2) low resistance ohmic contacts that operate at high temperature; and (3) efficient heat sink material to provide optimal temperature difference between hot and cold junctions. In Phase I, we addressed all of these issues. We successfully produced device quality n-type and p-type, single crystalline and bulk nano-composite PbTe material suitable for TEPG device fabrication. We also developed a novel electrical contact technology having low electrical resistance and capability to withstand significantly elevated temperatures (&gt;800 degree C). And we developed a light weight, highly thermal conductive (50 to 60 &#37; better than copper) heat sink material with tailored low coefficient of thermal expansion (CTE). These improvements allowed us to develop the design and technique for fabrication of large scale TEPG on a manufacturing level. In Phase II we will expand upon these developments and implement them. We will fabricate TEPG devices using the nano-composite materials. These devices will utilize the ohmic contacts and the heat sink technology that we developed. We will also utilize another approach that we developed in which two materials (PbTe and (Bi-Sb)2(Se-Te)3  based alloys) are segmented into a two-part material that has high efficiency over the entire temperature range from 200-500 degreeC, PbTe being at the hot end and the (Bi-Sb)2(Se-Te)3 based material at the cold end. Our ultimate goal will be to build a TEPG module using such segmented devices to demonstrate the generation of 1kWatt of power. We will develop the technology of fabricating these modules at a large scale manufacturing level, at low cost.
Based on the successful feasibility demonstration in Phase I, Physical Optics Corporation (POC) proposes to continue the development of a novel Structural Integrity Inspection and Visualization System (SIRIUS), which addresses NASA's need for compact nondestructive evaluation (NDE) of the structural integrity of spacecraft components and structures. SIRIUS is based on one-sided three-dimensional (3D) structure imaging via collecting the information on density profiles in multiple object cross sections through hard X-ray Compton-scattered imaging. The SIRIUS Phase I prototype system demonstrated excellent potential for 3D localization of defects in various aerospace materials and structures, such as thermal protection system (TPS) ceramic foam tiles, micrometeoroid and orbital debris (MMOD) shielding, spacecraft pressure walls, inflatable habitat structures, composite overwrapped pressure vehicles (COPV), aluminum-rubber composites, and metal honeycomb materials. In Phase II, POC will develop a compact, standalone version of the SIRIUS system with improved performance (in terms of resolution and data acquisition speed), as well as an advanced graphical user interface (GUI) for straightforward data acquisition and visualization. At the end of Phase II, POC will perform a TRL-6 demonstration of SIRIUS at the NASA facilities. SIRIUS will provide NASA with an effective NDE tool for both in-space and on-ground applications.
A few NASA decadal missions such as the Aerosol Clouds Ecosystems (ACE) mission require space-based millimeter-wave radar apertures to complete the science objectives. We propose to create dual-polarized microfabricated copper-based antenna apertures with integrated MMICs that go beyond the capabilities funded to date at the upper frequencies of interest by enabling electronic scanning at W-band frequencies, while not precluding the co-location of Ka-band capability in the same aperture. This Phase II effort will constitute element-, feed-, MMIC-, and array-level analyses of the trade space for the proposed aperture. In addition we will provide a hardware demonstration of a W-band transmit/receive array tile showing MMIC integration on the necessary scale for W-band phased arrays and high-efficiency dual polarized antenna elements.
The proposed Wireless, passive, SAW sensor system operates in a
multi-sensor environment with a range in excess of 45 feet. This
proposed system offers unique features in two (2) important areas. The
first is in the development of a new sensor type, a strain gauge that is
based on OFC techniques and implemented with the low loss
characteristics of SAW Unidirectional transducers. The second is in the
design of an integrated interrogator system that has DSP-based embedded
signal processing. Interrogator will also be capable of rapidly
performing multiple interrogations which can them be used to make
ibration measurements or averaged to extend the operational range of the
system. This proposal extends the Phase I and previous work in two major
areas; developing a SAW strain sensor, and dramatically increasing
interrogation range, which is applicable to both the new strain sensors
and the previously developed temperature sensors.  In order to increase
SAW sensor range, sensitivity and accuracy, the most important device
parameters were identified and initial investigation begun in Phase I
and will be put into practice in Phase II. To reduce SAW sensor loss and
minimize multi-transit acoustic echoes, low loss unidirectional studies
were initiated.  Phase I produced three alternative low-loss approaches
that will be evaluated in the Phase II work.  Success will lower the
insertion loss by approximately 15 dB, and multi-transit echoes are
predicted to be less than -40 dB from the main signal; doubling the
system range and reducing the sensors self-noise.  Advanced coding
techniques were investigated in Phase I that have led to longer delay
path lengths, and shorter codes with less inter-sensor  interference.
During Phase II, the interrogator will improve the following critical
capabilities: onboard-fully-integrated DSP, extended connectivity
options to customer's computer, and rapid interrogation capabilities.
This will allow vibration sensing and signal integration.
The Area-I team has developed and flight tested the unmanned Prototype-Technology Evaluation and Research Aircraft or PTERA ("ptera" being Greek for wing, or wing-like). The PTERA flew successfully during Phase I of this program, and stands to enhance the already capable NASA Aeronautics Test Program (ATP) by enabling the low-cost, low-risk, flight-based evaluation of everything from advanced aerodynamic treatments to control systems and sensor payloads. The PTERA will bridge the gap between wind tunnel testing and manned flight testing to greatly reduce technology development time, cost, and risk. This work seeks to further mature the PTERA system through rigorous flight testing and will begin the integration of the PTERA into the NASA ATP through the delivery of a new PTERA baseline system to NASA. Several core capabilities that the PTERA would bring to the ATP include:
1)	A low-cost, low-risk flight test facility that can be used to expand ATP's role in the testing and validation of NASA's physics-based multi-disciplinary analysis and optimization (MDAO) tools
2)	The ability to flight test advanced aerodynamic treatments, health management and control systems, and to perform experiments in structures and aeroelasticity for a fraction of the cost of a manned flight test program.
3)	The ability to flight test cutting-edge and complex systems whose cost and risk are too high for manned flights.
4)	A testbed with modular airframe that enables the evaluation of multiple technologies with the same airframe.
5)	A testbed with a large payload capacity that facilitates the inexpensive and risk-mitigating flight test evaluation of a wide array of sensors and payloads as well as the evaluation of flight-test measurement systems before they transition to manned programs.
6)	The ability to perform unmanned, autonomous, flight experiments relating to the burgeoning field of autonomous unmanned aircraft, including experiments supporting UAS integration into the NAS.
A Space Communications and Navigation (SCaN) flight experiment will demonstrate Next Generation Navigation Techniques and Advance SDR/STRS Communications Technology to TRL-7.  Scintillation-hardening techniques will be applied to an open-source waveform ported to the SCaN platform.  This will result in improved GPS navigation during geomagnetic storms.

The ported waveform will be STRS-compliant and open source.  It will provide a validation of the STRS architecture and software defined radio technology for space applications.  While operational, the waveform will autonomously detect scintillation and automatically switch into a data collection mode for relaying the GPS samples to the SCaN avionics subsystem for later transmission to White Sands.

The open-source, STRS-compliant waveform software and GB of GPS scintillation data will be enduring products of the flight demonstration.  The STRS infrastructure will be expanded with the STRS tool kit produced during this project.  The STRS tool kit will be similar to the OSSIE tool kit for the SCA, providing automatic code generation of STRS wrappers and interfaces.  An eclipse-based framework will provide drag-and-drop of components for developing STRS-compliant software.
Since Mars rovers have limited life span, NASA wants to maximize the exploration activities during this period. Rock sample analysis is one of the main tasks of rover missions. Traditionally, rock selection is decided by human operators. Due to long communication delay, manual selection process is time-consuming. There is a strong need to develop an automatic software system to automate the process. 

We propose a novel and high performance approach to enhancing rock selection process. We explicitly take advantage of the availability of LIBS instrument in the new generation of Mars rover. First, we use LIBS to quickly sample the neighborhood of the rover. LIBS can collect samples in seconds.  Our software algorithms can quickly analyze the LIBS data and determine whether there are any interesting chemical elements. If yes, the APXS instrument will be activated. Otherwise, the rover will move to a new location and start the process again. In Phase I, we have demonstrated that our smart processing tools using actual Mars data and our results are more consistent than a current method. Moreover, our tools can implemented in a parallel processing system to achieve real-time performance. Our parallel processing system utilizes multi-core CPUs for distributed processing and we have used such processing architecture for speech and genomic processing.
In response to Topic S3.04 "Propulsion Systems," Busek Co. Inc. will develop a high throughput Hall effect thruster with a nominal peak power of 1-kW and wide throttling range in terms of both power and Isp.
  
In Phase I the preliminary thruster design was completed.  Project activities focused on achieving a magnetic field that shields the discharge channel from ion induced erosion.  The goal is to achieve a propellant throughput greater than 100 kg/kW.  Numerical modeling is playing a critical role in the thruster design.  In Phase I, we used a fluid based code developed by JPL to model the plasma in an existing thruster that is currently undergoing life testing.  The erosion predictions of the model were found to agree well with actual measurements.  The numerical model was then applied to the magnetically shielded 1-kW thruster and preliminary results were found to be reasonable.  The goal is to demonstrate a thruster design where channel erosion is entirely eliminated as a life limiting mechanism.

In Phase II, we will build and test the extended lifetime thruster.  The performance, lifetime, and plume properties of the thruster will then be evaluated, and the design will be optimized.  Numerical modeling will be used throughout the process to ensure that magnetic shielding is achieved.  Code predictions will be grounded in plasma measurements taken with a variety of diagnostics including channel wall probes, high speed intrusive channel probes, and plume probes.  The ability of the thruster to achieve its lifetime goals will be assessed through a 500 hour wear test.  When the design is finalized, an engineering development unit (EDU) thruster will be designed, built, validated, and delivered to NASA.  The EDU thruster design will be modeled thermally and structurally to facilitate the transition to Phase III.  At the end of the Phase II, the TRL will be 5/6.
Orbital Research proposes to develop, build and test 3 additional high temperature components for use in the design of a Data Concentrator Module in distributed turbine engine control at high temperatures.  The concentrator receives analog and digital signals related to turbine engine control and communicates with a FADEC or high level command processor. This data concentrator follows the road map put forth by DECWG for use in creating a demonstration platform for turbine engine distributed controls communication development that operates at temperatures at least up to 225C.

Phase I was the development of detailed specifications for each component needed for the system, as well as to define the total system specification.  This entailed a combination of system design, compiling existing component specifications, laboratory testing, and simulation.  The results showed the feasibility of the data concentrator.

Phase II of this program will focus on three key objectives:
The first objective will be to update Data Concentrator design modifications from DECWG and Prime Contractors.  Secondly, to define the requirements for the three new high temperature ASICs.  Finally to validate each design by testing over temperature and under load.
In Subtopic X11.01, NASA has identified the need to develop advanced radiation-shielding materials and systems to protect humans from the hazards of space radiation during NASA missions.  The radiation components of interest include protons, alpha particles and heavy ions from galactic cosmic rays, protons and other ions from solar particle events, high energy electrons and neutrons, and high-energy electromagnetic radiation.  International Scientific Technologies, Inc., in conjunction with the College of William and Mary, proposes to raise the technology readiness level of selected polymeric radiation-shielding materials through participation in the Materials on the International Space Station Experiment program, named MISSE-X.  The Phase I SBIR program demonstrated the feasibility of developing a flight-qualified Technology Demonstration Experiment to be carried on board the ISS as part of a MISSE-X payload to facility Technology Infusion.  Phase II Technical Objectives will include specification and fabrication of polymeric materials to shield astronauts and sensitive electronic equipment, acquisition and test of detectors/dosimeters suitable for measurement of total ionizing dose, design, construction, test and optimization of an experimental package compatible with the guidelines and specifications of the MISSE-X program, and field testing and integration in conjunction with NASA personnel and NASA contractors.  The anticipated result of the Phase II program is the delivery of an experiment package for MISSE-X.
Extensive human-in-the-loop testing of NextGen concepts and technologies is typically required in a controlled lab environment before they can be integrated for evaluation in the field. The experiments tend to require the participation of a large number of subject-matter experts (SMEs) including air traffic controllers (ATC) and (pseudo-)pilots, which makes the experiments costly and the logistics with so many participants make them difficult to plan. These experiments often are designed only to collect data from either ATC or the pilots, but not both; the counterpart is needed only to provide realism in communication between them. The proposed research will develop a Speech-Enabled Simulation Interface Agent (SESIA) to replace the non-essential human subjects in these experiments. SESIA can interact with the SMEs through voice communication, and interface with the simulation platform to perform the intended control. It has the benefit of reduced cost associated with the experiments and increased convenience in their planning, thus allowing the opportunities to schedule additional testing. In cases where a pseudo-pilot would normally represent multiple flights and communicate to the ATC with the same voice for all flights, SESIA will actually increase the realism of the experiments by allow different voices to be synthesized to simulate different pilots.
Modern flight-critical systems include hundreds of thousands to millions of lines of code.  The Boeing 777, for instance, includes over 2 million lines of code.  Future projects will only feature an increasing amount of source code, mostly written in the C programming language.  The only way to completely ensure the safety of flight critical systems is through static, formal program verification.  In order to effectively verify such large programs written in the C programming language, we propose a scaleable system for the verification of program written in C based on matching logic, or program verification logic.  Matching logic has the benefit of being more scaleable than traditional Hoare/seperation logic verifiers because they build a large first order logic proof goal for entire functions at a time, while matching logic proceeds in program order, proving goals incrementally.  Additionally, matching logic verifiers are based on operational semantics of the programming language in question.  Operational semantics offer the benefit of being fully executable, so that one may increase belief that they are correct by testing typical compiler test suite programs, such as the GCC torture tests for the C language.  Ultimately, our proposed research will result in a verifier that is both more scalable and more trustworthy than the competition.
The Phase 2 effort will be used to advance the material and design technologies that were explored in the Phase 1 study of hybrid gears. In this hybrid approach, the conventional metallic web is replaced with a composite element. This alternative design generates a significant weight reduction and the potential for the reduction of noise and vibration.  The Phase 2 program will make the first large scale hybrid gears that can be run in a rotating gear rig with imposed torque loading. Several full scale gears will be made as well as full scale test elements. Test results from full scale testing will be applied to computer simulation models. This effort will apply topology optimization techniques to predict the best design of the gear elements. This should enable significantly more efficient designs than those fabricated and tested in the Phase 1 program. This program will also explore a power transmission system that integrates gear and shaft into a single structure. It is hoped that this integrated system will benefit weight, noise and tolerance of misalignments.
An orifice element is commonly used in liquid rocket engine test facilities to provide a large reduction in pressure over a very small distance in the piping system.  Orifice elements are used in propellant lines, feed systems, plume suppression systems and steam ejector trains. While the orifice as a device is largely effective in stepping down pressure, it is also susceptible to a wake-vortex type instability and cavitation instability that propagate downstream and interact with other elements of the test facility resulting in structural vibration. In this proposal a new proprietary instability mitigation device has been developed that steps down  the pressure, straightens the flow and suppresses all instability modes. The device is scalable and can be used for different mass flow rates and varying levels of de-pressurization conditions. It is relatively inexpensive to manufacture, easy to fabricate and install, and can be tailored to meet the performance requirements of a given facility. In Phase I, the device has been successfully demonstrated in a sub-scale cryogenic test facility. In Phase II the performance of the device will be calibrated  for full-scale operation in a cryogenic test facility and a water test facility.
Michigan Aerospace Corporation proposes to develop an integrated LIDAR instrument capable of identifying icing conditions while also providing air data sensing capabilities. The resulting Raman Icing Detection System (RIDES) will be an integrated air data sensing and icing condition detection instrument, providing a backup to the Pitot tubes potentially affected by icing, thus providing redundancy for critical information. The proposed solution will operate without protrusions into the flow, behind a flush mounted window on the skin of the aircraft, mitigating the risk of ice build-up during operation.  This project will utilize MAC's extensive heritage of rugged LIDAR system design and construction.
New aircraft designs depend on an integrated active approach to flight control, flutter suppression and structural mode attenuation to meet desired handling quality performance and gust load alleviation. Tao Systems will team with Professor Gary Balas at the University of Minnesota to (1) develop a robust controller that demonstrates improved aerostructural performance over current state-of-the-art techniques by utilizing a novel aerodynamic load sensor, and (2) provide a robust linear parameter varying controller that (a) requires no ad hoc methods of gain-scheduling, (b) provides robustness guarantees  that more traditional methods do not offer, and (c) allows for explicit rate bounds enabling less conservative, higher performing controller designs. The benefits include improvement of aerodynamic and structural efficiency using robust aeroservoelastic control methods over a range of flight speeds, in the presence of significant turbulence.
In the proposed Phase II program, we will transition MicroLink's 6-inch epitaxial lift-off (ELO) solar cell fabrication process into a manufacturing platform capable of sustaining large-volume production.  Key Phase II improvements in the ELO process are reduction in cycle time and increase in the yield of large-area devices.  In addition, we will transition all critical device fabrication processes to 6-inch production tool sets that are designed for volume production, with an emphasis on automated cassette-to-cassette and batch processes that will minimize operator dependence and variability.  During the Phase II program we will establish a pilot production line capable of at least 1500 6-inch wafers per month at greater than 80&#37; yield. We will also increase the yield and manufacturability of the 6-inch reclaim process, which is crucial to reducing the cost of the cells.  This will involve a closer collaboration with our substrate reclaim vendor and the establishment of clear metrics to qualify key process variables impacting device yield.  A successful conclusion of this Phase II program will place us in strong position to support potential SEP volume solar cell manufacturing requirements.
The objective is to produce high efficiency DC/DC power modules in a small low profile package that can tolerate extreme environment conditions.  The primary effort of the Phase II program is to address the need for very high performance power electronics that meet a combination of high radiation tolerance, high thermal tolerance and extremely low EMI susceptibility/radiation. The power modules incorporate several radical new advances in power design including ceramic cores and quasi-linear circuitry.  The program will exit with such modules having been verified for thermal vacuum and electromagnetic (susceptibility and radiation) performance of modules that can tolerate &gt;0.3Mrad and &gt;200C operation with negligible electromagnetic coupling and extremely high electrical isolation.
In Phase I project, by leveraging on Agiltron's experience in optical fiber components and our unique fabrication procedure of fiber array, we successfully designed and fabricated the samples of the gradient index fiber (GIF) lens arrays and single mode (SM) fiber arrays for composing a coherent single-mode fiber (SMF) spatial filter array (SFA), which demonstrated the promising results to meet NASA's requirements for the applications in planet exploration. This novel GIF and SMF array based SFA has several advantages over the current approach in small aberration, low insertion loss, high uniformity, high robust and stability.  

In Phase II, Agiltron will further improve and optimize the fabrication procedure to make the prototype of GIF and SMF array based SFA for NASA applications. This SFA prototype will have more than 1000 effective fiber counts in the requested aperture. Furthermore, the improvements of precision fabrication procedure developed in Phase I will assure that center-to-center deviation in GIF and SMF arrays' deviation is less than +/-0.2?m. At the end of the Phase II, the novel SFA prototype will be provided with fully function integration and environmental test to insert into the experiment system of NASA for further comprehensive evaluation.
High-performance HDTV cameras are commercially widespread, but are not presently available in radiation-hard versions. The objective of the proposed SBIR effort is to develop and commercialize a radiation-hard, high-performance HDTV sensor for NASA missions and other space-based and high-energy physics applications. Key features of this program are the use of radiation-hard, fully depleted silicon photodiodes to maximize quantum efficiency, and the use of both radiation-hard-by-process and radiation-hard-by-design strategies in the development of the highly integrated readout circuit.
We will develop an efficient Graphics Processing Unit (GPU) based parallel Binary Decision Diagram (BDD) software package, and will also combine it with our GPU-based parallel SAT solver that we are currently developing in a NASA SBIR Phase II project in order to solve much larger and more complex Boolean formulas from formal verification than possible with either method alone. BDDs are a data structure that satisfies some simple restrictions, resulting in a unique representation of a Boolean function regardless of its actual implementation. This property of BDDs allows the efficient solution of many problems. The proposed tool will exploit multi-core CPUs and the thousands of stream cores in the latest GPUs, which were made accessible to programmers through specialized software development kits. These large numbers of stream cores in GPUs, and the possibility to execute non-graphics computations on them, open unprecedented levels of parallelism at a very low cost. In the last 8 years, GPUs had an increasing performance advantage of an order of magnitude relative to x86 CPUs. Furthermore, this performance advantage will continue to increase in the next 20 years because of the scalability of the chip manufacturing processes. The technical objectives will be to efficiently exploit the GPU parallelism in order to accelerate the execution of our prototype GPU-based parallel BDD package, and to implement hybrid approaches combining it with our GPU-based parallel SAT solver. BDDs and SAT solvers are orthogonal methods with different advantages, and a hybrid of the two will significantly increase both the speed and capacity when formally verifying complex software for space missions. We achieved at least 2 orders of magnitude speedup with our prototype GPU-based parallel BDD package in a previous Phase I, and expect to achieve at least 4 orders of magnitude speedup with our hybrid BDD-SAT tool by the end of Phase II, compared to the current state of the art.
During Phase I of this effort, ZONA Technology, Inc. significantly improved the medium fidelity design and analysis capability of NASA's MDAO architecture by successfully adding ZONA CAE tools such as ZAERO, ZEUS, ASTROS and ZMORPH synergistically integrated within a ModelCenter MDAO framework. In Phase II of this effort, ZONA aims to improve all the three tiers of NASA's MDAO architecture as follows: (1) The low fidelity capability will be enhanced by incorporating ZONAIR for providing flight loads (for structural design) and pressure differential (for sonic boom mitigation). ZONAIR will also 'flexiblize' rigid CFD loads for aeroelastic analyses, (2) the medium fidelity capability will be further extended by addition of new ModelCenter plug-ins and improvements in the existing plug-ins for ZONA CAE tools, for facilitating ease of design process, and (3) the high fidelity analyses capability will be augmented by the development of supportive software offering beneficial features such as automated surface+flowfield mesh morphing/generation, commonality of input within all branches of fidelity, etc. Rapid shape sensitivity generation capability will be offered with incorporation of ZEUS-DO into the framework. For ease of model-making and input setup process, a pre/post-processor software called ZONA-MV will be further improved with linkage to NASA's VSP tool. A NASTRAN-to-ASTROS finite element model converter will be developed. The overall development outcome of Phase I+II effort will then be combined as a 'ModelCenter.ZONA MDAO Pak' with on-demand cloud computing ability, unlimited tokens for massively parallelized optimization efforts, and will be perpetually licensed within all NASA Research Centers.
Working with our System Integrator partner (ITT-Exelis) and Richard Lyon (NASA/GSFC Principal Investigator Compact Achromatic Visible Nulling Coronagraph Technology Maturation) and his telescope expert Lee Feinberg, Trex will perform a preliminary design of a 1-meter aperture, ultrastable, UVOIR telescope made using Trex Chemical Vapor Composite Silicon Carbide (CVC SiC&amp;#153;). The highly athermal silicon carbide telescope provides an affordable solution for the Balloon Exoplanet Nulling Interferometer (BENI) Mission to qualify the VNC, with traceability to the requirements of the ATLAST observatory. 
Trex also proposes to demonstrate replicated, powered CVC SiC&amp;#153; substrates using a new, polishable graphite mandrel material which allows the release of our CVC SiC&amp;#153; deposit from the mandrel with a spectral finish. The new process eliminates rough and fine grinding of the optical surface, which is directly ready for fine lapping and polishing.  The payoff will be at least a factor of 2X reduction in the areal cost of high performance CVC SiC&amp;#153; mirrors, with an associated reduction in schedule on the order of 6-months. Using meniscus mirror designs for lightweighted mirrors in the telescope, rather than a web-based isogrid design, will also reduce the cost and schedule for CVC SiC&amp;#153; mirrors, while not sacrificing weight or stiffness.
Nearly all mechanism applications require some form of gearbox.  Wet lubricated gearbox technologies are limited to the relatively narrow temperature ranges of their lubricants.

Dry lubricated gearboxes have proven to be problematic with poor life and reliability characteristics.  Testing has shown that dry lubricated rolling elements can be made to work reliably provided they are operated at conservative contact stresses, however when dry film lubrications are tested under the sliding conditions in conventional transmissions they are no longer reliable. 

During the Phase I SBIR Rocketstar Robotics developed the preliminary design of a transmission that consists of all rolling elements and has eliminated all of the sliding elements that exist in conventional gearing.  The transmission operates at contact stress values that are conservative and within the envelope proven through previous testing to provide reliable performance in rolling elements.  The resulting transmission can be provided in a range of sizes and offers considerable torque capability within a reasonable envelope while operating within conservative rolling contact stress regimes at operating temperatures from near absolute zero to over 500C.

The development and test of a successful prototype could revolutionize the torque transmission industry and open the door to mechanisms operations over a much broader temperature range than is now possible.   Rocketstar Robotics proposes that the design be carried through the detailed design phase which includes detailed analysis models and that multiple prototypes be built of two different size transmissions.  The units would then be tested for performance and life over the extremes of temperature from near cryogenic to 500C operation.

Rocketstar will build 3 small 100 in-lb units and 3 large 400 in-lb units for testing along with spare splines to allow development testing with multiple DFL types.  One of each unit will be delivered to NASA.
Hybrid turboelectric aircraft with gas turbines driving electric generators connected to electric propulsion motors have the potential to transform the aircraft design space by decoupling power generation from propulsion.  Resulting aircraft designs such as blended-wing bodies with distributed propulsion can provide the large reductions in emissions, fuel burn, and noise required to make air transportation growth projections sustainable.  The power density requirements for these electric machines can only be achieved with superconductors, which in turn require lightweight, high-capacity cryocoolers.  We have developed a Cryoflight turbo-Brayton cryocooler concept that exceeds the mass and performance targets identified by NASA for superconducting aircraft.  In Phase I of this project, we extended our initial design study and developed modeling tools to support system-level optimization and individual component designs.  We focused on the critical component for mass reduction &amp;#150; the recuperative heat exchanger &amp;#150; and performed risk reduction activities to demonstrate the feasibility of our concept for this component.  In Phase II, we will design, build, and test two compact lightweight, high-performance recuperators for the Cryoflight cryocooler.  This development effort will provide an enabling technology for the superconducting systems needed for hybrid turboelectric aircraft to be feasible.
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 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 interest under this NASA sub-topic is the development of Lidar systems capable of detecting and measuring aircraft wake vortices in order to enhance aircraft separation criteria. To perform this task well a Lidar must have certain characteristics and be paired with a highly optimized wake processing algorithm.  Key areas of development include:
- Pulse energy / pulse repetition frequency (PRF) combination to adequately sample a region of space containing the wake vortices. 
- Pulse width for optimally sampling the wake disturbance. Determination of the optimal range resolution for measuring wakes is algorithm dependent and is an area of current research.  
- Scanner capable of efficiently scanning the region of interest.  The scanner needs to be able to report the elevation and azimuth accurately so that wake positions can be estimated.
- Raw data acquisition and signal processing for generating range resolved Doppler spectral estimates. Processing should produce periodograms over the 2D or 3D region of interest with adequate frequency resolution, velocity bandwidth and with minimal distortion.  
- Wake vortex algorithm for detecting, tracking and estimating the circulation strength and position of the vortices from the Doppler spectral estimates.
SIBELLOPTICS proposes a Phase 1 SBIR to determine the feasibility of its compact, innovative fiber LIDAR sensor, now in Phase II development, to detect and measure wake vortices using spatially dependent spectral matched filter algorithms similar to those currently being developed for NASA by Coherent Research Group.
We propose to build a compact, high-precision single-axis accelerometer based on atom interferometry that is applicable to operation in space environments. Based on our successful Phase I design, the proposed accelerometer emphasizes reliable operation and exceptional acceleration sensitivity. It incorporates several innovative features that make it appropriate for a variety of space-based and terrestrial applications. 

Phase II will result in a completed sensor build, including a sensor head, laser system and electronic control system.

Space-based inertial sensors based on atom interferometry are a compelling technology for both technological and scientific applications because of the exceptionally high performance that can be enabled by long interrogation times with cold atoms in a microgravity environment.
The requirement for cost effective manufacturing and metrology of large optical surfaces is instrumental for the success of future NASA programs such as LISA, WFIRST and IXO(now NGXO). OptiPro's UltraForm Finishing (UFF) is a sub-aperture compliant wheel and belt type polishing process for rapid material removal from the ground state to a finished optic. The UFF removes residual grinding sub-surface damage, mid spatial frequency errors, and provides the mechanism required for surface corrections. OptiPro's technologically advanced optical manufacturing capabilities along with a support partnership with the University of Rochester Mechanical Engineering Department and the Penn State EOC, gives us a very strong team and a clear path towards solving the difficult problems associated with, grinding, polishing and metrology of large complex optical surfaces. The UFF, with its 5-6 axis of motion provides a platform to polish traditional flats and spheres as well as aspheres and freeform shapes. The UFF was designed for deep concave shapes and it is suitable for finishing conformal optics. The Proposed Phase II will include further development on UFF using a 200 mm x 200 mm fused quartz mandrel to optimize the process to meet NASA's X-ray optical requirements. Grinding development will also be performed on OptiPro's eSX platforms to minimize material removal required during polishing. The part geometry will be measured by a non contact optical probe using OptiPro's UltraSurf free-form measurement system. Once development is complete, OptiPro will work on the mandrels that will be supplied by Goddard Space Flight Center to attempt to correct the form error on those surfaces. OptiPro will also build and install a 6-axis UFF machine to NASA. The UFF platform will be used for development during the Phase II effort, and installed at NASA at the end of the contract.
We propose to develop an efficient, tunable Q-switched SSL operating at a wavelength of 1651 nm with pulse energy &gt;1 mJ at 2000 Hz repetition rate with in-band laser diode pumping. We will leverage initial work carried out during Phase I of this program to pursue two approaches:  (i) a tunable injection-seeded Q-switched SSL, and (ii) a regenerative power amplifier. In Phase I, we investigated a variety of gallium garnet gain media &amp;#151; including comprehensive characterization of absorption and fluorescence spectra &amp;#151; and we have identified the most promising prospective crystals for 1651 nm emission.  We have also demonstrated sufficient tunability to enable differential path LIDAR techniques for the detection of methane.
We propose to develop a 3064 actuator, continuous facesheet MEMS deformable mirror using a modified fabrication process that will eliminate mid-spatial frequency surface figure errors resulting from actuator "print-through" topography and stress-induced mirror scallop topography. These figure errors, which occur at spatial frequencies outside the DM control band, are the most significant technological development hurdle preventing the use of MEMS DMs in proximity glare suppression for astronomical coronagraphy. Such wavefront control devices fill a critical technology gap in NASA's vision for high-contrast, high-resolution space based imaging and spectroscopy instruments. Space-based telescopes have become indispensible in advancing the frontiers of astrophysics. Over the past decade NASA has pioneered coronagraphic instrument concepts and test beds to provide a foundation for exploring feasibility of new approaches to high-contrast imaging. From this work, NASA has identified a current technology need for compact, ultra-precise, multi-thousand actuator DM devices. Boston Micromachines Corporation has developed MEMS DMs that represents the state-of-the-art for scalable, small-stroke high-precision wavefront control. The emerging class of high-resolution DMs pioneered by the project team has already been shown to be compact, low-power, precise, and repeatable. These DMs can be currently produced with uncorrectable shape errors as small as 10nm root mean square (rms). The residual shape errors on the DM are mostly periodic and act essentially as a grating, producing diffraction spikes in the image plane. In the Phase I effort, DM fabrication process modifications were developed which will enable the manufacture of these enabling components with an unprecedented surface figure of less than 2nm rms by eliminating surface features resulting from print-through , etch access holes, and mirror attachment posts, and compensating for residual stress induced scalloping.
MetroSim is a Metroplex-based arrival, departure, and surface optimization.  Linking with both the NASA-developed Traffic Management Advisor (TMA) tool as well as the NASA-developed System Oriented Runway Management (SORM) tool, 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 weather forecasts. To accomplish all these goals simultaneously, the MetroSim architecture contains a collection of different tools, some of which are simulations, some of which are physics-based computations, and some of which are mathematical optimization calculations.  These tools all interoperate in a distributed computational environment to provide real-time airport planning and optimization at the Metroplex level for all operations&amp;#151;arrivals, departures, and surface movements.  The type of each tool is chosen to be the best and fastest at what it is required to compute.
The protocols needed to coordinate the activities of distributed components, such as consensus algorithms, are notoriously difficult to design, implement, and verify.  Abstraction is the only way to gain intellectual control over this complex problem; so ATC-NY and Cornell University have developed Event Logic, a high-level model for describing and reasoning about distributed systems, and EventML, a high-level functional language for implementing distributed protocols by "programming with events."   Properties of EventML protocols can be formally verified by interactive theorem proving in the Nuprl environment.  To integrate these conceptual tools with standard processes of system development, and to make the labor intensive task of verifying protocol properties more efficient, ATC-NY is developing Emile.  Emile is a software tool that provides: a semantic interface to EventML that translates assertions about properties of EventML programs into logical forms to which powerful fully automated analysis tools can be applied, along with a "logical manager" that can direct analyses involving the interaction of these tools.  We will demonstrate Emile by using it to verify the key properties of EventML source code for standard consensus algorithms, such as Paxos.
In Phase 1, Intelligent Fiber Optic Systems Corporation (IFOS), in
collaboration with North Carolina State University, successfully
demonstrated a Fiber Bragg Grating (FBG)-based system for simultaneous,
continuous, multipoint temperature measurements at different depths in a
representative Thermal Protection System (TPS) material (Super
Lightweight Ablator  SLA), with testing performed near its char
temperature. Special high-temperature FBG sensors were also developed
and tested to 1000C with an applied 7 kpsi tensile stress, and with an
applied 18 kpsi after cooling to room temperature.  A pure thermal
loading calibration of these sensors in this temperature range was
performed. The response of the FBG sensors was much faster than that of
thermocouples, and all electrical wires were replaced with a single
optical fiber. In Phase 2, IFOS will embed 1000 C-capable optical fiber
sensors into a TPS material. Following an appropriate instrumentation
development, we will demonstrate temperature profile measurements with a
depth resolution of 250-m or better. We will also distinguish between
temperature- and strain-induced responses in the FBG sensors, a critical
consideration for embedded sensor arrays. Our Phase 2 base work plan is
designed to advance the TRL to 5, with TRL 6 being obtained in a Phase
2-E program.
NASA's Space Communications and Navigation (SCaN) roadmap, calls for an integrated network approach to communication and navigation needs for robotic and human space exploration missions, from near-Earth to planetary missions. Anytime, anywhere connectivity for Earth, Moon and Mars is a stated goal, with high-bandwidth optical relay crosslinks for Earth, Moon, Mars and planets. Laser based optical communication links for space provides more than an order of magnitude higher data rates than corresponding RF links.. In addition, this is achieved with much smaller size, weight &amp; power (SWaP) burden to spacecraft payloads, making spacecraft resources available to enhance or extend science missions, and the overall mission productivity. Tremendous progress made in 1.5um &amp; 1-um fiber-optic fiber laser/amplifier technologies, their power scaling, and availability of reliable high-power components, makes such transmitters feasible for space mission application. In this SBIR proposal, we propose to develop 1.5mm fiber-amplifier based laser transmitters, with Pavg&gt;4W, and compatible with a variety of M-ary PPM formats, that have a clear path to a space-qualification roadmap. In addition, power-scaling to 10W, athermal operation over a wide temperature range (with passive conductive cooling only), and improved power efficiency, are simultaneously addressed. Limited scope qualification tests relevant for space environment will also be conducted. These activities leverage prior and ongoing related activities at Fibertek, on high-performance, high-reliability fiber laser transmitters.
NASA has a critical requirement for a neurodiagnostic tool that can be used to monitor the behavioral health of the crew during long duration exploration missions. The device should unobtrusively monitor and classify neurophysiological markers associated with decrements in behavioral state and cognition. The neurodiagnostic monitor should be lightweight and compact and should require minimal time or effort for the crew to use. The device should be unobtrusive enough to allow mission operations to be performed during monitoring. In Phase 1 of the program, we were able to successfully monitor cortical activity using multi-parameter sensor modules. In addition to electroencephalography (EEG) and functional near infrared spectroscopy (fNIRS) signals that provided the electrophysiological and cortical oxygenation information, we were able to obtain photoplethysmography (PPG) and electrooculography (EOG) signals to compute the heart rate and frequency of eye movement. In Phase 1 we also demonstrated the functionality of an algorithm that automatically classifies the varying degrees of cognitive loading based on the measured physiological parameters. In the proposed Phase 2 program, we will develop a flight-capable neurodiagnostic device that can be unobtrusively worn on the head. Based on the neuro and non-neurophysiological parameters obtained from the multi-modality sensors, we will detect and classify neurophysiological markers associated with decrements in behavioral state and cognition. We will develop an automated algorithm that can recognize and identify key decrements in behavioral state.
Made in Space has completed a preliminary design review of the Additive Manufacturing Facility. During the first half of Phase 1, the design went through conceptual development, simulation testing, cost analysis, and comparison testing of which off-the-shelf parts can be used. The deliverables for Phase I include a written report detailing evidence of demonstrated technology (TRL 5) in the laboratory and will outline in detail the path taken toward hardware demonstration for Phase II (TRL 6). The preliminary design is ready to be manufactured as an engineering test unit in Phase II. A feasibility study was created to demonstrate what could be fabricated for the inside of the ISS (parts and spares) and for the outside (possible satellites). It is anticipated that many of the sample uses that the AMF will make possible on-orbit have not yet been envisioned.
The U.S. portion of the International Space Station (ISS), which has been designated by Congress as a National Laboratory, holds great potential for a broad spectrum of researchers who are eager to take advantage of its unique scientific research facilities. The Light Microscopy Module (LMM), which was developed and is being managed by the NASA Glenn Research Center (GRC), is one such facility currently operating and producing fascinating results on ISS. LMM will yield even more astonishing results with the addition of enhancing subsystems. Techshot is currently developing one such subsystem, the LMM-Dynamic Stage (LMM-DS), which will satisfy a host of new experiments proposed for LMM. However, GRC has many more researchers awaiting the ultimate enhancing subsystems for conducting colloid science experiments in the LMM that could lead to new advanced materials with significant commercial potential. Capitalizing on Techshot's rapid progress with the LMM-DS, the company's vast array of mixing and separations technologies, and its extensive experience with microfluidic systems, a series of Colloid SPEcialty Cell Systems (C-SPECS) will be developed by Techshot for use in the LMM-DS. These innovative low-volume mixing devices will enable uniform particle density and remotely controlled repetition of LMM colloids experiments. In addition C-SPECS will minimize crew time, as well as avert the need for multiple, costly colloid samples that are expended after only one examination. C-SPECS are vital analytical microgravity research technologies that will greatly enhance the capability of the LMM, thereby enabling ISS to become even more effective as a national laboratory.
In the proposed project, we will formally verify the correctness of the interaction between a Real-Time Operating System (RTOS) and user processes under various operating scenarios, such as multitasking, interrupt handling, user and kernel mode switching. The formal verification will be done assuming execution on the PowerPC 750 architecture that is implemented in the radiation-hardened RAD750 flight-control computers utilized in many NASA space missions, and are planned to be used in future spacecraft, including the Orion Multi-Purpose Crew Vehicle. A unique advantage of our project will be that the formal verification will precisely account for the bit-level semantics of all instructions, as well as the memory system, the bus, and devices on the bus, including multiple CPUs, and thus will allow us to precisely analyze all possible behaviors of the entire system, which is critical for aerospace applications.
During Phase I we will lay the foundation for Phase II by: developing initial models of the memory system and the bus; formally defining the bit-level semantics of additional instructions from the PowerPC 750 architecture that we have not specified yet; identifying properties that we will prove to guarantee correct interaction of user processes with the target RTOS, the memory system, and the bus, including scenarios such as multitasking, interrupt handling, user and kernel mode switching; proving some of these properties; and identifying the most promising directions for Phase II work.
We propose to design and develop VDM/RP, a visual data mining system that will enable analysts to acquire, store, query, analyze, and visualize recent and historical robot performance data. During mission operations, these capabilities will enable operators to more quickly and accurately detect and interpret data patterns that support or rebut candidate diagnoses or hypotheses about robot problems. During robot system development and experimentation, VDM/RP will enable analysts and robot designers to review robot test data to create and refine models that specify quantitative relationships among robot system health and status variables that hold for nominal and off-nominal modes.  Key innovations include interactive arrays of timelines and graphs for visualizing multivariate, time-oriented data, temporal queries to search for significant data patterns, and intelligent assistance to simplify user selection of data, analyses, and visualizations. During Phase I, we prototyped visualizations to analyze K10 rover LIDAR scan failures. During Phase II, we will develop three successively more capable versions of VDM/RP for test usage and evaluation by NASA's Intelligent Robotics Group.
Advanced trajectory design and estimation capabilities in complex nonlinear dynamical regimes represent two of the greatest technical challenges of modern space flight. The impact of nonlinear effects in both path planning and estimation is often most noticeable when the spacecraft under consideration transitions through a region of space where multiple exogenous perturbations become significant.  Perhaps the most salient example of such effects are libration point missions. To address these challenges, DECISIVE ANALYTICS Corporation seeks to advance the capabilities of NASA's open source General Mission Analysis Tool (GMAT) by integrating the latest advances in trajectory path planning and estimation, including multi-sensor data fusion. This includes the development of an advanced path planning capability that leverages concepts from dynamical systems theory, multi-phase targeting, and visualization for trajectory design in regions where multi-body effects are significant. Parallel to that, we are developing an advanced estimation capability that leverages approximately $10 million of research and development performed by DECISIVE ANALYTICS for the Missile Defense Agency (MDA) and the US Air Force. The capabilities sought during Phase II will leverage two GMAT prototype plugins, developed as part of the prior Phase I effort, that partially demonstrate some of the functionality proposed.
TDA Research, Inc. is developing a compact, low power, Next-Generation Exercise Device (NGRED) that can generate any force between 5 and 600 lbf. We use a closed loop control system and a servo motor to smoothly and accurately simulate the gravitational and inertial loads of lifting a weight on earth. However, because the system uses a computer-controlled motor, the load can be varied independently during the concentric and eccentric phase of the exercise. Thus, the system can easily provide an eccentric overload during the return stroke, greatly increasing the physiological benefit of a workout. 

The NGRED has a user-friendly interface where the exercise is selected from a drop-down menu, along with the desired weight and overload. The NGRED will automatically adjust to the user's stored range of motion (ROM) for the selected exercise and apply the set load only during the ROM. The NGRED automatically applies the eccentric overload at the top of the ROM and advances to the next rep at the bottom. The time required to change between users, exercises, and weights is less than 10 seconds. This makes much better use of the astronaut's time; with current mechanically adjustable exercise machines up to two thirds of the time is spent adjusting the machine. The software includes data logging and communication abilities to meet NASA requirements as well as redundant hardware and software fail-safe mechanisms.

The NGRED includes an efficient energy recovery system which stores the energy generated by the user during the concentric phase of the motion (pull stroke) and applies that energy to provide resistance during the eccentric phase (return stroke). The average power consumption of the NGRED will be less than 50 W during an exercise session. The expected weight of the NGRED at the end of Phase II will be 20 kg, and the total volume is expected to be 55 L, including all electronics and controls. A flight-like NGRED will be delivered to NASA at the end of Phase II.
Robots and rovers exploring planets need to autonomously navigate to specified locations.  Advanced Scientific Concepts, Inc. (ASC) and the University of Minnesota will develop a navigational system that employs an IMU and a 3D FLASH Lidar camera manufactured at ASC.  The system will furnish both the position of the rover and an elevation map of the terrain.  The map will be useful in detecting hazards to navigation both by rovers and during entry, descent and landing (EDL).  The algorithm is designed to function in real-time with the comparatively slow speed computers available in space by employing an advanced algorithm that makes efficient use of Lidar determined landmarks.  Those landmarks that only appear in a few images are not retained in the state vector, but nevertheless furnish constraints on the rover's pose for improving its state estimates.   Those landmarks that persist in many images are used for improving the accuracy of both the rover's state and the map at complexity only linear in the number of landmarks.  Significant components of this approach have enjoyed success in NASA tests in the Mohave Desert for EDL and have been assessed at level TRL 4.
NASA has an ongoing commitment to collect in situ data with a documented uncertainty in keeping with established performance metrics for vicarious calibration of ocean color satellite sensors. This proposal seeks funding to develop an in-water "Hybridspectral" capability that combines two differing practices for data collection (multiwaveband and hyperspectral) to satisfy the diversity, accuracy, and precision requirements of future ocean color missions.  Called the Compact Hybridspectral Radiometer (C-HyR), C-HyR places special focus on two important priorities from the call: 1) Instruments making measurements of the apparent optical properties; and 2) Hyperspectral radiometers (340 - 900 nm) for use in near-surface profiling.  The C-HyR system leverages a 2004 NASA SBIR microradiometer development that lead to the Compact-Optical Profiling System (C-OPS), a commercially available multiwaveband radiometer system and adds a spectrograph-based upwelling Radiance Collector Assembly (RCA) for operations very near the surface of the water at the top of a vertical profile.  In Phase II, attention will be paid to spectrograph selection with the goal of making optically valid measurements out to 900 nm, as requested in the call.  For improved deployment security and shadow avoidance, the system uses an innovative buoyancy backplane with twin positioning thrusters to ensure ship avoidance and allow maneuvering the profiler to a desired sampling location.  The result is an innovative expansion of existing state-of-the-art commercial instruments to include a spectral sampling capability that exceeds current and planned satellite requirements, and that can operate in optically complex near-shore regions.  The benefits of this new sampling capability are an improved ability to separate the biotic and abiotic components of seawater, an improved ocean color mission calibration and validation capability into Case 2 waters, reduced deployment effort, and reduced deployment risks.
High-power electric propulsion with Hall thrusters has been proposed as a strong candidate for Electric Path missions, but conventional power processing units (PPUs) are complicated and the mass of the discharge power converters needs to be reduced. Direct Discharge Power Processing Units (DDUs) have been proposed as an alternative due to their simplicity and low mass, but the achievable operating range of thrust and ISP is significantly limited because power regulation for DDUs is only achieved through gas flow control, array offpointing or shunting. This proposal presents a compromise between PPUs and DDUs called a Hybrid Direct Drive Power Processing Unit (HDDU) that provides a wider operating range than DDUs while reducing the mass and increasing the efficiency compared to conventional PPUs. An HDDU provides filtering like a DDU, but it can additionally raise or lower the discharge voltage over a limited range. An HDDU only processes the power necessary to raise or lower the discharge voltage. We propose using a soft switching non-inverting interleaved buck-boost circuit similar to what was built for Phase I, but with improved control circuitry and a modular chassis. Straight-through direct drive operation is possible by leaving the buck switches on continually while having the boost switches off.  The proposed HDDU would operate from an input voltage of 150 V to 300 V, and would provide 15 kW output power from approximately 200 V to 500 V. The HDDU approach is readily scalable to higher power levels by connecting modules in parallel because the proposed circuit naturally shares output currents. The HDDU will also include a digital control interface unit (DCIU), heater, keeper and magnet supply modules and driving circuits for a VACCO gas flow controller.  The DCIU will be controlled through a Windows GUI and a MIL-STD-1553 communication to USB adapter. The modular approach and enhanced operating range promote design re-use and reduce life-cycle costs.
The goals of reducing total cost and increasing reliability and safety of access to space continue to be top priorities for NASA.  The most immediate propulsion launch challenge involves increasing lift weight from 70 to 130 metric tons by developing the heavy lift Space Launch System (SLS).  Solid rocket motor analysis tools are needed to simulate ignition and propellant recession during the burn, but current models are limited in their ability to capture ignition transients or large grain deformations during motor operation.  We propose to advance propellant surface heating, ignition, and burning models as well as surface mesh recession algorithms to address a strong need for improved ignition physics and grain burn back and to deliver a unique and powerful software tool for current and next generation solid rocket motor simulations.  The Phase I products have already been fielded by NASA for ignition calculations involving the Launch Abort System Jettison Motor and RSRMV.  While these calculations are still in the preliminary stages, continued innovation of this successful technology strongly suggests that our research products will provide NASA with the important capability to simultaneously analyze solid propellant heat transfer, combustion, and grain burn back within a single framework.  Validation of the integrated tools to a TRL of 5 will be accomplished using available motor data provided by ATK while phased releases of the new software capabilities will allow NASA immediate access to incremental updates as soon as they are available.  Advancing this simulation capability will provide a large benefit to NASA because of its compatibility with NASA's mission and expertise.
HJ Science &amp; Technology, Inc. proposes to develop a novel high pressure "pump-on-a-chip" (HPPOC) technology capable of generating high pressure and flow rate on the microchip level.  When combined with a "valve-on-a-chip" (VOC) platform, HPPOC is naturally suited for NASA planetary science applications including on-chip HPLC sample manipulation and analysis.  In Phase I, we have established the technical feasibility of the technology by fabricating a set of HPPOC chips and successfully demonstrating the required maximum pressures and flow rates.  In addition, we have also established a novel HPPOC actuated VOC platform.  In Phase II, we will construct, test, and deliver a high performance and low power consumption microfluidic sample manipulation manifold prototype.  In particular, we will build an integrated on-chip HPLC buffer and sample injection pump and valve manifold specifically engineered to support the chip-based LC-MS research effort at GSFC.  In addition, the Phase II work will also be performed in parallel with efforts to develop such manifolds for the commercial analytical markets.
Understanding task performance and crew behavioral health is crucial to mission success and to the optimal design, development, and operation of next-generation spacecraft. Onboard resources, like a conventional 2D video camera, can capture crew motion and interaction; however, there is a critical need for a software tool that achieves unobtrusive, non-invasive, automatic analysis of crew activity from this footage.

The proposed automatic video-based motion analysis software (AVIMA) supports this R&amp;D effort by automatically processing and analyzing complex human motions in conventional 2D video without the use of specialized markers. Unlike many video analytics solutions, AVIMA goes beyond simple blob-based video analysis by tracking the geometric configuration of human body parts like the trunk, head, and limbs. This tracking enables human motion understanding algorithms to model and recognize complex human actions and interactions.

The resulting system will represent a substantial breakthrough providing benefits to an array of applications in video surveillance, human-computer interaction, human factors engineering, and robotics.
The Compound Specific Analyzer &amp;#150; Combustion Products, used on the International Space Station as a warning monitor of smoldering or combustion events, is being phased out of service.  Southwest Sciences Inc. proposes to develop a replacement laser-based analyzer using wavelength modulation spectroscopic absorption.  This device would be capable of real-time measurements of the four most important gases of interest (carbon monoxide, carbon dioxide, hydrogen cyanide, and hydrogen fluoride) at concentration levels relevant to pre-combustion events and with a 1 second response time.  This battery-operated device would be hand-held, use very little electrical power, and have a multi-year lifetime without the need for consumables, re-calibration, or maintenance, in contrast to the currently-used analyzer.

The Phase I research focused on what we believe are the most critical risks to using our approach.  All of these objectives were successfully accomplished, laying a strong foundation for continuation of the research in Phase II.  In Phase II, a fully functional prototype analyzer, meeting all of the requirements for operation in the International Space Station, will be built and tested.  Issues relating to space-qualification will be identified so as to ease the transition to Phase III and subsequent development.
The NASA's PATH mission includes the GeoSTAR satellite that carries aboard a microwave sounder employing an array of 375 microwave antennas with corresponding receivers. Each receiver is tuned to the 180GHz frequency, while the intermediate frequency (IF) reaches 500MHz. The IF signal is quantized at 1GHz with 2-bit accuracy. The resulting data rate is 700Gb/s. This data has to be pre-processed aboard the satellite before it can be transmitted to Earth for further processing. One of the steps of such data processing is cross-correlation. For a space borne instrument, power dissipation and radiation hardness are among the most important requirements. Pacific Microchip Corp. is designing an ASIC that includes a cross-correlation unit with interfaces for the GeoSTAR's receivers. The ASIC will have greatly reduced power consumption compared to that of the FPGA-based or classic ASIC-based implementations. This ASIC must be designed and integrated with already existing system components of the GeoSTAR instrument. The ASIC includes cross-correlation cells based on novel architecture. The deep submicron SOI CMOS technology selected for the ASIC's fabrication will increase its tolerance to the total ionizing dose (TID) and reduce the probability of radiation-induced latch-up. The design of the ASIC will follow design for testability (DFT) methods, which will simplify characterization and testing of the fabricated ASIC, reduce risk and lower the cost of the product.
Planetary rocks, soils, liquids and atmospheric gases are ideal targets for scientists to study the possibility of life existence and the habitability, nature and evolution of planetary systems. Currently, NASA uses different sensing technologies to analyze planetary samples. The use of multiple instruments increases the weight, complexity, power consumption as well as the probability of system malfunction. It is critical to develop lightweight miniaturized multi-functional sensor to enable NASA's multiple-mission needs and therefore make the best use of limited resources by reducing the cost, size, and the number of instruments. Crystal Research Inc. (CRI) proposes a novel compact optical sensor with multiple in-situ sensing capabilities for measurements of various inorganic and organic samples for planetary study and search of biomarkers. The proposed technique is based on a nonlinear coherent interaction process to detect the backward spectral signals from the targets. The detection is enabled by using our novel electro-optic (EO) switchable spectral filtering technique to eliminate spectral artifacts and nonresonant background. The standoff scheme facilitates the implementation of multiple measurements by using a single sensor for nondestructive analysis of different samples on land surface or in atmosphere. It eliminates the sample preparation process, contamination and other related accessories.
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.
NOFBX propulsion technology is being developed actively for a number of applications including a flight experiment on the International Space Station NOFBX propellant has unique electrical properties that allow the potential for development of an extremely low energy ignition mechanism when coupled with the design of an NOFBX combustion chamber. This has the potential for dramatically reducing the volume, mass, voltage, and electromagnetic interference (EMI) emissions. The development we are proposing is a very low energy ignition system that utilizes the unique attributes of the NOFBXTM propellant that minimizes the volume, mass, and voltage of a block redundant system to be used in NOFBX propulsion systems.
This Phase II program will build and deliver a tunable single-frequency laser operating in the 1.645 micron region on optimum CH4 absorption line features.  Under this program an all-solid-state parametric-converted laser will be delivered to NASA LaRC which will be suitable for acquiring range-resolved and column CH4 measurements, and compatible with integration into an airborne methane DIAL system under future programs.  Due to its relative insensitivity to aerosol and cloud interferences, a DIAL system based on this pulsed laser source will be ideal for NASA investigating high-latitude CH4 releases over polar ice sheets, permafrost regions, wetlands and over open ocean during night and day. In addition the methane lidar system has commercial applications in detection of fossil fuel leaks.  This development advances the laser system TRL from 3 to 5. The proposed laser is designed to be compatible with manned or UAV platforms and traceable to space=based instruments.
In situ resource utilization (ISRU) is essential for several of NASA's future flagship missions.  Currently envisioned ISRU plants include production of oxygen from hydrogen reduction of lunar regolith and extraction of water from Martian regolith or asteroid material.  NASA's Regolith &amp; Environmental Science and Oxygen &amp; Lunar Volatile Extraction (RESOLVE) mission's objectives are to analyze the distribution of volatile compounds in the lunar surface and to demonstrate ISRU operation on the moon.  To support ISRU activities, NASA requires the development of a compact, lightweight gas chromatograph/mass spectrometer (GC/MS) instrument that can quantify volatile gases with masses below atomic number 70 released by sample heating.  The instrument must also be designed to withstand exposure to the release of HF, HCl, or Hg that may result from heating regolith samples to high temperatures.  Creare proposes to design, build, and test a compact, lightweight GC/MS system capable of detecting, identifying, and quantifying 100 ppm to 100&#37;-level concentrations of relevant compounds having mass less than 70 amu.  Our GC/MS design is based on components that can be space qualified using techniques proven on numerous past space hardware development projects.  During the Phase I project, we proved our design with benchtop testing, and in Phase II, we plan to build a brassboard version of our GC/MS that will meet the important performance requirements for the intended application.
Advanced space suits require lightweight, low-power, durable sensors for monitoring critical life support materials. No current compact sensors have the tolerance for liquid water that is specifically required for next-generation portable life support systems (PLSS). Intelligent Optical Systems (IOS) is developing a luminescence-based optical sensor probe to monitor carbon dioxide, oxygen, and humidity. Our monitor will incorporate robust CO2, O2, and H2O partial pressure sensors interrogated by a compact, low-power optoelectronic unit. The sensors will not only tolerate liquid water but will actually operate while wet, and can be remotely connected to electronic circuitry by an optical fiber cable immune to electromagnetic interference. For space systems, using these miniature sensor elements with remote optoelectronics provides unmatched design flexibility for measurements in highly constrained volume systems such as PLSS. Our flow-through monitor design includes an optical sensor we have already developed for PLSS humidity monitoring, and an optical oxygen sensor with similar IOS technology. In Phase I of this project IOS demonstrated a CO2 sensor capable of operating while wet, and a miniature prototype PPCO2-H2O-O2 sensor probe was fabricated and tested under relevant environmental conditions. In Phase II, in collaboration with Hamilton Sundstrand (Hamilton), we will design and produce prototypes for space qualification, and will conduct extensive testing under simulated space conditions, culminating in validation in NASA systems, bringing the monitor to TRL 6-7. Engineers from IOS and Hamilton will design the new sensor system to be compatible with electronics developed and fabricated for space operation by Hamilton (in particular, the common modular data bus interface unit). This approach will minimize the power requirements and size of the monitoring device, and will tremendously facilitate the infusion of the technology into the PLSS.
Los Gatos Research (LGR) proposes to employ Off-Axis ICOS to develop triple-isotope water analyzers for lunar and other extraplanetary exploration.  This instrument will provide highly accurate quantification of dD, d18O, and d17O to better than &amp;#177 0.3 0/00,  &amp;#177 0.1 0/00, and  &amp;#177 0.15 0/00 respectively with minimal calibration or consumable standards.  Moreover, due to the inherent benefits of Off-Axis ICOS, the analyzer will be selective, robust, and economical.  In addition to being a strong candidate for extraplanetary exploration, the instrument will be deployed for field testing and research by scientists in NASA's Space Science and Astrobiology Division.
&lt;p&gt;This proposed research will explore how NASA intercalation technology can be used to lower the resistivity of the new Rice-Teijin fiber make them viable for NASA spacecraft applications. In addition, this research will shed light on the interaction between halogens and graphene carbons. This, in turn, could enable the discovery and exploitation of new nanoscale strategies and compounds that might result in further property improvements for CNT-based materials.&lt;/p&gt;
Cosmic Origins Project
Exoplanet Light and Imaging Spectroscopy (ELIAS) Project
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	JPL will design, fabricate, and fully characterize a 640x512 format HOT-BIRD FPA with increased quantum efficiency and extended spectral coverage. Unlike the small format experimental FPA, the proposed FPA will undergo a substrate removal process which extends the cut-on wavelength into the visible range, as well as paving the way towards very large-format (multi-megapixel) arrays. One advantage of the extended spectral coverage FPA is that it eliminates the need for multiple infrared planes; a single optical train can be used to cover the visible to MWIR spectral bands on imagers, spectrometers, spectral- imagers, and hyper-spectral imagers. The other key advantage is the higher operating temperature, which enables passively cooled operations from low earth orbit (LEO), eliminating the need for active coolers. Passive cooled systems use no moving parts, have no vibrations, and provide better reliability. These advantages lead to a reduction in instrument size, mass, mechanical complexity, optical complexity (i.e., no beam splitters, prisms, etc.) and power requirements.&amp;nbsp;&lt;/div&gt;
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&lt;p&gt;
	&lt;span style="font-size: 10.5pt; font-family: Arial, sans-serif;"&gt;The Optical Space Telescope Assembly (OSTA) task is to demonstrate the technology readiness of assembling large space telescopes on orbit in 2015. This task is an integrated part of the Optical Testbed and Integration on ISS eXperiment (OpTIIX) program. FTE at JSC will design, build, and test the Gimbal and the robotic driven attachment mechanisms, develop the robotic operation assembly and maintenance plan and procedures, and perform the integrated ISS analysis of the OpTIIX Payload. For FY12, this task will be brought to a PDR level of documentation and hardware.&lt;/span&gt;&lt;span style="font-size: 7pt; font-family: Arial, sans-serif;"&gt;&lt;o:p&gt;&lt;/o:p&gt;&lt;/span&gt;&lt;/p&gt;
&lt;p&gt;Develop key technologies that enable&amp;nbsp;&lt;u&gt;operational&lt;/u&gt; deep space optical communications.&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Spacecraft disturbance isolation platform for sub-microradian pointing with half the mass and power of present technology&lt;/li&gt;&lt;li&gt;Photon counting space receiver to increase sensitivity 10X and uplink from 100 &amp;nbsp;b/s to multi-MB/s&lt;/li&gt;&lt;li&gt;Ground receiver detector array suitable for multi-meter Earth optical receiver antenna to shift burden from space to groudn for 2X improvement in downlink data rate with no increase in spacecraft burdern&lt;/li&gt;&lt;li&gt;Advance readiness level of above technologies integrated to lightweight SiC optics, deep-space laser transmitter&amp;nbsp; and electronics&lt;/li&gt;&lt;/ul&gt;
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		IMLI coupons have been outperforming traditional MLI. IMLI has better thermal performance&amp;mdash;with some insulating properties improved by up to 37 percent (and analysis indicates that this could grow to 73 percent for a full system). IMLI reduces system uncertainty in thermal performance and lowers fabrication and installation costs. In addition, it has a more durable structure and was not damaged by the high acoustic noise levels associated with launching on a rocket.&lt;/div&gt;
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&lt;div&gt;
	In 2013, the project conducted two tests with IMLI blankets applied to storage tanks: a thermal test and an acoustic test. The tests will have already been completed with traditional MLI. NASA Glenn conducted the thermal test in its Small, Multi-Purpose Research Facility (SMiRF), which simulates the vacuum and temperature extremes of space. The researchers tested IMLI that is supporting a Broad Area Cooling shield actively cooled by a cryocooler to see if IMLI can be used for the long-duration storage of liquid hydrogen with reduced boil-off.&lt;/div&gt;
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		NASA Marshall conducted the acoustic test, subjecting an IMLI blanket and shield identical to those used in the SMiRF tests to the vibrations and noise levels experienced during launch on a rocket. Use of this new insulation system supports NASA&amp;rsquo;s goal to achieve zero boil-off, which would help enable longduration missions as NASA develops new capabilities for&lt;/div&gt;
	&lt;div&gt;
		human space exploration. On Earth, this superinsulation may one day be used in homes and factories&amp;mdash;reducing energy usage and furthering NASA&amp;rsquo;s mission to drive advances in science that benefit everyone.&lt;/div&gt;
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&lt;p&gt;
	&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Because of their predictable pulsations, pulsars are highly reliable celestial clocks that can provide the same high-precision timing as the atomic clock signals supplied through the 26 satellite, military operated Global Positioning Satellite System (GPS)&amp;mdash;a space-age navigational capability now as ubiquitous as the stars in the sky.&lt;/p&gt;&lt;p&gt;To demonstrate this technique, NICER/SEXTANT will use its 56 X-ray telescopes, detectors, and other advanced technologies to detect X-ray photons from these powerful beams of pulsated light to estimate their arrival times. With these measurements, the system will use specially developed algorithms to stitch together an onboard navigation solution.&lt;/p&gt;&lt;p&gt;Long before the advent of GPS and now NICER/SEXTANT, humans relied on the sky and increasingly more sophisticated technology to find their way. And now, NASA scientists are developing NICER/SEXTANT, the latest incarnation of celestial navigation. This technique could extend humankind&amp;rsquo;s ability to navigate to the farthest reaches of the solar system and potentially beyond using pulsars as a timepiece. In a sense, the development follows a grand tradition that began thousands of years ago when the first travelers looked to the skies to venture beyond the horizon.&lt;/p&gt;
&lt;p&gt;The Hypersonic Inflatable Aerodynamic Decelerator (HIAD) project will focus on the development and demonstration of hypersonic inflatable aeroshell technologies suitable for an ISS down-mass capability. The project will focus on the completion of an IRVE 3 development flight test and other necessary analysis and ground-based testing. The key technologies include flexible TPS materials for hypersonic entry conditions, attachment and inflation mechanism and high-strength, lightweight, inflatable bladder materials capable of withstanding high temperatures. The HIAD Project is developing a truly crosscutting technology for atmospheric entry. This technology enhances, and potentially enables, a variety of proposed NASA missions to destinations with atmospheres (Mars, Venus, Titan, the gas giants). This holds true for returning payloads to Earth from Low Earth Orbit (LEO) and beyond, such as ISS down mass or sample return capsules. Not only is this technology applicable to robotic vehicles, the technology is envisioned to be scalable to crewed missions (to Mars or Earth return). The HIAD Project is orchestrating a series of ground and flight tests to demonstrate the viability of thermal resilient materials manufactured in robust configurations to withstand the extreme structural and thermal environments experienced during atmospheric entry. Benefits of using the inflatable decelerator design includes mission flexibility provided by the minimal volume and mass requirements to transfer the stowed HIAD to its destination, as well as increased landed mass, accuracy, and altitude in a variety of space applications.&lt;/p&gt;
&lt;p&gt;The ADEPT Project is developing a mechanically deployable low-ballistic coefficient aeroshell entry system to perform entry descent landing (EDL) functions for planetary missions.&amp;nbsp; This concept would be used to safely deploy scientific payloads or enable long-term human exploration to other planets with their associated cargo needs.&amp;nbsp; The deployable idea allows mission planners to develop an aeroshell design that fits within existing launch vehicle systems, and yet prior to the EDL mission segment, transforms into a low ballistic coefficient configuration.&amp;nbsp; Thus during atmospheric entry, design requirements such as heating, acceleration, and pressure profiles imparted to the entry system are significantly lowered, allowing the use of lower heat capacity TPS and lower design loads for other spacecraft components, including science instruments.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;The ADEPT Project in FY12 has successfully demonstrated the 12-layer carbon fabric system to perform at heating rates up to 250 W/cm2 under flight relevant mechanical loads.&amp;nbsp; In FY13, the project built and tested (with over 50 stow/deploy cycles) a 2m Ground Test Article to demonstrate integrated system performance and assembly techniques.&lt;/p&gt;&lt;p&gt;The near-term focus and technology development for this project will be on developing a 1m-class ADEPT to support Mars, Venus and Earth LEO mission scenarios.&amp;nbsp; The design approach will target an entry configuration capable of delivering 5-10 kg payloads for a Mars mission. &amp;nbsp;Component and system level testing will be performed at arc jet and wind tunnel test facilities at relevant environments, culminating in a Mach 3 sounding rocket flight demonstration test by the end of FY15.&amp;nbsp; Further technology maturation with a focus on 6m Venus New Frontiers class missions is planned for FY16 -18.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;SWORDS will place nanosatellites into precise low earth orbits to provide capabilities both where and when they are needed. Nanosatellites will no longer have to wait months or years for piggyback rides subject to the schedule and orbital locations of other payloads. SWORDS will allow the affordable maintenance of constellations of nanosatellites in low earth orbit to provide communications and other services at an unprecedented low level of mission command, regardless of where American forces are deployed. The SWORDS launch vehicle can be transported by C-17 aircraft, and is designed to launch out of multiple ranges, including austere ranges with as little infrastructure as a simple concrete pad.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;The focus of the SWORDS dedicated nanosatellite launch vehicle is on low cost rather than high performance. Ultra low cost is achieved by careful selection and judicious application of commercial-grade materials and components, as opposed to traditional aerospace-grade components. SWORDS uses a pressure-fed propellant system, eliminating the need for a turbopump. Thrust magnitude steering is used vice engine gimbals. Commercial-off-the-shelf electronic components are used for avionics. Safe, widely available, and inexpensive fuel and oxidizer is used. Range costs are minimized using a &amp;ldquo;ship and shoot&amp;rdquo; concept that inherently reduces the amount of time spent on the range. The innovation of SWORDS is in the systems engineering and integration of current technologies to achieve low cost, low part count and high operational readiness.&lt;/p&gt;
&lt;p&gt;
	Develop advanced technologies to enable a variable heat rejection Thermal Control System (TCS) capable of operating through a wide range of thermal environments while simultaneously being required to reject varying heat load levels&lt;/p&gt;
&lt;p&gt;This project advances the state of robotic technology to enable the routine servicing of satellites that were not designed with servicing in mind, including observatories and space infrastructures.&amp;nbsp;It improves technologies necessary for robotic satellite servicing, rescue, and disposal, particularly technologies for the remote survey, relocation, refueling, replacement (of orbital repair units), and repair of orbiting satellites. &amp;nbsp;Primary project activities include developing a conceptual robotic servicing mission for Government and commercial satellites, as well as an aggressive technology development campaign to rapidly advance the TRL of multiple cross-cutting technologies. The campaign includes the: &amp;bull; Robotic Refueling Mission, a technology demonstration on the International Space Station (ISS) that uses the Canadian Dextre robot and NASA-developed tools and task boards to demonstrate tools, technologies and techniques to refuel and repair satellites that were not designed for in-flight service.&amp;nbsp; Operations to date have included the most dexterous robotic maneuvers performed on orbit.&lt;/p&gt;
&lt;p&gt;The project is building the first prototype integrated system to mitigate solar event risk through probabilistic modeling, forecasting, and dose projection. This new capability will provide mission operators with tools to assist in mission planning and design, assessment of &amp;lsquo;worst-case&amp;rsquo; radiation dose, prediction of event occurrence, and projection of cumulative radiation dose once an event has begun.&amp;nbsp; Tools are being built utilizing historical satellite data spanning four decades, satellite imagery of the Sun, and large-scale first-principles simulations of the inner heliospheric environment.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Cutting edge customer driven research in two areas:&lt;/p&gt;&lt;p&gt;&lt;u&gt;Aerosciences&lt;/u&gt;, including the completion and delivery of two new aerothermal CFD codes, a first ever validated shock layer radiation model, and an experimental validationdatabase, at flight-relevant enthalpy, for current and future generations.&lt;/p&gt;&lt;p&gt;&lt;u&gt;EDL Materials&lt;/u&gt;, including the&amp;nbsp;development and delivery of two&amp;nbsp;new flexible TPS systems to&amp;nbsp;enable HIAD missions, vastly&amp;nbsp;improved ablator modeling&amp;nbsp;capability, and improved&amp;nbsp;polymer resins&amp;nbsp;to enhance or enable&amp;nbsp;future developments&amp;nbsp;in woven, flexible and&amp;nbsp;conformal thermal&amp;nbsp;protection systems.&lt;/p&gt;
&lt;p&gt;The Heatshield for Extreme Entry Environ&amp;shy;ment Technology (HEEET) project seeks to mature a game changing Woven Ther&amp;shy;mal Protection System (TPS) technology to enable in situ robotic science missions recommended by the NASA Research Council Planetary Science Decadal Sur&amp;shy;vey Committee.&amp;nbsp; Recommended science missions include Venus probes and lan&amp;shy;ders; Saturn and Uranus probes; and high&amp;shy;speed sample return missions.&amp;nbsp; Currently, these missions are limited to the use of heritage materials such as Carbon Phenolic (CP) as their only TPS solution.&amp;nbsp; Due to its inherent properties, heritage CP constrains the mission application, and in the long term, poses significant sus&amp;shy;tainability challenges.&amp;nbsp; The goal of HEEET is to develop a woven TPS technology to Technologu Readi&amp;shy;ness Level (TRL) 5/6 that will provide an alternate TPS solution for these missions.&amp;nbsp; The tailorable woven TPS will reduce entry loads and signifi&amp;shy;cantly reduce heatshield mass by 30&amp;shy;-40&#37; for extreme entry environ&amp;shy;ments missions.&amp;nbsp; Woven TPS is a science enabler that will allow for a high return on investment made by both NASA&amp;rsquo;s Space Technology Mission Directorate and Science Mission Directorate.&lt;/p&gt;
&lt;p&gt;The 3D MAT Project seeks to design and develop a game changing Woven Thermal Protection System (TPS) technology tailored to meet the needs of the Orion Multi-Purpose Crew Vehicle (MPCV) compression pad design for lunar return EM-1 mission and beyond.&amp;nbsp; The technology being developed is a multifunctional ablative thermal protection system material that is capable of meeting the structural and thermal requirements for the MPCV Orion EM-1 mission and beyond.&amp;nbsp; The Orion compression pads serve as the interface between the Crew Module and Service Module.&amp;nbsp; The Orion compression pads must carry the structural loads generated during launch, space operations and pyroshock separation of the two modules, and then must serve as an ablative TPS withstanding the high heating of Earth re-entry.&amp;nbsp; Current materials do not meet all of the requirements due to either insufficient mechanical strength or limited ability to manufacture to the required dimensions.&amp;nbsp; The goal of 3D MAT is to deliver a prototype compression pad material at Technology Readiness Level (TRL) of 4 in 2014 to enable Orion&amp;#39;s further development and use of the material on the MPCV flight in 2017.&lt;/p&gt;
&lt;p&gt;CA-TPS is leveraging earlier investments made by ARMD&amp;rsquo;s Hypersonic and HEOMD&amp;rsquo;s ETDD program that matured the concept from TRL 1 to 2.CA-TPS starts with thick, carbonized rayon felt and the flexible felt is converted to ablative TPS via low density phenolic resin infusion similar to the PICA process.&amp;nbsp; The resulting conformal TPS molded to the required shape prior to resin infusion can then be machined and bonded to the carrier structure.&amp;nbsp; The ease of machining holes to accommodate protrusion on the heat shield or back shell is an attractive feature.&amp;nbsp; The material can be machined with exceptional tolerance and compliance which allows TPS integration with extremely simple seams to form a robust system. The design should result in much larger molded TPS panels that can be directly bonded to most carrier structures and allow for a simplified design of seams between gore panels.&amp;nbsp; This will eliminate the need for gap filler design and strain isolation pads, and should accommodate a wider range of allowable carrier structure imperfections when compared to a rigid material such as PICA.&lt;/p&gt;
&lt;div&gt;
	Planetary entry and near-Earth object return missions with an anticipated heat flux between 1,500 and 10,000 W/cm&lt;sup&gt;2&lt;/sup&gt; are currently limited to one viable TPS material - fully dense carbon phenolic (CP). However, high-density CP is only mass efficient at heat fluxes above 4000 W/cm&lt;sup&gt;2&lt;/sup&gt;. This mid-density TPS performance gap can be filled using cost-effective weaving technology to produce high-grade, conformal, mid- to high-density TPS. Woven TPS not only bridges this gap but also offers a superior performing replacement for heritage CP.&lt;/div&gt;
&lt;div&gt;
	&amp;nbsp;&lt;/div&gt;
&lt;div&gt;
	A woven TPS approach can result in TPS solutions that are optimized to a given mission&amp;#39;s environments but with much-reduced costs compared to current TPS development and certification approaches. The woven TPS approach utilizes a stable U.S. weaving industrial base and processes that has a proven legacy and longevity in manufacturing commercial and advanced aerospace products. This industry has demonstrated capability to weave highly complex patterns in a 3D weave configuration for commercial applications.&lt;/div&gt;
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	&amp;nbsp;&lt;/div&gt;
&lt;div&gt;
	The Woven TPS Project will demonstrate this concept in partnership with a reliable industrial weaver selected through a Request for Information process in a 14-month program. We will accomplish this by designing and manufacturing a series of low-, mid- and high-density samples of woven carbon fiber material of varying yarn compositions, weave architectures, and level of resin infiltration and by testing them at extreme conditions. It is the project&amp;#39;s goal to develop a preliminary database, compare the performance of woven TPS against heritage fully dense CP, and raise the woven TPS from Technology Readiness Level (TRL) 2 at the start of the project to TRL 3 at project completion.&lt;/div&gt;
&lt;p&gt;The task is to investigate the technology path to develop a 10kW modular Silicon Carbide (SiC) based power processing unit (PPU). The PPU utilizes the high temperature SiC device technology and multi-chip packaging technology enabling the PPU operating at high junction temperatures to reduce the thermal mass for in-space propulsion applications, focusing on a Hall thruster propulsion system. The comparison of the topologies for the Hall thruster PPU has been on-going, and the current design is a non-isolated straight boost topology for the discharge supply, with the trades of the detail design features of the topology being investigated. PPU packaging scheme is also being developed to provide a thermal distribution on the PPU board to optimize the topology and packaging design from the thermal perspective through an iterative process. The goal is that no additional thermal management mass will be added to the 10kW PPU module. Both SiC and high temperature silicon-on-insulator (SOI) technologies are investigated for the control circuit scheme as variable options, along with passive technologies and path to space qualification methodology.&lt;/p&gt;
&lt;p&gt;Develop new cell and blanket technologies and manufacturing processes that reduce overall array costs&lt;/p&gt;&lt;p&gt;&amp;bull;Cells: develop new cell technology comparable to SOA with reduced cost at various production levels&lt;/p&gt;&lt;p&gt;&amp;bull;Blankets: develop blanket technology compatible with the space environment at costs less than SOA&lt;/p&gt;&lt;p&gt;&amp;bull;Electrical Interconnects and Cell Protection: develop automated processes for stringing cells and providing protection from the space environment&lt;/p&gt;&lt;p&gt;&amp;bull;Lab-scale development of technologies with greater power density and cost reduction through multiple programs tested for reliability by thermal cycling and space plasma interactions&lt;/p&gt;&lt;p&gt;&amp;bull;Flight-sized cell/blanket demonstrators for integration in SOA solar array structures&lt;/p&gt;
&lt;p&gt;The development of high specific energy devices will enable NASA&amp;rsquo;s future robotic and human-exploration missions. &amp;nbsp;The need for advances in energy storage and power generation technologies is captured in various roadmaps and strategic investment plans.&amp;nbsp; The National Research Council (NRC), &lt;em&gt;NASA Space Technology Roadmaps and Priorities&lt;/em&gt;, consistently identifies the increase in available power and &amp;ldquo;the elimination of the constraint of power availability for space missions by improving energy generation and storage with reliable power systems that can survive the wide range of environments unique to NASA missions.&amp;rdquo;&lt;/p&gt;&lt;p&gt;This objective of this project element is to develop transformational technologies that will enable future space exploration missions by maximizing specific energy of devices while maintaining safety, reliability and duty cycles.&amp;nbsp; It is anticipated that the core technologies developed under this project element will advance energy storage for the broad user base that not only includes NASA, but also other Government Agencies and the commercial sector. &amp;nbsp;&amp;nbsp;&amp;nbsp;The project element has been divided into two categories:&amp;nbsp; Category One, &amp;ldquo;High Specific Energy System Level Concepts&amp;rdquo; will focus on system level battery technologies such as packaging and cell integration.&amp;nbsp; Category Two, &amp;ldquo;very High Specific Energy Devices&amp;rdquo; will focus on energy storage technologies that have the potential to go beyond the capabilities characterized by Li-ion chemistry, while maintaining the required safety and duty cycle of any system operating in space.&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The Inflatable Structures (InSTAR) project goal is to demonstrate long term durability of inflatable habitat structures for potential utilization as either in-space or planetary habitats.&amp;nbsp; Using a multi-center approach to leverage capabilities and recent contributions from prior NASA-funded inflatable technology projects, industry, and DoD activities.&amp;nbsp; Unique test facilities will be designed and outfitted to conduct experimental tests on SOA high strength webbings and full configuration inflatable modules.&amp;nbsp; Unique test hardware and data acquisition systems will be built to capture global displacements and strains of webbing materials.&amp;nbsp; Collaboration with industry and government partners will be conducted.&amp;nbsp; Periodic reviews of the technical work will be conducted, schedule will be tracked and budget will be monitored on a regular basis.&lt;/p&gt;
&lt;p&gt;Increase the tensile strength of CNT fibers to produce composites with specific tensile strengths of 2.0 GPa/(g/cc) and demonstrate their impact on the mechanical properties, coefficient of thermal expansion, and damage tolerance of CFRP&lt;/p&gt;&lt;p&gt;Approach:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Increase tensile strength of commercially available CNT materials via&amp;nbsp; a combination of processing modifications (increased CNT length and improved alignment) and post-processing methods (increase CNT-CNT bond strength)&lt;/li&gt;&lt;li&gt;Incorporate into composites and perform coupon level tests to quantify improvements in mechanical properties, damage tolerance and dimensional control&lt;/li&gt;&lt;li&gt;Demonstrate benefits and flight readiness by design, fab, ground and flight test of a CNT reinforced COPV&lt;/li&gt;&lt;li&gt;Partner with DoD and other agencies under the NNI Sustainable Nanomanufacturing Signature Initiative to leverage resources and capabilities&lt;/li&gt;&lt;li&gt;Utilize other NASA investments, e.g., Space Technology Research Fellowships, SBIR/STTR to accelerate technology development&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;&amp;bull;Develop ultralightweight, high strength composites from carbon nanotube reinforcements&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Targeting specific strength 1.5 to 2X that of conventional aerospace carbon fiber reinforced epoxy&lt;/li&gt;&lt;li&gt;Estimate 30&#37; reduction in launch vehicle total mass by using CNT composites in cryotank&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&amp;bull;CNT reinforcements are available on commercial and developmental scales&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Primary application is for lightweight electrical cables&lt;/li&gt;&lt;li&gt;Best reported mechanical properties are about &amp;frac12; that of conventional carbon fiber, actual properties are much lower&lt;/li&gt;&lt;li&gt;Theoretical studies (Cornwall and Welch) suggest that tensile strengths 12X that of conventional carbon fiber are possible through a combination of processing (longer, better aligned CNTs) and post-processing (cross-linking)&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&amp;bull;Collaborating with industry, universities, DoD and NIST to improve tensile properties of CNT reinforcements and utilize them in composites&lt;/p&gt;
&lt;p&gt;NASA supports the Advanced Manufacturing National Program Office (AMNPO).&amp;nbsp;&lt;/p&gt;&lt;p&gt;Hosted by the National Institute of Standards and Technology (NIST) the AMNPO is staffed by representatives from federal agencies with manufacturing-related missions as well as fellows from manufacturing companies and universities.&lt;/p&gt;&lt;p&gt;The scope of the interagency effort includes:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Convening and enabling industry-led, private-public partnerships focused on manufacturing innovation and engaging U.S. universities including the National Network for Manufacturing Innovation (NNMI)&lt;/li&gt;&lt;li&gt;Designing and implementing an integrated whole of government advanced manufacturing initiative to facilitate collaboration and information sharing across federal agencies.&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;Develop integrated computational/experimental/processing methodologies for accerlating discovery and insertion of mateirals to satisfy NASA&amp;#39;s unique mission demands&lt;/p&gt;&lt;ul&gt;&lt;li&gt;The challenges:&lt;ol&gt;&lt;li&gt;Validated design tools that incorporate materials properties, processes and design requirements&lt;/li&gt;&lt;li&gt;Materials process control to rapidly mature emerging manufacturing methods to industry ready&lt;/li&gt;&lt;/ol&gt;&lt;/li&gt;&lt;li&gt;Approach:&lt;ol&gt;&lt;li&gt;Physics-based modeling to guide material design e.g. matrix composition, crosslinking between CNTs, grain size and texture&lt;/li&gt;&lt;li&gt;Multiscale modeling influence of materials design on mechanical properties and durability&lt;/li&gt;&lt;li&gt;Process modeling to determine processing parameters required to produce as-designed material nano-/micro-structures and enable advanced manufacturing methods utilization&lt;/li&gt;&lt;li&gt;Utilize material data management to support robust material design methodology&lt;/li&gt;&lt;/ol&gt;&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;Develop and mature manufacturing technology to enable fabrication of single-piece integrally-stiffened launch vehicle structures to replace expensive, heavy, and risky multi-piece welded assemblies.&lt;/p&gt;
&lt;p&gt;MIS, Inc., under SBIR Phase III contract with NASA, will build a 3D printer that can build objects out of plastic feedstock. NASA will provide insight to ensure that the design and materials meet flight certification (safety, interfaces, and operability) requirements as well as performing qualification and performance testing. The 3D Print payload will demonstrate melt deposition modeling additive manufacturing in a consistent microgravity environment. Lessons learned from this technology demonstration will be incorporated into future generations of advanced manufacturing technology for space applications.&lt;/p&gt;
&lt;p&gt;CIM encompassed computational methods, tools and processes that go into the materials, design, manufacturing and qualification of composite aerospace structures. This effort proposed that test articles and analytical techniques be developed in order to investigate the appropriate treatment of model-based methods to achieve the maximum benefit of using the computational approaches for optimization of cost, performance, and reliability materials for launch vehicle structures such as the EUS.&lt;/p&gt;&lt;p&gt;Materials&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Extend use of out-of-autoclave materials to load-bearing composite structures&lt;/li&gt;&lt;li&gt;Introduce damage-based allowables to improve performance while reducing cost&lt;/li&gt;&lt;li&gt;Reduce allowables variability&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;Design&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Tailor composite wall construction to maximize load-carrying capability while minimizing mass&lt;/li&gt;&lt;li&gt;Implement model-based integration of design and qualification/certification&lt;/li&gt;&lt;li&gt;Reduce artificial knockdown factors by implementing damage-based allowables at a component level&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;Manufacturing&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Implement model-based, automated manufacturing of relevant-scale structures&lt;/li&gt;&lt;li&gt;Demonstrate light-weight bonded joint technology to reduce numbers of fasteners&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Rapidly fabricated, modular and integrated small satellite subsystems will be developed from digital fabrication workflows. The following are planned modular components:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Cube Satellite structure using state-of-the-art advanced manufacturing technologies, techniques, and materials&lt;/li&gt;&lt;li&gt;Modular &amp;quot;Digital Material&amp;quot; technology for spacecraft subsystems and components to maximize payload volume&lt;/li&gt;&lt;li&gt;Modular computing architecture to be used with Commercial Off the Shelf (COTS) microcontrollers&lt;/li&gt;&lt;li&gt;Digital repository of widely accessible, easy to replicate and modify satellite components&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;The main objectives are to develop and integrate Integrated Systems Health Management (ISHM) tools and component technologies into a seamless health management architecture and to create an autonomous cryogenic loading capability. ACLO components will be developed for mission-relevant cryogenic platforms/environment (i.e., ground-based and micro-g in-space capability) and demonstrated against the KSC Cryogenic Test Facility&amp;rsquo;s Simulated Propellant Loading System, a.k.a, the Cryogenic Testbed. The autonomous cryogenic loading capability and component technologies developed under the ACLO Project Element will be used to help mature concepts for variable levels of autonomy and will enable NASA to rapidly adapt to and support various launch concepts with multiple vehicle types in a multi-use launch pad or an in-space environment. The ACLO Project Element will continue to build on capabilities and concepts developed and/or demonstrated in FY13 under ACLO and previous ground autonomy and health management efforts:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Systems Autonomy Demonstration Program: Knowledge-based Autonomous Test Engineer (KATE), which proved the feasibility of using high-fidelity physics models and simulations to enable integrated system health, status and control for autonomous tank loading operations&lt;/li&gt;&lt;li&gt;Constellation pathfinder demonstrations and trade studies: Ares I-X Ground Diagnostic Prototype &amp;amp; Fault Detection, Isolation and Recovery Architecture Prototype, which developed a certifiable configuration and approach for integrated health management for ground and launch operations&lt;/li&gt;&lt;li&gt;AFRL Future Responsive Access to Space Technologies Program: Rapid Propellant Loading Project, which developed concepts for distributed launch operations and cryogenic loading operations using KATE and the Hybrid Diagnostic Engine&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;During 2014, the Robotic Technologies for Asteroid Missions activity has four tasks:&lt;/p&gt;&lt;ol&gt;&lt;li&gt;Asteroid Retrieval Capture Mechanism Development and Testbed;&lt;/li&gt;&lt;li&gt;Mission Operations Tools for Asteroid Capture and Retrieval;&lt;/li&gt;&lt;li&gt;Prototype Anchoring End Effector for Asteroid with Sensors; and&lt;/li&gt;&lt;li&gt;Develop Prototype Tendon-Actuated Manipulators to Enable In-Space Operations.&lt;/li&gt;&lt;/ol&gt;&lt;p&gt;The full descriptions for each task within this project element are listed under individual Technologies below:&lt;/p&gt;
&lt;p&gt;During 2012, NASA funded 9 grants to research institutions and universities, after reviews by NSF panels and NASA robotics experts.&amp;nbsp; The 9 research grantees performed well and reported on their findings in June 2013 at the NRI continuation review.&amp;nbsp; All grantees were approved to continue for a second year of work.&lt;/p&gt;&lt;p&gt;The titles of the FY14 grants are listed here for convenience:&lt;/p&gt;&lt;ul&gt;&lt;li&gt;&lt;em&gt;Long, Thin Continuum Robots for Space Applications&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;A Novel Powered Leg Prosthesis Simulator for Sensing and Control Development&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Long-range Prediction of Non-Geometric Terrain Hazards for Reliable Planetary Rover Traverse&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Active Skins for Simplified Tactile Feedback in Robotics&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Actuators for Safe, Strong, and Efficient Humanoid Robots&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Manipulating Flexible Materials Using Sparse Coding&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Whole-Body Telemanipulation of the Dreamer Humanoid Robot on Rough Terrains Using a Hand Exoskeleton (EXODREAM)&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Toward Humanoid Avatar Robots for Co-exploration of Hazardous Environments&lt;/em&gt;&lt;/li&gt;&lt;li&gt;&lt;em&gt;Building the Robotic Commons, Open Source Robotics Foundation &lt;/em&gt;&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;The full descriptions for each research grant are listed under individual Technologies below:&lt;/p&gt;
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&lt;p&gt;This project involves a demonstration for a new environmentally safe and accurate cleaning method for removing contaminants (oil films, fungi,) in enclosed areas such as pipes, tanks, and tubes.&amp;nbsp; It relies on a combination of techniques such as, Laser-induced fluorescence (LIF), Optical trapping (OT), Holographic in-line interferometry (HILI), Coherent fringe projection (CFP), and Optical evaporation (OE).&amp;nbsp;&amp;nbsp; To enable inspection and operation of the method inside enclosed surfaces, the techniques will operate with a flexible coherent optical fiber bundle.&amp;nbsp; A unified approach for modeling both HILI and CFP will be developed to demonstrate that these techniques are suitable for accurate remote characterization of contaminants.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;The proposed project will explore and test the feasibility and effectiveness of using a cryogenic fluid (liquid nitrogen) to facilitate acoustic suppression in a rocket engine testing environments.&amp;nbsp; Typically, a pressurized water &amp;ldquo;curtain&amp;rdquo; is used to provide acoustic suppression. Achieving the volume and flow rates of the water required to suppress acoustic reverberation is extremely energy intensive and, often can limit the test duration or profile. In recent years, investigation into acoustic suppression using water has been explored which has included the development of some empirical relations so that levels of acoustic suppression can be assessed. However, most relations developed are simplistic, and merely scale the total mass flow rate or momentum of the propellants to determine the optimal water volume required.&amp;nbsp; Therefore, for this project, the utility of cryogenic fluid to suppression acoustic energy will be explored to assess its utility in a rocket engine testing environment.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;Fission-ignited fusion systems have been operational &amp;ndash; in weapon form &amp;ndash; since the 1950&amp;rsquo;s. Leveraging insights gained from the weapons physics program, a Z-Pinch device could be used to ignite a thermonuclear deuterium trigger. The fusion neutrons will induce fission reaction in a surrounding uranium or thorium liner, releasing sufficient energy to further confine and heat the fusion plasma. The combined energy release from fission and fusion would then be directed using a magnetic nozzle to produce useful thrust. This type of concept could provide the efficiency of open cycle fusion propulsion devices with the relative small size and simplicity of fission systems; and would provide a radical improvement in our ability to explore destinations across the solar system and beyond.&lt;/p&gt;
&lt;p&gt;The idea of suspended animation for interstellar human spaceflight has often been posited as a promising far-term solution for long-duration spaceflight. A means for full cryo-preservation and restoration remains a long way off still. However, recent medical progress is quickly advancing our ability to induce deep sleep states (i.e. torpor) with significantly reduced metabolic rates for humans over extended periods of time. NASA should leverage these advancements for spaceflight as they can potentially eliminate a number of very challenging technical hurdles, reduce the IMLEO for the system, and ultimately enable feasible and sustainable missions to Mars.&lt;/p&gt;&lt;p&gt;SpaceWorks proposes the design of a torpor-inducing Mars transfer habitat and an architectural-level assessment to fully characterize the impact to Mars exploration.&lt;/p&gt;&lt;p&gt;The habitat is envisioned as a very small, pressurized module that is docked around a central node/airlock permitting direct access to the Mars ascent/descent vehicle and Earth entry capsule by the crew. We believe the crew habitat mass can be reduced to only 5-7 mt (for a crew of 4-6), compared to 20-50 mt currently. The total habitat module volume would be on the order of 20 m3, compared to 200 m3 for most current designs.&lt;/p&gt;&lt;p&gt;An end-to-end Mars mission architecture will be evaluated using the new habitat design. For comparison purposes, technology assumptions being used in other ongoing NASA studies will be used. This human-stasis option will then be compared with various Design Reference Architectures (DRAs) to quantify the impact and merits of the approach.&lt;/p&gt;
&lt;p&gt;We propose to develop a new landing approach that significantly reduces development time and obviates the most complicated, most expensive and highest-risk phase of any landing mission. The concept is a blanket- or carpet-like two-dimensional (2D) lander with a low mass/drag ratio, which allows the lander to efficiently shed its approach velocity and provide a more robust structure for landing integrity. The flat nature and low mass of these landers allows dozens to be stacked for transport and distributed&amp;nbsp;&lt;em&gt;en masse&lt;/em&gt;&amp;nbsp;to the surface. The concept leverages recent developments in microelectronics and MEMS technology, such as the lab-on-a-chip, integrated RF comm, and laser probes.&lt;/p&gt;
&lt;p&gt;Tensegrity engineering is&amp;nbsp;a newly established discipline pioneered by one of the authors - with the mathematical rigor to deliver safe minimal mass structures.&amp;nbsp;We will use and expand these analytical tools to accomplish our stated research objectives. We will create new devices for providing&amp;nbsp;momentum control through the tensegrity structure. We will describe &amp;quot;space capable&amp;quot; robotic processes to enable autonomous&amp;nbsp;fabrication and construction of tensegrity structures from asteroidal regolith. We will devise new hull structures for protection from&amp;nbsp;the space environment, and accompanying strategies for interaction with the thermal and radiation environment.&lt;/p&gt;&lt;p&gt;The&amp;nbsp;capability, flexibility and adaptability that this new technology represents, coupled with parallel developments in mining of space based&amp;nbsp;resources, private sector launch capability and the nascent space tourism industry, can introduce the component of early date free&amp;nbsp;space habitats into the space economy, resulting in new calculations of economic possibility.&lt;/p&gt;
&lt;p&gt;Inputs to the processor could include&amp;nbsp;space mission solid wastes, such as biodegradable packaging, but focused largely on cellulose from inedible plant materials. This celluose could be the&amp;nbsp;ineidible&amp;nbsp;portion&amp;nbsp;of biomass from plants that might be used for future life support systems (e.g., inedible leaves, stems and roots). The&amp;nbsp;processor itself consisted of two reactors or compartments: The first compartment contained cellulose degrading fungi to produce simple sugars, such as glucose. The second compartment contained yeast that used the glucose to produce milk fat.&amp;nbsp; The overall intent was to combine the two processes in one single reactor column, hence the name &amp;quot;Cow-in-a-Column&amp;quot;.&lt;/p&gt;&lt;p&gt;The process could also be adapted to generate&amp;nbsp;high value protein, such as milk casein, or even biofuels such as methane, biodiesel, or solvents. The project involved selecting and testing various microorganisms for their ability to convert the different wastes into the target products. This also required accurate chemical assays&amp;nbsp;of the end products to verify the column performance. The concepts were demonstrated by the end of the 1-year project but further testing is needed to demonstrate sustained operation and / or to expand the process to produce other products. Future testing could involve the use of genetically&amp;nbsp;engineered microbes to improve the overall efficiency of converting solid wastes into edible products.&lt;/p&gt;
&lt;p&gt;Recent work in the NASA Kennedy Space Center (KSC)&amp;nbsp;Surface Systems Office (NE-S) Swamp Works&amp;nbsp;and at the University of Southern California (USC) under two NASA Innovative Advanced Concept (NIAC) awards have shown promising results with regolith (crushed basalt rock) materials for in-situ heat shields, bricks, landing/launch pads, berms, roads, and other structures that could be fabricated using regolith that is sintered or mixed with a polymer binder.&amp;nbsp;&lt;/p&gt;&lt;p&gt;&lt;span style="line-height:1.6em"&gt;These results indicate that the unique properties of granular planetary regolith are well suited for use as a construction material with high insulation values, low densities and&amp;nbsp; good&amp;nbsp; manipulation characteristics. Examples of regolith manipulation processes are solar heat sintering, microwave sintering, laser sintering, polymer binders, compaction, regolith paste extrusion&amp;nbsp; and waterless concrete forming .&lt;/span&gt;&lt;/p&gt;&lt;p&gt;Methods of transferring regolith to a &amp;ldquo;3D Print Head&amp;rdquo; mounted on a robotic arm will be developed to investigate the feasibility of adhering the regolith particles together in successive 2D layers to achieve a 3D printing additive manufacturing proof of concept process with net shape characteristics of useful structures such as blast walls, landing pads, habitats, bricks, roads, antenna towers, heat shields and even propellant tanks. This will result in high mass savings as local in-situ regolith is without transporting material and equipment from Earth. Power consumption per product kilogram is determined for each transfer method.&lt;/p&gt;
&lt;p&gt;Advances continue to be made in areas of novel materials and mechanical refrigeration equipment for the thermal management of cryogens in applications from space transportation to medical imaging. The investigation of novel materials/systems in combination with mechanical refrigeration equipment for use in thermal management systems is the focus of this project. Materials include coatings and other surface finishes while the refrigeration may be active (with cryocoolers), passive (cryogen only), or a combination.&lt;/p&gt;&lt;p&gt;Another important aspect of efficient thermal management is the storage and transport of cryogenic fluids such as liquid hydrogen and liquid helium. These two low-viscosity cryogens are the main challenge and prime target for future applications.&lt;/p&gt;
&lt;p&gt;NASA Kennedy Space Center&amp;nbsp;is developing a testbed&amp;nbsp;for producing large volume mixtures of ice and regolith under low pressure inside a laboratory vacuum chamber. This will allow those&amp;nbsp;technologies that are being developed to excavate and utilize icy planetary regolith, to be tested and evaluated during actual operation&amp;nbsp;under simulated surface conditions such as those&amp;nbsp;found&amp;nbsp;on asteroids, Mars, and the Moon.&lt;/p&gt;&lt;p&gt;The results of testing under relevant environmental conditions will be used to validate existing or future physical models that predict excavation forces related to mining planetary regolith, and&amp;nbsp;to determine the amount of energy required to excavate the regolith and to sublimate solid volatiles contained in icy regolith.&lt;/p&gt;
&lt;p&gt;Shape memory alloys applies to a group of materials that demonstrate the ability to return to some previously defined shape when subjected to the appropriate thermal procedure. Generally, these materials can be plastically deformed at some relative lower temperature, and then upon exposure to some higher temperature will return to their original shape prior to the deformation. Materials that exhibit this property are referred to as one-way shape memory; some materials also undergo shape change upon re-cooling, and are referred to as 2-way shape memory. &amp;nbsp;&lt;/p&gt;&lt;p&gt;Generally, an alloy undergoes a transformation from the austenite phase to the martensitic upon strain below the transformation temperature, which is then reversed upon heating, returning to the parent phase. The only two alloys that have achieved any level of commercial exploitation are the nickel titanium&amp;nbsp;(NiTi) alloys and the copper-base alloys, particularly copper-aluminum-nickel (CuAlNi) and copper zinc aluminum (CuZnAl).&amp;nbsp; In training and testing of these SMAs there are indications that they are susceptible to cycle fatigue depending upon conditions of use. In this project, two different novel designs previously developed are being enhanced and evaluated for&amp;nbsp; cycle &amp;nbsp;fatigue&amp;nbsp; of the 2-way SMAs effects for use in intelligent &amp;nbsp;thermal systems. &amp;nbsp;Knowing the effective, efficient lifetime of each system, it will then be possible to design and optimize a system to a specific application in the future.&lt;/p&gt;
&lt;p&gt;An investigation into a new mission concept approach to achieve unlimited high altitude long endurance flight to achieve geosynchronous atmospheric satellites for civil missions.&amp;nbsp; The study will compare the new approach to existing approaches, with detailed analysis of the key differences that enable a reduction in structural weight by 50&#37;, while also decreasing the drag by 50&#37; through significantly higher aspect ratio wings, higher wing loading, and lower payload drag.&lt;/p&gt;
&lt;p&gt;Imagine being able to print anything from tools and composite building materials to food and human tissues. Imagine being on Mars with the ability to replace any broken part, whether it&amp;#39;s a part of your spacesuit, your habitat, or your own body. We propose a technique that would allow just that. By printing 3D arrays of cells engineered to secrete the necessary materials, the abundant in situ resources of atmosphere and regolith become organic, inorganic, or organic-inorganic composite materials. Such materials include novel, biologically derived materials not previously possible to fabricate.&lt;/p&gt;
&lt;p&gt;The full potential of small spacecraft remains untapped because they lack maneuverability. Plasmonic force propulsion provides attitude control capability for small spacecraft with no power penalty and minimal mass and volume penalty. This creates new capabilities for small spacecraft enabling NASA science and exploration missions that were previously impossible. One of NASA&amp;rsquo;s strategic goals is expanding scientific understanding of the Earth and the universe. NASA envisions a broad class of scientific missions where extremely fine pointing and positioning of spacecraft is required, such as a single Earth observing spacecraft, deployable x-ray telescopes, exoplanet observatories, and constellations of spacecraft for Earth and deep space observations. In recognizing this, the National Research Council emphasized the need for micro-propulsion for extremely fine pointing and positioning of micro-satellites for astrophysics missions.&lt;/p&gt;&lt;p&gt;Within the context of these types of missions, we propose to assess the ability of plasmonic force propulsion to advance the state-of-the-art. We propose to numerically simulate plasmonic force fields with asymmetric/gradient geometry and relevant solar light constraints, predict nanoparticle velocity, mass flow rate, and resulting propulsion performance (thrust, specific impulse), and evaluate spacecraft position control resolution and pointing precision enabled by plasmonic propulsion. We will compare our results with state-of-the-art thrusters (e.g., colloid/electrospray electric propulsion) and torquers (e.g., reaction wheels). We will also assess the feasibility of plasmonic propulsion to meet and/or exceed the stringent demands of future NASA missions.&lt;/p&gt;
&lt;p&gt;Electromotance energy has historically produced problems for electrical systems. This project will innovatively employ high electron density fields that have the ability to attract the energy released from the charged electromagnetic spectrum similar to the way a thick steel enclosure functionally collects and dissipates electromotance energy into a ground source.&amp;nbsp; The strategically oriented fields with an appropriate electron density have the potential to capture and channel the energy away from electronic cabling consequently reducing electromotance effects.&amp;nbsp; These fundamental principles will be used to develop a novel prototype system that can be used to perform improved electromotance noise reduction in a laboratory environment.&amp;nbsp; Additionally, it could be deployed within sensitive instrumentation shielding in a similar fashion as previously used shielding techniques.&lt;/p&gt;
&lt;p&gt;&lt;span style="line-height:1.6em"&gt;Placed on the sunny rim of a permanently-shadowed crater, or at the entrance to a cave, Transformers can be used in conjunction with rover exploration, projecting a favorable micro-environment into cold and dark areas.&amp;nbsp; These challenging sites are particularly exciting and scientifically interesting. For example, water found in the permanently shadowed areas of craters on the Moon or Mercury can reveal clues about planetary formation and history, and could be used as a resource for astronauts. Cave exploration on Mars offers the possibility of finding extraterrestrial life; furthermore, caves are time capsules preserving geochemical traces and may safely shelter future human explorers.&lt;/span&gt;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;This project will perform real-time collection of prognostic valve operational data by deploying smart eddy-current probes with the use of the MTconnect&amp;reg; system, and demonstrate its value within an operational environment.&amp;nbsp; The MTconnect&amp;reg; system provides an abundant amount of significant operational information without requiring numerous sensors to be deployed. The MTConnect system will be installed within the Liquid Nitrogen (LN2) Pump facility for integration with the smart eddy-current valve probes.&amp;nbsp; This process will include updating the LN2 pumping facility&amp;rsquo;s Autonomous Monitoring and Managing Utility (AMMU) with an enhanced TEAMS model so that the smart sensor probes can be incorporated for use.&amp;nbsp; The addition of these new probes will provide an abundant amount of supplementary information about the operational health of the evaporator systems.&amp;nbsp; This information will enable the AMMU to better identify degraded valve performance before it can impact facility operation.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;If successful, the LBR will allow high spatial and spectral resolution follow-on studies from missions such as Herschel, Spitzer, and SOFIA to be performed at a fraction of the cost of space-based systems. The large collecting area of the LBR will also permit sensitive limb sounding studies of the Earth&amp;#39;s atmosphere to be made and serve as a powerful tool for realizing communication networks for low-power ground stations or surveillance activities.&lt;/p&gt;
&lt;p&gt;We propose a revolutionary electro-optical (EO) imaging sensor concept that provides a low-mass, low-volume alternative to the traditional bulky optical telescope and focal plane detector array. This imaging sensor concept consists of millions of direct detection white-light interferometers densely packed onto photonic integrated circuits (PICs) to measure the amplitude and phase of the visibility function at spatial frequencies that span the full synthetic aperture. Our approach replaces the large optics and structures required by a conventional telescope with PICs based on emerging photonic technologies which are produced by standard lithographic fabrication techniques (e.g., CMOS fabrication). By integrating advanced optical interferometry and photonics technologies, this new EO imaging sensor concept enables exciting new NASA outer planet missions since it provides a large-aperture, wide-field EO imager at a fraction of the cost, mass and volume of conventional space telescopes. As part of the initial investigations, we will study several areas tailored to potential NASA missions and requirements including, development an imaging model for potential interferometer array geometries and low light environments, evaluation of PIC architectures and corresponding signal-to-noise models, and development of a technology roadmap that addresses unique NASA mission requirements such as survivability in high radiation environments.&lt;/p&gt;
&lt;p&gt;This project identified specific knowledge and expertise in radioactive hydrogen effluent filter technology, so that internal resources on NTP engine exhaust scrubbing system technologies and design could be augmented. The goal was to advance the technical immaturity of the direct gas treatment (effluent scrubbing) approach; and to investigate filtering feasibility and identify design requirements.&amp;nbsp; The scope of this effort is to identify and research the latest technologies in radioactive effluent scrubbing comparable to the relative magnitude and needs of a NTP engine and stage vehicle development, as well as to scope and estimate the cost of the specific work and effort associated with and required for the development of a hot hydrogen scrubber system that would support NASA&amp;rsquo;s NTP engine and stage development goals.&lt;/p&gt;
&lt;p&gt;Small, light-weight and low-cost missions will become increasingly important to NASA&amp;#39;s exploration goals. Ideally teams of small, collapsible robots, weighing only a few kilograms apiece, will be conveniently packed during launch and would reliably separate&amp;nbsp;and unpack at their destination. Such robots will allow rapid, reliable in-situ exploration of hazardous destination such as Titan, where imprecise terrain knowledge and unstable precipitation cycles make single-robot exploration problematic. Unfortunately&amp;nbsp;landing lightweight conventional robots is difficult with current technology. Current robot designs are delicate, requiring a complex combination of devices such as parachutes, retrorockets and impact balloons to minimize impact forces and to place a robot in a&amp;nbsp;proper orientation. Instead, we are developing a radically different robot based on a &amp;quot;tensegrity&amp;quot; built purely upon tensile and compression elements. Such robots can be both a landing and a mobility platform allowing for a dramatically simpler mission profile&amp;nbsp;and reduced costs. These multi-purpose robots can be light-weight, absorb strong impacts, are redundant against single-point failures, can recover from different landing orientations and are easy to collapse and uncollapse. These properties allow for unique mission profiles that can be carried out with low cost and high reliability. We believe tensegrity robot technology can play a critical role in future planetary exploration.&lt;/p&gt;
&lt;p&gt;Conceptual existence of circumnavigation routes was speculated in the proposing team&amp;rsquo;s Phase I NIAC research, but at that time terrain model resolution was too low to enable accurate route-finding, and fidelity of terrain knowledge was too low for validation of route existence. The Lunar Reconnaissance Orbiter (LRO), Mars Reconnaissance Orbiter (MRO), and Messenger missions have changed that fact: detailed surface maps now exist for the Moon, Mars, Mercury, and some asteroids, and the time is right for a great leap of viability for the visionary concept of Nomadic Exploration.&lt;/p&gt;&lt;p&gt;The proposed research will discover and characterize the first Nomadic Routes to encircle planets, dwell at peaks, and circumnavigate asteroids. Research thrusts in sensing and planning technologies for rover energetics, speed, and autonomy will make the great leaps necessary for Nomadic expeditions like equatorial circumnavigation. Magellan Routes on the Moon will be discovered by applying resource-aware planning methodology to terrain, solar, and thermal data acquired in recent missions. These concepts will be extended to asteroids with slow orbital periods that might allow for sun following in very low gravity and for seasonal polar missions to Mars. Demonstration of critical concepts will occur in simulated and physical test-beds tuned to emulate the parameters of terrain, illumination, temperature and gravity essential for these missions.&lt;/p&gt;
&lt;p&gt;In Phase I we were able to demonstrate that sample return missions utilizing high velocity penetrators (0.1- 1 km/s) could provide substantial new capabilities for sample return missions at lower cost than soft landing techniques. Key innovations include new energy absorbing material, and utilization of tethers for deployment of the penetrator and extraction of the sample, to reduce the DeltaV requirements while maximizing the probability of return , and minimizing the components that could be damaged by a hard impact.&lt;/p&gt;&lt;p&gt;The work also incorporated proof-of-concept field testing of components under relevant environments. The proposed work seeks to (a) expand the modeling of the interaction of the penetrator with the surface material so that penetration depth can be more accurately predicted for different types of materials likely to be encountered at different solar system objects, (b) enhance the properties of the energy absorbing materials to handle speeds up the upper ranged for planned impacts, and (c) to perform field testing of the tether extraction of the return sample and refine the simulations of the tether dynamics. In addition, the proposed work has the potential for allowing electronic enabled penetrators which could for example be used for seismic imaging of the interior. Because of the ability to provide multiple samples, the full system which would be developed in greater detailed in Phase II will provide unprecedented analysis&amp;nbsp;of the interior structure of a solar system object. Our ability to perform modeling, lab testing and field experiments will enable the system to go for TRL2 to TRL4/5 within 2 yrs.&lt;/p&gt;
&lt;p&gt;Develop a comprehensive understanding of requirements for a facility that could safely conduct effluent treatment for a Nuclear Thermal Propulsion (NTP) rocket engine system.&amp;nbsp; Methodology options that could be implemented for NTP effluent treatment are being compiled and evaluated.&amp;nbsp; NTP effluent treatment is necessary to ensure compliance with environmental and safety standards associated with any potential release of radioactive species.&amp;nbsp; The types of rocket engines reactors and fuel elements under consideration will affect the effluents mitigation technologies and the monitoring capabilities that could ultimately be utilized for an NTP rocket engine testing facility. Therefore, an extensive understanding of the current state-of-the-art related to effluent technologies is required, which includes exploring innovative effluent treatment options, so that the safest and most optimal decision making can be recommended for an NTP ground testing system facility. Review of such systems and consideration of other recent developments in offgas treatment should be conducted in support of planning for future NTP testing activities.&lt;/p&gt;
&lt;p&gt;The purpose of this project is to develop lunar regolith based geopolymer concrete and perform differential shielding studies on various geopolymer formulations to determine if sufficient protection from radiation in space environments can be enabled. For the initial testing of these concrete matrices, a variety of locally-available radiation sources will be used. As part of the proposed work, geopolymer and &amp;lsquo;Lunamer&amp;rsquo; concrete matrices will be constructed and their ability to shield radiation will be evaluated. The geopolymer matrices will be prepared using fly ash as the pre-curser, barite (BaSO4) and hematite (Fe2O3) as the aggregate and metallic chips, representing the state-of-the-art in Earth-based construction practices. The &amp;lsquo;Lunamer&amp;rsquo; concrete matrices will be made using geopolymerized lunar regolith with entrained carbon fibers and carbon black for EMI shielding and metallic chips. These will include radiation energies within this range of biological interest, but will also include those of lower energies. While such low energy sources cannot be used to correlate the biological impact of high energy radiation, they do provide a useful tool to quantify the relative shielding behavior of different materials.&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The purpose of this project is to develop a spectrally adaptable floor-stand smart-lamp. Intelligently mixing different narrow band color light sources can produce a wide range of light quality which can affect human performance. This smart-lamp will be designed and constructed so that illumination can be adjusted, depending on the need. Discrete color Light Emitting Diodes (LEDs) will be used as the light source, and illumination and individual color brightness will be controlled by a micro-computing device that will have the capability to adjust light levels based upon the need. An efficient diffuser will be used to eliminate the point source emissions of the LED light sources, mix the individual colors and produce pleasant diffuse illumination.&lt;/p&gt;
&lt;p&gt;&lt;strong&gt;The objective of this project is to precisely control the flow of thermal, electrical and thermoelectrical energy by advancing the development of a new class of thermoelectric (TE) materials. The goals of this project are to (1) optimize metamaterial structure so power generation efficiency can be increased; (2) synthesize high power factor materials once deemed inappropriate for efficient thermoelectrical operation due to their large thermal conductivity; (3) assemble and test a thermoelectric module with an optimized TE metamaterial; and then finally, (4) characterize, on a micron scale, the thermal behavior of the metamaterial. Thermal behavior must be experimentally characterized, under a variety of operating conditions, using a research grade infrared (IR) camera. The results will enable validation studies with finite element models.&lt;/strong&gt;&lt;/p&gt;
&lt;p&gt;The Coiled Brine Recovery Assembly (CoBRA) project will result in a proof-of-concept demonstration for a lightweight, compact, affordable, regenerable and disposable solution to brine water recovery. The heart of CoBRA is an evaporator that produces water vapor from brine. This evaporator leverages a novel design that enables passive transport of brine from place to place within the system. While it will be necessary to build or modify a system for testing the CoBRA concept, the emphasis of this project will be on developing the evaporator itself. This project will utilize a &amp;ldquo;test early, test often&amp;rdquo; approach, building at least one trial evaporator to guide the design of the final product.&amp;nbsp;&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Q-thruster technology is a mission enabling form of electric propulsion and is already being traded by NASA&amp;#39;s Concept Architecture Team (CAT) &amp;amp; Human Space Flight (HSF) Architecture Team (HAT) as an electric propulsion effector for Asteroid Recovery Vehicle (ARV) mission extensibility options out to Mars.&amp;nbsp; The Nuclear Electric Propulsion mission allows for rapid transit while allowing for a heavy, more near-term reactor design and the Solar Electric Propulsion mission allows for a power starved approach with similar mission durations to Design Reference Architecture - DRA 5.0 that would not be possible without the Q-thruster technology.&lt;/p&gt;
&lt;p&gt;As manufacturing technologies have matured, it now appears possible to build all the major components and subsystems of an upper stage-class rocket engine for substantially less money and much faster than traditionally done. However, several enabling technologies must be developed before that can happen. This activity will address these technologies and demonstrate the concept by designing, manufacturing, and testing the critical components of a rocket engine. The processes developed and materials&amp;rsquo; data will be transitioned to industry upon completion of the activity.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;Technologies to enable the concept are:&amp;nbsp; copper alloy process development, AM post-processing finishing to minimize surface roughness, AM material deposition on existing copper alloy substrate, and materials characterization.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;Specifically, the LCUSP project element will (1) develop materials properties and characterization for SLM manufactured GRCop, (2) develop and optimize SLM manufacturing process for a full component GRCop chamber and nozzle, (3) develop and optimize the Electron Beam Freeform Fabrication (EBF3) manufacturing process to direct deposit a nickel alloy structural jacket and manifolds onto an SLM manufactured GRCop chamber and nozzle, and (4) demonstrate the process for integrating the engine system by performing a hot fire, resistance test.&lt;/p&gt;
&lt;p&gt;Besides serving as a launch vehicle, the carrier balloon provides a stable mount for the enclosed telescope. Looking up, the LBR will serve as a telescope. Looking down, the LBR can be used for remote sensing or telecommunication activities. By combining successful suborbital balloon and ground-based telescope technologies, the dream of a 10 meter class telescope free of ~99&#37; of the Earth&amp;rsquo;s atmospheric absorption in the far-infrared can be realized. The same telescope can also be used to perform sensitive, high spectral and spatial resolution limb sounding studies of the Earth&amp;rsquo;s atmosphere in greenhouse gases and serve as a high flying hub for any number of telecommunications and surveillance activities. LBR is a multi-institution effort between the University of Arizona (the PI institution), SWRI, JPL, and APL. LBR was selected in 2013 by the NASA Innovative Advanced Concepts (NIAC) program to proceed into Step B of the NIAC Phase I program. This makes LBR eligible to propose for a 2014 Phase II award. The goal of our NIAC Phase II effort is to bring LBR concepts to a Technology Readiness Level of at least 2 in maturity, by addressing key unknowns, assumptions, risks, and paths forward remaining after the completion of our Phase I study.&lt;/p&gt;
&lt;p&gt;The objective of this project is to determine the engineering techniques required to manufacture complex, thin-shelled instrument structures. These techniques will be validated through the end-to-end development of a functional imaging instrument.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Our main objective in this study is to design, fabricate, and analyze the partially transparent petaled&lt;br /&gt;(PTP) masks using gray scale lithography to suppress the diffracted light along the optical axis of&lt;br /&gt;secondary mirror of the New Space-based Gravitational-wave Observatory (NGO) telescope.&lt;/p&gt;
&lt;p&gt;Geomagnetic storms drive geomagnetically induced currents (GIC) in high-voltage power transmission systems worldwide. GIC distribution in the transmission system is a function of the large-scale surface geoelectric field and DC characteristics of the transmission system. Geoelectric field carries information about magnetospheric-ionospheric electric current systems and geological structures. It is common to use information about magnetospheric-ionospheric electric current systems or geomagnetic field variations on the ground together with geological and transmission system description to model GIC. However, no work or technology exists for inverting spatiotemporal space physical and geological information from extensive distributed GIC observations.&lt;/p&gt;&lt;p&gt;We will utilize the US high-voltage power transmission system for the first time as a science tool to map large scale GIC&amp;rsquo;s. Large-scale application of the set up will allow unprecedented, game changing, extraction of space physical and geological information over wide range of spatial and temporal scales. Further, the new GIC observation set up can be turned into a valuable resource for the power transmission industry.&lt;/p&gt;&lt;p&gt;We envision that the large-scale implementation of the concept can be carried out in collaboration with the industry and other federal agencies after the 1-year pilot phase. With sufficient funds, full-scale implementation of the concept with a larger number of GIC observation sites can be achieved within 2-3 years after the pilot phase.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;An ideal integrating bolometer can achieve breakthrough sensitivity in IR photon detection by removing practical barriers to extreme thermal isolation of the absorber.&amp;nbsp; In the first quarter of FY14, the effort will be focused on design of the IIB, with the goal of having a layout ready by the beginning of the calendar year.&amp;nbsp; During this period, we will also design parts needed for the test facility and start fabrication.&amp;nbsp; In the second quarter, the IIBs will be fabricated.&amp;nbsp; Also during this period, the test facility will be assembled and dry run testing completed.&amp;nbsp; In the third quarter, the IIB samples will be installed in the cryostat and tested. The final quarter will be dedicated to further debugging and testing the IIB samples, and completing the final report.&lt;/p&gt;
&lt;p&gt;The goal is to complete process development to make OFET&amp;rsquo;s on flexible substrates compatible with ultra-lightweight deformable mirrors and to demonstrate simplified active device integration process with a functional deformable mirror as a precursor for future integrated circuit development.&lt;/p&gt;
&lt;p&gt;Conventional high reflectance optical coatings consisting of multilayer stacks of alternating high and low refractive index dielectric materials can achieve high reflectivity and low loss over the visible to the near infra red range.&amp;nbsp; &lt;em&gt;Unfortunately, conventional all-dielectric interference optical coating technologies are not viable for making these components in the mid to far-infrared range due to large thick&amp;shy;nesses required and the lack of materials with low enough absorption at those wavelengths. &lt;/em&gt;The task becomes even harder since the coatings typically have to operate at a cryogenic temperature: mul&amp;shy;tilayered dissimilar materials inevitably crack and delaminate from the substrate surface due to thermal expansion mismatch.&lt;/p&gt;
&lt;p&gt;In this one year research project, we propose to do the following four tasks;&lt;/p&gt;&lt;p&gt;(1) Design the silicon wafer X-ray mirror demo unit and develop a ray-tracing code to estimate the mirror performance. We will need to determine detailed parameters of the unit, such as size of the silicon wafer, their angle and pitch.&lt;/p&gt;&lt;p&gt;(2) We have to find a wafer processed by the &amp;ldquo;right&amp;rdquo; method suitable for our application: appropriately flat and thin. We will procure the silicon wafers and measure the surface flatness using an optical interferometer.&lt;/p&gt;&lt;p&gt;(3) Design a holding structure of the silicon wafer and place them in the K-B system configuration. The structure should be able to place the wafers in micron accuracy. If the machining accuracy doesn&amp;rsquo;t allow us to do this, we would need to develop a method to align the wafer.&lt;/p&gt;&lt;p&gt;(4) Once we have the manufacturing drawing, we will need to identify the manufacturer and fabricate the designed housing. Then we will assemble the first demonstration unit, and measure its performance at the X-ray beamline. The X-ray test results will be compared with ray-tracing simulations and used for the further developments in the future.&lt;/p&gt;
&lt;p&gt;Here, we propose to develop a breadboard laser system that is capable of producing radiation in two UV wavelengths.&amp;nbsp; This Selectable Output Ultraviolet Laser (SOUL) system will utilize an existing solid-state laser infrastructure, as well as a series of nonlinear frequency conversion crystals to up-convert the fundamental laser wavelength to deep UV wavelengths.&amp;nbsp; A piezoelectric steering mechanism will enable the SOUL system to alternate between these UV output wavelengths at a rate of several hundred Hz.&lt;/p&gt;&lt;p&gt;This proposed system will also offer a &amp;ldquo;burst mode&amp;rdquo; of operation similar to the MOMA flight laser being developed by Laser Zentrum Hannover e.V.&amp;nbsp; The design proposed here will be more thermally robust and thus require shorter recovery times compared to the MOMA laser.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp; Our effort will focus on the difficult task of designing, implementing and demonstrating a multi-staged UV-producing train of optics capable of switching between two different output wavelengths with variable output power. The success of the nonlinear portion of the total system lies primarily with the choices of materials, operating environments, laser wavefront and power control, and optical layout. The selectability of this prototype laser for upcoming mission opportunities will depend not only on the performance of the instrument, but in the compactness (mass and volume), robustness (operational conditions and survivability), and power requirements of the design.&lt;/p&gt;
&lt;p&gt;This activity will significantly increase the fidelity of the miniaturized component packaging of the &amp;micro;-CIT mass spectrometer assembly. Our design approach emphasizes the smallest feasible footprint, combining MEMS MS component integration, and the use of ultra-high vacuum (UHV) materials and techniques for fabrication of the final package. Final package systems designs and component parts have been fabricated using micro fabrication capabilities and MEMS processing.&amp;nbsp; Assembly and integration of the package takes advantage of existing packaging expertise, materials, and tooling. The component packaging system will be evaluated for form, function, outgassing, and vibration here at GSFC.&lt;/p&gt;
&lt;p&gt;Nuclear power systems&amp;nbsp;enable human and robotic exploration missions to solar system locations where other power system&amp;nbsp;alternatives&amp;nbsp;are infeasible, such as deep space or the dark and dusty surface of Mars.&amp;nbsp; Currently, Radioisotope Power Systems fueled by Plutionium-238 can be used for missions needing a few hundred watts, and NASA is demonstrating the technology that would be needed for tens to hundreds of kilowatts for human outposts on planetary surfaces (see the Nuclear Systems Project in Techport).&amp;nbsp; A gap exists in the 1-10 kilowatt regime for higher power science missions that would consume large portions of the world&amp;rsquo;s limited Pu-238 supply, as well as for lower power elements of human exploration missions.&amp;nbsp; A NASA/Department of Energy nuclear demonstration in 2012 at the Nevada National Security Site provided proof-of-principle benchtop validation that the technology needed for small fission power systems works, and can fill this gap.&amp;nbsp;&amp;nbsp; The Kilopower Small Fission Systems Project will advance this technology in three years to readiness for near term space missions by conducting a full-scale nuclear demonstration of a space-capable small fission power system in a relevant environment.&lt;/p&gt;
&lt;p&gt;This effort utilizes the high elastic strain limit and net-shaped processing of metallic glasses to fabricate low-cost harmonic drives that outperform steel.&amp;nbsp; The harmonic drive design and performance will be modeled and a 3D polymer version will be printed.&amp;nbsp; A harmonic drive will be fabricated from commercially die cast bulk metallic glass parts.&lt;/p&gt;
&lt;p&gt;The task objective is to develop a gamma ray scintillator technology with subnanosecond temporal resolution and the capability to withstand unprecedented rates and doses of high energy gamma radiation. This is a joint project with Caltech Prof. Dave Hitlin to detect BaF2 fast scintillation (&amp;tau;&amp;nbsp;~&amp;nbsp;0.9ns at &amp;lambda;&amp;nbsp;~&amp;nbsp;220nm) while rejecting slow scintillation (&amp;tau;&amp;nbsp;~&amp;nbsp;650ns at &amp;lambda;&amp;nbsp;~&amp;nbsp;330nm). We will also develop solar blind coatings using ALD technology for DUV bandpass filter.&lt;/p&gt;
&lt;p&gt;This task is to collaboratively design and fabricate the free-form WIRIS telescope primary mirror with our partner Zygo as a technology demonstration. Fabricating the primary is challenging as it has 865 um of aspheric departure and is not rotationally symmetric.&lt;/p&gt;
&lt;p&gt;The task goal is to develop and demonstrate an innovative software architecture, the &amp;ldquo;Resilient Spacecraft Executive&amp;rdquo;, that will enable highly-resilient spacecraft and reduce future mission risk and cost. We will develop resilient execution capability that is easily deployable and can handle multiple novel situations. The task will also mature and integrate technologies such as risk-aware execution, correct-by-construction control policy synthesis, and model-based systems engineering.&lt;/p&gt;
&lt;p&gt;This research project is evaluating an innovative technique that uses fiber optic strain sensors to measure structural deformations and full field strains. An inverse finite element method (iFEM) analysis reconstructs a deformed structural shape based on the strain measurement data simulated by FEM analysis to represent the &lt;em&gt;in-situ&lt;/em&gt; strain measurements. By mapping the iFEM displacement solution onto a full FEM model, without the applied loading, the complete fields of displacement, strain, and stress are reconstructed to a high degree of accuracy. This project supports the work on multiple flight research projects at NASA Armstrong.&lt;/p&gt;&lt;p&gt;&lt;strong&gt;Work to date&lt;/strong&gt;: The team has completed and validated a 1-dimensional beam element test using a compliant slider mechanism.&lt;/p&gt;&lt;p&gt;&lt;strong&gt;Looking ahead&lt;/strong&gt;: Future plans involve developing and validating the algorithm on a full size flight test article.&lt;/p&gt;&lt;p&gt;&lt;strong&gt;Benefits&lt;/strong&gt;&lt;/p&gt;&lt;ul&gt;&lt;li&gt;&lt;strong&gt;Accurate&lt;/strong&gt;: Algorithm is capable of accurate full-field structural shape and strain measurement&lt;/li&gt;&lt;li&gt;&lt;strong&gt;Economical&lt;/strong&gt;: Uses a minimum number of sensors to recreate the full-field structural deformations and strains&lt;/li&gt;&lt;li&gt;&lt;strong&gt;Improves safety&lt;/strong&gt;: Enables more efficient health monitoring of control surfaces and flexible structures&lt;/li&gt;&lt;/ul&gt;&lt;p&gt;&lt;strong&gt;Applications&lt;/strong&gt;&lt;/p&gt;&lt;ul&gt;&lt;li&gt;Aircraft wing flaps&lt;/li&gt;&lt;li&gt;Helicopter blades&lt;/li&gt;&lt;li&gt;Motor vehicles&lt;/li&gt;&lt;li&gt;Trains&lt;/li&gt;&lt;li&gt;Ships and submersibles&lt;/li&gt;&lt;li&gt;Wind turbines&lt;/li&gt;&lt;/ul&gt;
&lt;p&gt;The &amp;ldquo;Beach Ball&amp;rdquo; Coronagraph will be the first steps to simplify and revolutionize the next generation solar coronagraph design.&amp;nbsp; The solar corona is the source region of solar eruptions, both solar flares and coronal mass ejections (CMEs).&amp;nbsp; These eruptions are initiated above the solar surface in a region inside 2.5 solar radii from the Sun center. In observing the solar corona in this region using visible light, the contributions from the solar disk far outweigh, by orders of magnitude, the coronal loop observations of interest to study the initiation of these large eruptions.&amp;nbsp; The advent of the solar coronagraph, where an occulting disk is placed over the solar disk to block the dominant source of on-disk light, is used in order to make the observations of the dimmer coronal loops.&amp;nbsp; The major source of noise then in coronagraphs is now dominated by diffraction of light from the solar surface off the occulter. A &amp;quot;beach ball&amp;quot; coronagraph occultor with formation flying distance of 100+ feet can provide significant increase in the science capabilities possible.&lt;/p&gt;
&lt;p&gt;The key challenge for reducing a traditional satellite to such a small size is to remove the maximum possible functionality that is not critical for creating a working spacecraft. This includes moving as much functionality as possible from the sensor node to a host system (e.g. mothership or ground station). This process is extremely critical of functions that consume mass, power, or volume such as attitude controllers, sophisticated sensing systems, and redundancy.&lt;/p&gt;&lt;p&gt;Previous methods for separating special from temporal evolution include formations of a few large spacecraft. MMS and STEREO are examples. These prior missions have the drawback of being very expensive and being limited to only a few spatial measurements at a time.&lt;/p&gt;&lt;p&gt;The purpose of this effort is to develop a concept for how to construct a spacecraft platform that will enable sensing systems to be reduced in size to a very small (~50cm&lt;sup&gt;3&lt;/sup&gt;), wireless package that can be utilized in distributed space sensing systems, particularly for in-situ measurements. The innovations that were explored include energy harvesting and management, GPS tracking, electronic integration and mechanical packaging.&lt;/p&gt;
&lt;p&gt;The objective of this project will be to migrate some of the outputs from the WFF Mission Planning Lab (MPL) into a real-time visualization system.&amp;nbsp; The MPL is responsible for generating pre-flight RF margin link analysis, mission simulation &amp;amp; visualization, and other products for WFF missions.&amp;nbsp; This real-time visualization system would depict in 3D graphics the position and orientation of the launch vehicle(s) or suborbital carrier (UAV, sounding rocket), VIRTEx would be expanded to use a more flexible publish/subscribe architecture, and the system will leverage recently developed advanced telemetry and data handling systems within the Range network.&lt;/p&gt;&lt;p&gt;Another main objective will be updating VIRTEx to support a sounding rocket mission which is scheduled to launch from NASA Wallops Flight Facility (WFF) in the summer of 2014.&lt;/p&gt;&lt;p&gt;This project will also be used to demonstrate the successful attitude data conversion from a WFF telemetry system.&amp;nbsp; Updates are being finished on this telemetry system that convert various NASA Sounding Rocket attitude control systems (ACS) data formats.&amp;nbsp; Multiple ACS systems output different data formats, so libraries and algorithms were added to the telemetry system to convert this data into a standard yaw, pitch, and roll dataset for Range Safety.&amp;nbsp; VIRTEx will be able to easily show this data and will be able to compare it to the pre-flight attitude predictions.&lt;/p&gt;
&lt;p&gt;Our objective is to develop MENSA as a highly integrated planetary radio and digital spectrum analyzer cubesat payload that can be deployed as a satellite instrument or reside on a rover. We will also develop the supporting signal processing algorithms to perform spectral analysis and event detection of the various environments that are sensed by the system.&lt;/p&gt;&lt;p&gt;The end goal is to deliver MENSA as a flexible, minimum Size Weight and Power (SWaP) system that&amp;nbsp;for near-term Planetary Science. To save costs, the system will be developed using all commercial parts that have radiation tolerant flight part equivalents.&lt;/p&gt;
&lt;p&gt;This IRAD will advance the technology to provide a stellar sensor that may be used for astrometric alignments necessary for Formation Flying/Relative Navigation related missions.&lt;/p&gt;&lt;p&gt;The objective of this project is to develop an advanced stellar sensor for astrometric alignment and other challenging SmallSat-class Formation Flying/Relative Navigation missions such as the Virtual Telescope (VT) concept.&lt;/p&gt;
&lt;p&gt;Thermal control of small spacecraft, including CubeSats, is a challenge for the next era of NASA spaceflight. Science objectives and components will still require strict thermal control while smaller volumes will inherently absorb and shed heat more quickly than a larger body. Thus, game-changing technologies must be developed to stabilize the thermal environment inside of small spacecraft. Developing this technology will help place Goddard at the forefront of thermal control expertise in the fast-growing arena of smallsats and CubeSats.&lt;/p&gt;&lt;p&gt;The proposed CubeSat louver assembly will be based upon the proven designs of full-sized louvers for large spacecraft. Internal spacecraft components will be thermally coupled to the side of the spacecraft. Bimetallic springs serve as a passive control mechanism for opening and closing flaps. As the&amp;nbsp;spacecraft heats&amp;nbsp;up the springs expand due to the difference in thermal expansion rates of their two fused metals (hence bimetallic). This opens the flaps, changing the thermal radiation properties of the exterior surface. As the spacecraft cools the flaps close and return the exterior surface to the previous emissivity. These temperature-driven adjustments create a more stable thermal environment for components.&lt;/p&gt;&lt;p&gt;Analysis of the thermal louvers assumed that the louvers were in darkness, either shielded by the solar panels or facing deep space. The hand calculations of power dissipated via the thermal louvers shows a substantial difference between fully closed and fully open louvers at the high temperatures significant for electrical components.&lt;/p&gt;
&lt;p&gt;Our main objective in this study is to design, fabricate, and analyze the partially transparent petaled (PTP) masks using gray scale lithography to suppress the diffracted light along the optical axis of secondary mirror of the New Space-based Gravitational-wave Observatory (NGO) telescope.&lt;/p&gt;
&lt;p&gt;&lt;em&gt;The purpose of this project is to design, fabricate, and characterize a &lt;u&gt;D&lt;/u&gt;ynamic &lt;u&gt;O&lt;/u&gt;n-&lt;u&gt;C&lt;/u&gt;hip &lt;u&gt;Fl&lt;/u&gt;ow &lt;u&gt;a&lt;/u&gt;nd &lt;u&gt;T&lt;/u&gt;emperature &lt;u&gt;S&lt;/u&gt;ensor (DOCFlaTS) to mature and enable miniaturized lab-on-a-chip microfluidic instruments for a future missions to planetary satellites and primitive bodies. &lt;/em&gt;&lt;/p&gt;&lt;p&gt;&lt;em&gt;We will design a temperature and flow sensor that will be compatible with other NASA funded micro fluidic systems. This design is a proof-of-concept sensor that has the ability to sense temperature &lt;/em&gt;&lt;em&gt;and flow rate changes&lt;/em&gt;&lt;em&gt;. Furthermore, this can be calibrated using macro-scale systems.&lt;/em&gt;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The objectives of this effort are to measure atmospheric backscatter profiles and temperature using a zenith looking lidar, designed for a small lander.&lt;/p&gt;&lt;p&gt;The lidar will also measure temperature by scanning over two adjacent CO&lt;sub&gt;2&lt;/sub&gt; lines at 1572 nm that have different temperature sensitivities.&lt;/p&gt;
&lt;p&gt;We will demonstrate the usefulness of SIL for GSFC missions by attempting to compile the SIL source code with an autocoded sample GNC application flight software. &amp;nbsp;We will then attempt to execute the compiled GNC CFS applications on test flight hardware, collect performance data, and then document our results. &amp;nbsp;If possible, we will attempt to expand its functionality with regards to fault reporting, telemetry processing, and time management.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;CIRS-lite is a lightweight&amp;nbsp; version of the CIRS 43-kg Fourier transform spectrometer (FTS) currently returning data from Saturn.&amp;nbsp; CIRS-lite is of interest to planetary science as a high resolution&amp;nbsp; FTS, capable of a broad spectral range.&amp;nbsp; CIRS-lite is physically much smaller and far less massive than Earth science instruments.&amp;nbsp; For Earth science, CIRS-lite is envisioned as a 2-D imaging FTS covering the infrared spectral region to study the global distribution and rate of change of methane and other greenhouse gasses (carbon dioxide, water vapor, nitrous oxide) at regional and national scales.&amp;nbsp; CIRS-lite would register localized changes in spectroscopy with geographic patterns to distinguish anthropogenic activities (industry, agriculture, fossil fuel burning, etc.) from natural environmental changes such as melting permafrost, forest fires, wetland changes and the like.&amp;nbsp; CIRS-lite would also investigate the radiative role of water vapor and clouds.&amp;nbsp; The overall science contribution is the study of chemical and physical phenomena that influence climate change and the carbon budget.&lt;/p&gt;&lt;p&gt;CIRS-lite has significantly lower demands for mass, volume, and power relative to other Earth Science spectrometers, so it can fly on most space platforms or as a hosted payload.&lt;/p&gt;
&lt;p&gt;Our new detection concept uses two new technologies: improved optical filters and tunable fiber lasers.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The proposed technique will reduce parts count, mass, and, in particular, power consumption of an airborne or spaceborne phased-array radar system.&lt;/p&gt;
&lt;p&gt;Precisely identifying the species of cosmic-ray nuclei detected by a satellite or balloon instrument requires the use of several complementary detector systems. In particular, determining the nuclear charge of an incident nucleus, and so the element to which it belongs, requires precise measurements of the differential energy loss of the particle passing through a well-characterized layer of material, the velocity of the particle, and its trajectory. The goal of this project is to improve detectors for these measurements.&lt;/p&gt;
&lt;p&gt;In this study, we are only addressing the bore-sight changes due to internal instrument motions (tip/tilt). &amp;nbsp;The roll alignment jitter component will need to be monitored and controlled by the S/C platform.&lt;/p&gt;
&lt;p&gt;RFI is an increasingly important factor in the quality performance of radiometer instruments while the quantity of usable microwave measurements is decreasing due to the presence of RFI. Because of the widespread use of wireless communications such as cellphone and satellite TV, the frequencies reserved for the science community are seeing more and more contamination.&amp;nbsp;In particular, no scientific data can be retrieved for the heavily RFI contaminated region. This problem led to the Soil Moisture Active Passive (SMAP) mission implementation of an RFI detection capability on its radiometer digital backend. However, this instrument is limited by the sampling speed and processing resources available. In particular, the digital backend frequency bandwidth is limited to 24MHz. This shows that the spaceflight technology for RFI detection is limited any the higher frequencies for K, Ka band or beyond.&lt;/p&gt;&lt;p&gt;&lt;strong&gt;This effort proposes a game-changing, higher frequency RFI detection and mitigation digital backend for microwave radiometers.&lt;/strong&gt;&amp;nbsp;&lt;strong&gt;Prototyping a high frequency RFI detection instrument &lt;/strong&gt;by combining the GREX system with a new RFI detection algorithm based on information theory and complex-valued signal processing.&lt;/p&gt;
&lt;p&gt;The three goals of this IRAD are:&lt;/p&gt;&lt;p&gt;1.1 Research and develop the Hilbert-Huang Transform for 2D second and last component &amp;ndash; the Hilbert Spectral Analysis for 2D (HSA2) and complete the HHT2 theory;&lt;/p&gt;&lt;p&gt;1.2 Develop the engineering tool for a direct decomposition of the RFI-contaminated signal into 2D or bi-dimensional Intrinsic Mode functions (BIMFs) and use the BIMFs to recover RFI-contaminated science data points by HSA2;&lt;/p&gt;&lt;p&gt;1.3 Verify the new technology tool prototype by a controlled drone experiment at Wallops, comprising a miniature radiometer, a controlled RFI source, and science data processing on the ground.&lt;/p&gt;
&lt;p&gt;The objective of this IRAD is to establish in-house onboard OpNav measurement data processing capabilities through software development and testing.&amp;nbsp; Software development will include: 1) celestial and terrain-relative OpNav data processing, 2) high-fidelity camera modeling, and 3) onboard orbit determination software integration and testing.&lt;/p&gt;&lt;p&gt;Upon successful completion of this IRAD, enhancements to the Goddard Enhanced Onboard Navigation System (GEONS) will allow onboard orbit determination using optical navigation image data for interplanetary and small body spacecraft operations.&amp;nbsp; GEONS will ingest and process celestial and terrain-relative OpNav data in the form of control points (pixel/line) located in an image.&amp;nbsp; The processed measurements are then used to supplement radiometric data in the onboard orbit determination solution and produce real-time estimates of the spacecraft&amp;rsquo;s position and velocity relative to the target body.&amp;nbsp; The resulting navigation solutions will enable near-real time control, maneuver planning, and hazard avoidance for complex proximity operations.&amp;nbsp; GEONS was chosen as the target platform because of its high heritage and operational use as an onboard spacecraft navigation system.&lt;/p&gt;
&lt;p&gt;For this program, we are partnering with Stanford University, who will provide CDM multiplexers. We will assemble the&amp;nbsp;multiplexers&amp;nbsp;into a scalable detector test configuration to demonstrate operation and evaluate the achievable multiplex factors. The final result of this work will be to build and demonstrate a complete end-to-end CDM-based SQUID readout of a far-IR bolometer array.&amp;nbsp;Stanford will develop and provide the multiplexers; Goddard will purchase and assemble the electronics and software necessary to use the multiplexers; Goddard will fabricate and integrate a small TES bolometer array in a package customized for this purpose.&lt;/p&gt;
&lt;p&gt;The objective of this IRAD is to advance the TRL of the PPU to 6.&amp;nbsp; This includes supporting GRC with requirements review and validation, design updates and hardware modifications, assessment of parts selection and radiation analysis and FPGA board development.&lt;/p&gt;&lt;p&gt;The ultimate goal of the effort is to fabricate and flight qualify a prototype PPU whose design can be implemented with the other NEXT components.&lt;/p&gt;
&lt;p&gt;This activity will significantly increase the fidelity of the miniaturized component packaging of the &amp;mu;-CIT mass spectrometer assembly. Our design approach emphasizes the smallest feasible footprint, combining MEMS MS component integration, and the use of ultra-high vacuum (UHV) materials. This activity will significantly increase the fidelity of the miniaturized component packaging of the &amp;mu;-CIT mass spectrometer assembly. Our design approach emphasizes the smallest feasible footprint, combining MEMS MS component integration, and the use of ultra-high vacuum (UHV) materials and techniques for fabrication of the final package. Final package systems designs and component parts have been fabricated using micro fabrication capabilities and MEMS processing. Assembly and integration of the package takes advantage of existing packaging expertise, materials, and tooling. The component packaging system will be evaluated for form, function, outgassing, and vibration here at GSFC.&lt;/p&gt;
&lt;p&gt;The proposed work focuses on the evaluation and testing of the W-band SSPA on the current airborne Cloud Radar System (CRS) transceiver so that it can be operated with either the original Klystron-based transmitter, or the SSPA. We will swap in either transmitter to maintain the current EIK capability. As we gain more confidence in the SSPA-based transmitter, we will migrate entirely to this approach.&amp;nbsp; This SSPA-based transceiver will enable the usage a number of recently developed radar techniques, such as advanced versatile Tx/Rx waveform, ultra-low sidelobe pulse compression, and frequency diversity. &amp;nbsp;It is necessary to modify the hardware and firmware in order to accommodate the above new techniques. Recent advances to HIWRAP&amp;rsquo;s advanced waveform generation need to be transferred to CRS to take full advantage of the SSPA. The resulting work is readily applicable to upcoming cloud and precipitation radar spaceborne missions.&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;&lt;p&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The proposed &lt;strong&gt;&lt;em&gt;&amp;micro;Lid &lt;/em&gt;&lt;/strong&gt;system is in effect an attempt to miniaturize an extraction system to a chip-cup system with integrated heaters capable extremley hot temperatures.&lt;/p&gt;&lt;p&gt;The &lt;strong&gt;&lt;em&gt;&amp;micro;Lid &lt;/em&gt;&lt;/strong&gt;system will be composed of a silicon cup with a silicon lid, acting as the &lt;strong&gt;&lt;em&gt;&amp;micro;Lid. &lt;/em&gt;&lt;/strong&gt;The hinge structure supporting &lt;strong&gt;&lt;em&gt;&amp;micro;Lid &lt;/em&gt;&lt;/strong&gt;will be a bilayer composed of metal bilayer that upon a temperature change will actuate the bimetallic cantilever.&lt;/p&gt;
&lt;p&gt;The FOSS project primary test objectives are to demonstrate by flying on an Antares launch vehicle, the ability of FOSS flight hardware to measure strain and temperature on the launch vehicle during flight by measuring LOX and RP tank temperatures along the rocket longitudinal axis, strains on the Stage 1 thrust frame structure, and strains at several azimuths along as much of the vehicle length as practical in order to determine vehicle shape during flight.&lt;/p&gt;
&lt;p&gt;In considering targets for&amp;nbsp;human asteroid missions, there are several major factors that will make a significant difference in assessment of mission risks that can be addressed by simple photo-reconnaissance of a target. One of the most important of these factors is the spin state of the asteroid: does it rotate in a slow, easily predictable way? Asteroids that rotate very rapidly or that tumble about multiple axes present significant hazards in planning and executing proximity operations&amp;minus; especially operations that must be carried out over extended time periods.&amp;nbsp; Another consideration is the physical state of the asteroid itself: is it a coherent mass or does it consist of a gravitationally bound pile of much smaller pieces? A coherent structure is unlikely to rearrange its configuration in response to a push by an astronaut or a hardware deployment and will provide a much easier surface in which to plant anchors for astronaut mobility or to hold equipment to the surface than will a rubble pile.&lt;/p&gt;&lt;p&gt;The full success criteria entails flying by a near Earth asteroid and acquire images sufficient to determine the target volume, shape model, Asteroid spectral type and meteorite analogs, rotational properties (pole position, rotation period), orbit, debris/dust field in local environment, and regolith characteristics.&lt;/p&gt;&lt;p&gt;Meeting this requirement&amp;nbsp;addresses the need to fill Strategic Knowledge Gaps (SKG&amp;rsquo;s) related to asteroids as a precursor to subsequent safe and successful human missions.&amp;nbsp; The data obtained will also support the advancement of science interests in asteroids.&lt;/p&gt;
&lt;p&gt;The Advanced Radiation Project to date has focused on SEP events.&amp;nbsp; For long duration missions outside Earth&amp;rsquo;s geomagnetic field, the galactic cosmic ray (GCR) environment provides an even greater risk to astronauts.&amp;nbsp; Interplanetary space is filled with low fluxes of highly energetic, extremely penetrating ions believed to have been accelerated by supernova shocks in our galaxy.&amp;nbsp; These ions range from protons and alpha particles to heavier atoms such as carbon, oxygen, and iron stripped of their electrons.&amp;nbsp; These ions range in energy from a few eV to tens of GeV.&amp;nbsp; When GCR ions interact with shielding materials, secondary particles including charged ions, neutrons, pions, muons, and electrons are produced.&amp;nbsp; Under some conditions, the dose may be larger behind thick shields than behind thinner shields.&amp;nbsp; The thick GCR shield task will seek to validate the calculated shielding efficiency of hydrogen-dense materials and verify optimum GCR shield thicknesses necessary for minimal mass vehicle design.&lt;/p&gt;
&lt;p&gt;This project sought to study a catalyst consisting of a unique metal alloy and structure that could be used to ignite and sustain combustion of an advanced green monopropellant. Resistively heated microtubes of alloyed catalytic metal were designed and manufactured. These tubes will be tested under altitude conditions to examine the combustion behaviors of the system. Catalytic activation and deactivation concerns were also to be investigated.&lt;/p&gt;
&lt;p&gt;&amp;nbsp;The fabrication technology developed in this project will aid GRC in advancing &amp;nbsp;Lithium Ion Batteries (LIB) technology by developing new electrode and SSE materials to increase energy capacity and safety:&amp;nbsp; 1) high Li ion conducting electrolyte based on sulfide chemistry, 2) Li metal anode technology and 3) high capacity/high voltage cathode materials. &amp;nbsp;Lithium Ion Batteries with Li anode offer the highest theoretical capacity of all conventional battery types.&lt;/p&gt;
&lt;p&gt;The objective of the proposed work is to develop a rapid time response diagnostic using a suite of instruments for the detection of heated&amp;nbsp;polytetrafluoroethylene (PTFE) insulated wires based on chemicals and particles generated at relatively low temperatures. &amp;nbsp;The anticipated result of the proposed effort is the development of a conceptual design for an early warning system that can specifically detect the overheating of&amp;nbsp;polytetrafluoroethylene (PTFE) insulated wires. This design can be utilized as a subsystem integrated into a fully capable fire detection system.&lt;/p&gt;
&lt;p&gt;Tensegrity robots have attracted considerable attention for use in planetary exploration missions because they can be stowed into relatively small volumes before launch and are readily deployable upon landing. Because of their design and structure they can absorb significant impact shocks, such as those experienced during landing, and are well suited for use on extremely rough planetary terrains.&lt;/p&gt;
&lt;p&gt;The project will be developing a CFD approach that can handle the additional complexities needed in a NTP testing facility when modeling the combustion processes in a transient environment for fluid flows that will extend from low subsonic to supersonic during a typical NTP ground test sequence.&amp;nbsp;&amp;nbsp; Complex combustion processes will eventually need to be modeled in conjunction with down-stream effluent cooling systems such as water sprays and heat exchangers.&amp;nbsp; The simulation of water spray injection in a transient, time-accurate fashion will require implementation of robust numerical schemes which sufficiently capture the relevant physics of the water spray evaporation in the high-speed combusting flow.&amp;nbsp; In addition, the simulation of heat exchanger cooling systems will require fully coupling these multi-phase combustion simulations with a transient thermal analysis in a multi-physics analysis framework.&amp;nbsp; The successful demonstration of accurately and robustly coupling all these analysis into one simulation environment will be a new achievement for NASA.&amp;nbsp; &amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;&amp;nbsp;Specific objectives are:&lt;/p&gt;&lt;ol&gt;&lt;li&gt;Develop the fabrication process for producing fuzzy fiber with desired&amp;nbsp;carbon nanotube (CNT) length leveraging current collaboration with MIT through the National Space Technology Fellowship (NSTRF).&lt;/li&gt;&lt;li&gt;Evaluate fuzzy fiber composites with tailored CNT length&lt;/li&gt;&lt;li&gt;Develop&amp;nbsp;Boron Nitride Nanotube (BNNT) capabilities to enable incorporation of vertically aligned BNNTs into composite structures for multifunctional composite structures.&lt;/li&gt;&lt;li&gt;Model nanotube length and loading requirements to maximize transport properties through the resin rich inter-ply region of a composite and verify the model from composite data with different CNT lengths.&lt;/li&gt;&lt;/ol&gt;
&lt;p&gt;The proposed project technology need is evaluating the potential development to provide a capability that will produce high temperature hydrogen, in excess of 2500 Rankine (~2000&amp;deg;F) at a flowrate as high as 5 lb/sec to simulate a nuclear thermal propulsion (NTP) engine exhaust stream without use of a nuclear reactor as a heat source.&amp;nbsp; Preliminary investigations indicate that the two most feasible options relative to system development and test operations cost are as follows: (1) develop a specific purpose heat exchanger or (2) utilize an existing hot gas generator (GG) fixture presently stored in SSC&amp;rsquo;s component warehouse to heat ambient temperature gaseous hydrogen for test use.&amp;nbsp; &amp;nbsp;&lt;/p&gt;
&lt;p&gt;Initially, NASA GRC and GSFC will be studying the oxidation of molybdenum (highly oriented crystal and single crystal) and aluminum titanium nitride coatings and comparing to the performance of the sensor standard materials. In addition to chemical and thermal analysis, the surface conductivity and work function uniformity will be measured before and after exposure to selected levels of atomic oxygen to better understand oxide growth on conductive surfaces, and the effect of the resulting oxide on surface properties.&lt;/p&gt;
&lt;p&gt;The combined data acquisition and controls architecture is eliminating the need of the widely popular programmable logic control (PLCs).&amp;nbsp;&amp;nbsp; The system uses either Peripheral Component Interconnect (PCI) or PCI eXtension for Instrumentation (PXI) buffered controls cards for analog and digital outputs (ADO) in a chassis with a General Purpose Interface Bus (GPIB) interface.&amp;nbsp; The GPIB will connect to a commercially available off the shelf ADO. The control cards will output a timing sequence similar to that of a PLC (similar voltage and current levels) however the sequence data will be preloaded on a buffer prior to test.&amp;nbsp; The buffer will then be stepped through when the sequence begins.&amp;nbsp; The loop rate of a PLC can be surpassed by performing a buffered output so a finer resolution of controls&amp;rsquo; activities can be achieved. Additionally one piece of LabView&amp;trade; code will be required for this project to replace a mix of Wonder Ware&amp;reg;, LabView&amp;trade;, and Microsoft&amp;reg; Excel.&amp;nbsp;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The concept for this project is to take the hydrogen exhaust and inject it with a high mixture ratio of oxygen so the reaction produces steam.&amp;nbsp; In theory, in a radioactive state, any trace amounts of radioactive noble gases released by off-nominal NTP engine reactor performance would be contained in the steam.&amp;nbsp;&amp;nbsp; Water is injected to condense the potentially contaminated steam into water. This water and the Gaseous Oxygen (GO2) would then be captured in a containment area where the water and GO2 would be divided into separate containment tanks.&amp;nbsp;&amp;nbsp;&lt;/p&gt;&lt;p&gt;Additionally, the project will also look at mechanisms that may minimize the storage requirements, thereby, reducing hazard risk of these respective systems by using two methods for GO2 retention: (1) &amp;nbsp;compressed gas storage system and (2) liquid storage.&amp;nbsp; The compressed gas option would pump residual GO2 from the containment area at near ambient pressure to a 1000 psi Maximum Allowable Working Pressure (MAWP) storage vessel.&amp;nbsp; The liquid storage option flows GO2 from the containment area through a liquid nitrogen (LN2) heat exchanger to liquefy the GO2 and store the liquefied oxygen (LO2) in a vacuum/LN2 jacketed tank for storage, decay, and subsequent disposal.&lt;/p&gt;
&lt;p&gt;These issues are addressable by: increasing the thrust, power, and thrust-to-power ratio capability of EP systems; reducing the non-recurring engineering systems costs; and developing system architectures with performance characteristics that capture the broadest possible range of missions so that development &amp;amp; flight costs are amortized over multiple users.&amp;nbsp; We believe these objectives can be achieved by developing the Next Generation Electric Propulsion Thruster (NGEPT); a GRC-patented modular EP device based on a new arrangement of relatively mature and proven technologies with the potential to yield revolutionary capabilities&lt;/p&gt;
&lt;p&gt;AM offers the potential to be revolutionary for GRC hybrid disk concept as it: i) bypasses joining through direct deposition or &amp;ldquo;building&amp;rdquo; of the PX bore alloy on a SX rim and ii) circumvents interface heating issues that may cause microstructural degradation during welding. Our objective is to demonstrate the feasibility of the high payoff AM hydrid disk concept described through test specimens built up using electron beam melting (EBM).&lt;/p&gt;
&lt;p&gt;During chilldown of cryogenic fluid tanks and lines, the interface between&amp;nbsp;the liquid and vapor rapidly changes. Understanding these rapid&amp;nbsp;changes is key to understanding the thermal efficiencies of cryogenic fluid transfer in&amp;nbsp;microgravity. In order to demonstrate transfer line chilldown, you must&amp;nbsp;drain the storage tank. Draining a fluid storage tank in microgravity is a&amp;nbsp;complex task that can be solved with elegant surface tension features&amp;nbsp;inside the tank. Draining a tank during a transfer also presents&amp;nbsp;opportunities for secondary data gathering on&amp;nbsp;determining the fill level of the tank.&lt;/p&gt;&lt;p&gt;Kennedy Space Center (KSC) researchers have developed a&amp;nbsp;unique method to determine a tank fill level based on the tank&amp;rsquo;s response&amp;nbsp;to vibration input using PZT sensors/ actuators. This can also yield information on the health of&amp;nbsp;the tank. It has been demonstrated in microgravity using water for short durations produced by parabolic aircraft flights. This demonstration will increase its applicability to&amp;nbsp;cryogenic fluids and rapid draining of tanks.&lt;/p&gt;
&lt;p&gt;This technology will be a quantum advance in hemodynamic monitoring and will be applicable in numerous situations such as for immediate assessment and monitoring of patients in life-threatening emergencies, during environmental stressors, and in performance of hazardous occupational tasks. For NASA these benefits will apply to both flight and ground personnel. For the military this device can be used during actual combat to alert medical personnel when a service member is wounded and to monitor his/her condition even before help is provided thus lowering medical evaluation times. This can also be used to aid medical personnel allowing them to prioritize triage and evacuation in multiple casualty contingencies.&lt;/p&gt;
&lt;p&gt;The successful completion of this IRAD will deliver a fully functional instrument at TRL 6.&amp;nbsp; The key characteristics that we will demonstrate are simplicity, low cost, small size, and sufficient sensitivity to measure formaldehyde in the troposphere.&amp;nbsp; Our goal is to reduce the size and cost by a factor of three compared to our existing In Situ Airborne Formaldehyde (ISAF) instrument while sacrificing a factor of ten in sensitivity.&amp;nbsp; To maximize the value of this IRAD, we plan on testing the instrument on an aircraft.&amp;nbsp; Our target flight opportunity will be the Atlas jet operated at NASA Ames.&amp;nbsp; The Ames AJAX project (Atlas Jet Atmospheric eXperiment) is designed to validate OCO-2 with weekly flights. The same flights can be used for validating OMI on Aura and TEMPO (the recently selected Venture-1) by including measurements of formaldehyde, ozone, and CO.&lt;/p&gt;
&lt;p&gt;The University of Maryland is proposing to use a dielectric barrier discharge (DBD) as a means to dissociate N2O. DBD uses alternating high voltage differences between two electrodes to create strong electric fields. One or both of the electrodes is covered in a dielectric, and a gap in between allows gas to pass through. Nitrous Oxide sent through the gap between the electrodes has its free electrons accelerated by the large E-field, and in the process the electrons collide with N2O molecules.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Develop scalable graphene-based bolometer technology. Use low pressure chemical vapor deposition (LPCVD) technique to grow large area graphene. Develop a process to make saturable absorber with single layer, as well as multilayer graphene. Test and characterize graphene samples with in-house developed laser transmitter.&lt;/p&gt;
&lt;p&gt;Measurements of energetic neutral atoms (ENAs) are a new tool to improve our understanding of energy release and particle acceleration in solar eruptive events. &amp;nbsp;Due to limitations of past observations, even the most basic questions remain unanswered about the acceleration of solar energetic particles (SEPs) by shocks driven by coronal mass ejections (CMEs). &amp;nbsp;ENAs provide the only way to observe SEPs where they are accelerated. &amp;nbsp;The one observation of solar ENAs to date had low sensitivity, a high energy threshold, and no imaging information. The Solar Energetic Neutral-atom Imaging Coronagraph (SENIC) instrument concept is designed to observe ENAs from &amp;lt;~20 keV to a few hundred keV with a spectral resolution as good as 1 keV and image them from 2 R_sun to 40 R_sun with a spatial resolution of 0.1 R_sun. &amp;nbsp;Since ENAs cannot be imaged with focusing optics, this concept uses an indirect imaging technique similar to the one successfully used on RHESSI. &amp;nbsp;Thus, the SENIC instrument concept&amp;nbsp;combines large detector area, a low energy threshold, and high angular resolution.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;An ideal integrating bolometer can achieve breakthrough sensitivity in IR photon detection by removing practical barriers to extreme thermal isolation of the absorber.&amp;nbsp; The effort will be focused on design of the IIB, with the goal of having a layout ready.&amp;nbsp; During this period, we will also design parts needed for the test facility and start fabrication.&amp;nbsp; In the second quarter, the IIBs will be fabricated.&amp;nbsp; Also during this period, the test facility will be assembled and dry run testing completed.&amp;nbsp; In the third quarter, the IIB samples will be installed in the cryostat and tested. The final quarter will be dedicated to further debugging and testing the IIB samples, and completing the final report.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The magnetically-tuned TES (or MTES) takes characteristics that we have only recently come to understand are present and important in all state-of-the-art TES sensors and uses them in an interesting new combination.&amp;nbsp; Magnetic tuning simply changes the resistive transition of the TES sensor.&lt;/p&gt;&lt;p&gt;Our research program will answer the following questions in turn. Does an MTES reduce the relative sensitivity of the resistive transition in current? Does a MTES reduce the relative sensitivity of the resistive transition in current while maintaining a large relative sensitivity of the resistive transition in temperature? Does the MTES resistive transition depart from the weak-link theoretical model and if so in what ways?&lt;/p&gt;
&lt;p&gt;The sensor uses graphene based&amp;nbsp;devices to sense the surface potential of a graphene channel exposed to an analyte. When analyte molecules adsorb onto the graphene surface, they induce a local change in electrical resistance. This effect is very pronounced in graphene due to the high surface area; high electrical conductivity; and inherent low noise, which makes the changes in resistance detectable.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The Cleaning Lenses and Mirrored Surfaces with Electrons tasks include: Development of Fractal Wand Geometries; Vacuum Chamber testing for Fractal Wand Prototypes; and selection of best prototype.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Demonstrate angular resolution and sensitivity. Successful lab demonstration of ISS leak checking, using nitrogen, electron beam, and Lobster x-ray optic.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The project is to build a grazing incidence mirror for hard X-rays (E&amp;gt;20 keV) using a &amp;ldquo;scotch-tape&amp;rdquo; design, in which a thin plastic tape with a specific thickness profile and a multilayer reflective coating is tightly wound into a roll. Key challenges are (a) to find a suitably smooth tape substrate (this has been done), (b) to wind a large number of tape shells onto the smooth metal centerpiece without introducing and accumulating shape irregularities, and (c) to give the tape the variable thickness profile in order to achieve the desired optical figure. Our immediate goal is to demonstrate the idea feasibility by building a crude conical X-ray concentrator. If successful, we will aim at building and flying a mirror prototype on a balloon and then proposing for an Explorer mission or MOO. The ultimate goal is a telescope with 1 m^2 effective area at E=30 keV.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;We will work with the University of Maryland to design a single tank etching cell Etch porous silicon under different conditions and develop a method to characterize physical properties. Create fabrication processes that involve ion implantation and silicon-on-insulator wafers. Study the thermal conductivity&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;We will perform lab bench evaluations using Analog Devices Lyric Labs evaluation hardware as well as the&amp;nbsp;NASA/GSFC Radiation Effects and Analysis Group field-programmable gate array (FPGA)-based low-cost digital tester. &amp;nbsp;The evaluation hardware will be used to inform spaceflight hardware design decisions. &amp;nbsp;The Analog Devices Lyric Labs&amp;nbsp;probability processing technologies are fabricated in commonly-available commercial complementary metal oxide semiconductor (CMOS) processes. &amp;nbsp;Part of this project will also be to interface with other technology developers and scientists, both inside and outside of NASA/GSFC. &amp;nbsp;Analog probability processing is enough of a paradigm shift that the end-user applications may not be known a priori&amp;nbsp;and may either be based on insertion into pre-existing functions or development of new capabilities that could not be realized with existing hardware. &amp;nbsp;The probability processing hardware utilized for this project is the property of&amp;nbsp;Analog Devices Lyric Labs and was developed under a Defense Advanced Research Projects Agency (DARPA)&amp;nbsp;contract. &amp;nbsp;There is currently follow-on work at DARPA under the&amp;nbsp;Unconventional Processing of Signals for Intelligent Data Exploitation (UPSIDE) program.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Strained Layer Superlattice (SLS) detectors are a new class of detectors.&amp;nbsp;&amp;nbsp; In our FY12 IRAD &amp;ldquo;Strained Layer Superlattice Infrared Detector Array Characterization&amp;rdquo; we verified that these devices exhibit a dramatic increase in quantum efficiency (QE) over quantum well infrared photodetectors (QWIPs) and are approaching QE values comparable with mercury cadmium telluride and indium antimonide detectors.&amp;nbsp;&amp;nbsp; The anticipated advantages of SLS detector technology over existing IR detectors are: high sensitivity, band-gap tunable wavelength response (similar to QWIPs), warmer operating temperatures, array spectral uniformity (yet to be realized), high temporal stability, relatively low cost of manufacturing, scalability (to very large format arrays) and multiple vendor sources all contributing to higher performing scientific instruments.&amp;nbsp; Warmer and more stable focal planes lead to simpler instrument designs which result in higher reliability, longer mission lifetimes and reduced costs.&amp;nbsp;&amp;nbsp; In our FY12 IRAD we obtained a test SLS array and performed extensive tests to ascertain the veracity of researcher claims, as well as to assess the potential applications to NASA missions from a practical infusion standpoint.&amp;nbsp;&amp;nbsp; The most important result of that investigation was the verification of the (unexpected) very high QE.&amp;nbsp; However, along with the dramatic improvement in QE we measured much higher dark current and the array was quite non-uniform. Before we embark on an ambitious in-house program to design and fabricate SLS detectors it would be very valuable to build an IR camera system using the existing SLS array we currently have and perform some local field tests.&amp;nbsp; We believe that actual IR imaging of external environment scenery will prove most valuable.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Develop an Atom Interferometry-based gravity wave detector (vs Optical Interferometry). Characterize a high power laser. Use Goddard Space Flight Center Mission Design Lab to study a single flyer with boom&amp;nbsp; and developed cost estimate. Also funded a study at Stanford on Large Momentum Beam Splitters applications for Detection of Gravity Waves using Atom Interferometry.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Incorporate PF into GSFC&amp;rsquo;s Orbit Determination Toolbox (ODTBX). Augment PF with ODTBX&amp;rsquo; unique ability to partition error sources into subspaces for analysis. Utilize multi-core server to facilitate fast simulation of large particle populations.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;The effort&amp;#39;s objective is to realize broadband low-reflectance coatings. The two key technical challenges are the design of the precision engineered materials and their characterization.&lt;/p&gt;
&lt;p&gt;In this effort the following tasks will be addressed:&lt;/p&gt;&lt;p&gt;1) Develop reliable multilayer coatings for transition edge detectors, kinetic inductance films, and optical coatings.&lt;/p&gt;&lt;p&gt;2) Develop novel alloy films by depositing multiple materials simultaneously on test substrate wafers.&lt;/p&gt;&lt;p&gt;3) Characterization of electrical/optical properties and process repeatability.&lt;/p&gt;
&lt;p&gt;This study will employ a three phased approach: SAR image formation and calibration. DBSAR polarimetric and interferometric data analysis. PolInSAR algorithm development, validation and extension.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;If successful, the project will produce a prototype embedded hypervisor system that consists of a of a LEON3 processor board, a real time Core Flight Executive Virtual Machine, and a Science Data processing Virtual Machine. The system will be benchmarked against the standard embedded software running on the LEON3 in order to evaluate the performance impact of the embedded hypervisor. Detailed steps include: 1. Research and Purchase Hardware and Software 2. Define Software Development Environment 3. Setup Lab and Software Development Evironment 4. Establish Configuration Management System 5. Prototype Virtualization Environment 6. Integrate Hypervisor Software 7. Design/Document Virtual Machine Deployment and Communication Software 8. Develop Virtual Machine deployment and Communication Software 9. Develop/port Linux data processing software 10. Design and develop tests 11. Run tests 12. Document Results and plan follow on work.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;In this one year research project, we propose to do the following four tasks; (1) Design the silicon wafer X-ray mirror demo unit and develop a ray-tracing code to estimate the mirror performance. We will need to determine detailed parameters of the unit, such as size of the silicon wafer, their angle and pitch. (2) We have to find a wafer processed by the &amp;ldquo;right&amp;rdquo; method suitable for our application: appropriately flat and thin. We will procure the silicon wafers and measure the surface flatness using an optical interferometer. (3) Design a holding structure of the silicon wafer and place them in the K-B system configuration. The structure should be able to place the wafers in micron accuracy. If the machining accuracy doesn&amp;rsquo;t allow us to do this, we would need to develop a method to align the wafer. (4) Once we have the manufacturing drawing, we will need to identify the manufacturer and fabricate the designed housing. Then we will assemble the first demonstration unit, and measure its performance at the X-ray beamline. The X-ray test results will be compared with ray-tracing simulations and used for the further developments in the future.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;Here, we propose to develop a breadboard laser system that is capable of producing radiation in two UV wavelengths.&amp;nbsp; This Selectable Output Ultraviolet Laser (SOUL) system will utilize an existing solid-state laser infrastructure, as well as a series of nonlinear frequency conversion crystals to up-convert the fundamental laser wavelength to deep UV wavelengths.&amp;nbsp; A piezoelectric steering mechanism will enable the SOUL system to alternate between these UV output wavelengths at a rate of several hundred Hz.&amp;nbsp; This proposed system will also offer a &amp;ldquo;burst mode&amp;rdquo; of operation similar to the MOMA flight laser being developed by Laser Zentrum Hannover e.V.&amp;nbsp; The design proposed here will be more thermally robust and thus require shorter recovery times compared to the MOMA laser. &amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp;&amp;nbsp; Our effort will focus on the difficult task of designing, implementing and demonstrating a multi-staged UV-producing train of optics capable of switching between two different output wavelengths with variable output power. The success of the nonlinear portion of the total system lies primarily with the choices of materials, operating environments, laser wavefront and power control, and optical layout. The selectability of this prototype laser for upcoming mission opportunities will depend not only on the performance of the instrument, but in the compactness (mass and volume), robustness (operational conditions and survivability), and power requirements of the design.&lt;br /&gt;&amp;nbsp;&lt;/p&gt;
&lt;p&gt;NASA plans to build a lab bench operational system capable of tracking the position and orientation of small satellites as well as producing forces and torques on them. The goal is to be able to direct a satellite to move to various positions and orientations and then see how well it can accomplish this. The position resolution achieved is a major goal of the project.&lt;/p&gt;&lt;p&gt;We have previously demonstrated one directional forces and single torques to a satellite. We analyzed this and published a technique to extend it to more dimensions.&amp;nbsp;This project began on May 1st 2014. As results are developed more information will be provided to this site.&lt;/p&gt;
&lt;p&gt;ADN was developed by the Swedish Space Corporation (SSC), while HAN was developed by the Air Force Research Laboratory to be a propellant. Alliant Techsystems Inc (ATK) is predominantly evaluating ADN for future use, while Ball Aerospace was awarded a NASA Technology Demonstration Mission (TDM) to use HAN as a monopropellant to be launched from KSC/Cape Canaveral Air Force Station. Kennedy Space Center needs the technology in place prior to their arrival and needs to make recommendations as to their adoption if significant issues are found.&lt;/p&gt;&lt;p&gt;This is novel work that is necessary to safely support the evaluation and development of the next generation of &amp;ldquo;green&amp;rdquo; propellants.&amp;nbsp;The goal of this project is to develop leak detection and related technologies for the two new &amp;rdquo;green&amp;rdquo; monopropellants. This project is in its&amp;nbsp;early stage of development; information regarding this project will be updated in the near future.&lt;/p&gt;
&lt;p&gt;Using digital signal analysis tools, we will generate a repeatable output from the infrascope and compare it to the output of a traditional electrocardiogram, and real time blood pressure. &amp;nbsp;We will compare the signals to determine what known information is present in the output of the infrascope, what possible additional information may be present, and attempt to automate the analysis of the Infrascope signal.&lt;/p&gt;
Center Independent Research &amp; Developments: ARC IRAD Program
Center Independent Research &amp; Developments: DFRC IRAD Program
&lt;p&gt;Innovative projects are sought in the areas of basic research, fundamental research, applied research, development and systems and other concept formulation studies. Projects combining both science and technology are encouraged.&lt;/p&gt;
Center Independent Research &amp; Developments: LaRC IRAD Program
Center Independent Research &amp; Developments: MSFC IRAD Program
&lt;p&gt;Ecopoiesis is the concept of initiating life in a new place; more precisely, the creation of an ecosystem capable of supporting life. It is the concept of initiating &amp;ldquo;terraforming&amp;rdquo; using physical, chemical and biological means including the introduction of ecosystem-building pioneer organisms. The proposed concept will be subjected to extensive laboratory testing directed toward the ultimate emplacement of a test bed on (in) the surface of Mars to test (demonstrate) the activity of pioneer organisms selected on the basis of research on earth. To achieve this a device is proposed to penetrate and surround a sample of Martian regolith at a carefully selected site likely to experience transients of liquid water, completely seal itself to avoid planetary contamination, release carefully selected earth organisms (extremophiles like certain cyanobacteria), sense the presence or absence of a metabolic product (like O2), and report to a Mars-orbiting relay satellite. This will be the first major leap from laboratory studies into the implementation of experimental (as opposed to analytical) planetary in-situ research of greatest interest to planetary biology, ecopoiesis and terraforming.&lt;/p&gt;
&lt;p&gt;The diagram shows a conventional telescope pointed at an opaque disk along an axis to a distant target. Rather than block the view, the disk boosts the resolution of the system with no loss of collecting area. This architecture, dubbed the &amp;ldquo;Aragoscope&amp;rdquo; in honor of the scientist who first detected the diffracted waves, can be used to achieve the diffraction limit based on the size of the low cost disk, rather than the high cost telescope mirror. One can envision affordable telescopes that could provide 7cm resolution of the ground from geosynchronous orbit or images of the sky with one thousand times the resolution of the Hubble Space Telescope.&lt;/p&gt;
&lt;p&gt;The combination of novel photoelectrochemistry and 3-dimensional design allows tremendous mass saving, hardware complexity reduction, increases in deployment flexibility and removal efficiency. The high tortousity photocatalystic air processor design will achieve at least two orders of magnitude mass and power saving respectively, and enable feasibility of compact processors for spacecraft. The proposed work will demonstrate these drastic reduction in reactor mass, volume and power consumption in comparison to current technology with delivery of high-tortuosity device components allowed by 3D printing (potentially in space) at the end of the proposed work.&lt;/p&gt;
&lt;p&gt;WRANGLER will accomplish these functions by combining two innovative technologies that have been developed by TUI: the GRASP deployable net capture device, and the SpinCASTER tether deployer/winch mechanism. Successful testing of both technologies in a microgravity environment has established these technology components at mid-TRL maturity. The leverage offered by using a tether to extract angular momentum from a rotating space object enables a very small nanosatellite system to de-spin a very massive asteroid or large spacecraft. The WRANGLER system is suitable for an incremental development program that will validate the technology through an affordable test flight in which a nanosatellite launched on a rideshare opportunity would capture and de-spin the upper state used to launch it.&lt;/p&gt;
&lt;p&gt;The proposed instrument, which uses experimental techniques adapted from high energy physics, is a passive receiver of a naturally occurring signal generated by interactions of deep penetrating cosmic ray neutrinos. It could measure ice thickness directly,and at a significant savings to spacecraft resources. In addition to getting the global average ice thickness this instrument can beconfigured to make low resolution global maps of the ice shell. Such maps would be invaluable for understanding planetary features and finding the best places for future landers to explore. The approach and our findings so far are described in our paper in Icarus (Miller, et al., 2012, Icarus 220, 877&amp;ndash;888). The basic idea is to use radio receiver technology to detect cosmic ray neutrinos passing through the ice sheet and generating Cerenkov radio pulses (the Askaryan effect). The rate and directional distribution of the detected neutrino interactions will depend upon the thickness of the observed ice sheet. This technology has previously been demonstrated on Antarctic balloon flights by the ANITA neutrino project.&lt;/p&gt;&lt;p&gt;In this work we will extend the scope of our original investigation and explore in greater detail the possibility of making low resolution global maps of the ice shells - instead of simply getting a global average ice thickness. In addition, we will improve the fidelity of our initial simulation used to analyze the concept in several important areas in order to more precisely determine the final measurement capabilities of the instrument.&lt;/p&gt;
&lt;p&gt;This will study an exploration architecture combining remote survey with in situ sampling, with example missions to Europa and a Near Earth Object. In particular for this study, we will examine cold-stom gravimetry and ChipSat landers as enabling technologies to perform combined missions at Europa and asteroid targets. We will also investigate ChipSat landers as a technology for in situ sensing. These efforts will both mature cold-atom inertial sensing for use on small space platforms and mature ChipSats as a plentary landing platform.&lt;/p&gt;
The overall 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 (likely based on the presence of 90&#37; or more of the original API concentration).  This will be accomplished by designing and building a rugged, small, light weight, low power, easy to use analyzer with appropriate software, which can identify and quantify API and degradation products with little or no sample handling in 1 minute.  Feasibility will be demonstrated during Phase I by successfully measuring acetaminophen, azithromycin, epinephrine, lidocaine, and their degradation products at percent level concentrations.   

The overall goal of the Phase II program is to build a working prototype Drug Stability Analyzer that is suitable for space deployment (e.g. aboard the ISS) and capable of monitoring drug degradation.  The ability of the analyzer to nondestructively quantify the amount of the API and the degradation products, would also allow assessing drug potency at the time of use to ensure crewmember safety.  The Drug Stability Analyzer will be transitioned from a Technology Readiness Level 3 to a 7 (ground tested) from the beginning to the end of the program.
NxGEN Electronics Inc. (www.NxGENelectronics.com), teamed with its subcontractor Linear Signal, LLC (www.linearsignal.com) has successfully completed a Phase I contract for the 2011 NASA SBIR Phase I, Topic S1.02, subtopic, "Low Cost mm-wave Beamforming MMIC Receiver". These receivers, operating at 35.6 GHz and 94 GHz, are targeted for the space-borne, polarimetric, Doppler-capable radar for the NASA Aerosol/Cloud/Ecosystems (ACE) Mission, the successor to other cloud-study satellite missions such as CloudSat and EarthCare. The radar antenna itself will consist of 3.3 meter wide, 35.6 GHz and 94 GHz co-located linear antenna arrays that scan across the direction of orbit.     

The size of integrated receiver electronics behind each of these arrays does not extend beyond the antenna outline.  The critical physical specification for phased array antennas is the spacing between antenna elements. At 94 GHz, this implies an element spacing of 1.6 mm, while at 35.6 GHz the spacing is more generous at ~4.2 mm.   Then, for this particular configuration of 3.3 meter wide arrays the total number of receive elements is ~800 for the 35.6 GHz antenna and ~2048 for the 94 GHz antenna.  The  integrated receiver combines multiple array elements and their supporting circuitry into one integrated electronics package which results in an order of magnitude reduction in per channel cost and size.   Moreover, the decrease in package interconnect will also result in marked increase in reliability.
The other main goal of this project is to meet the functional requirements for W-band receiver.  The original requirements per the Phase I solicitation is as follows:
- Frequencies: 35.6, 94 GHz
- Input Channels: 16 
- Phase shifter: 360 degrees, 5 bits
- Serial phase update rate: &gt; 10 kHz for all channels
- Output IF: 1 channel,  &lt; 2 GHz
- Bandwidth: &gt;100 MHz
NASA is keen on advancing technologies for lightweight composite cryotanks for heavy lift vehicles for future NASA missions. Two primary challenges must be overcome to enable the use of composite tanks for these new classes of heavy launchers. One is to develop novel, microcrack-resistant, polymer matrix composite materials that will enable the manufacture of 5 to 10 meter diameter composite tanks, and the second is to develop out-of-autoclave manufacturing methods. In response, CTD is developing novel matrix materials based on toughened epoxy and benzoxazines to meet these goals and exceed the performance of current state of the art materials. The end goal of the Phase II program is to advance the material systems suitable for out-of-autoclave fabrication of very large cryotank (10 meter diameter) structures from TRL 3 to TRL 4. The proposed Phase II SBIR program will be a synergistic effort between analytical assessments of material performance requirements, material and process development, testing to assess material performance improvements and the ability to manufacture these novel materials into microcrack resistant composites laminates and cryotanks.
A small Mars (or other celestial body) ascent vehicle is unlikely to achieve the necessary propellant fraction required to achieve orbit.  Scaling down of liquid propulsion systems, as shown in the figure, is difficult.  In the 100-kg class of vehicles, liquid propellant vehicle designers should expect a propellant fraction of only 0.75.  In contrast, solid rocket motors (SRM) scale down much easier, so designers should expect a propellant fraction of at least 0.92.  To be practical, however, the SRM must operate in extreme low temperature environments, which is difficult for state of the art polybutadiene binders.  ASI proposes to develop a new, low temperature binder based upon siloxane.  Siloxane polymers have glass transition temperatures below 150K, making them ideal for use on Mars with little or no external heaters required.  A siloxane binder SRM-based MAV will easily achieve the propellant fraction needed for a sample return mission.
LOX/propylene
We propose to develop a soda-can-size, 500 g, 400 mW instrument for mounting on small lander or rover arms: the ultra-Compact Optical Spectrometer for Organic Mapping (uCOSOM) instrument. Two core technologies enable the proposed instrument: a narrow linewidth deep UV  laser and a new uncooled, resistive gate linear DUV CCD array detector with high quantum efficiency in the DUV with fast read rates and low read noise.
  The need for in situ micro-scale mapping for trace concentrations of organics on planetary surfaces is exemplified by requirements put forth the (July 09) Mid Range Rover; Science Analysis Group (MRR-SAG) and again in a 2010 Astrobiology paper by Pratt et al. uCOSOM fulfills similar organic needs on future in-situ missions with MER class rover/arm sizes or small landers to planetary bodies such as Mars, icy worlds (Titan, Europa, Enceladus), and small primitive bodies. uCOSOM provides a broad organic and inorganic compound measurement capability without the need for sample handling or reagents. 
   It will excite sub-ppb levels of organic compounds on rocks, soil, or other surfaces in the deep UV below 250 nm and simultaneously measure Raman scattering in the 250 nm to 260 nm region (1000 to 4000 cm-1) and native fluorescence in the 260 nm to 700 nm region at a working distance of several cm, with long depth of focus, and with the ability to map areas up to 1 by 1 cm in size with 100 micrometer spatial resolution. 
   The pulsed source enables solar blind gated Raman and fluorescence spectral measurements but also fluorescence and phosphorescence decay measurements to provide orthogonal information about target composition.
  The instrument can also provide spectral reflectance of targets from 250 nm to 700 nm together with Raman and fluorescence data, using solar illumination, and enable solar and stellar irradiance and sky background measurements.
During our Phase I STTR effort, Balcones Technologies, LLC (BT) and The University of Texas at Austin Center for Electromechanics (CEM) successfully achieved all Phase I objectives and developed concept designs for controlled Canfield Joint Systems (CJS) for numerous applications that currently employ two-axis gimbal systems, including flywheel energy storage systems, integrated flywheel energy storage and attitude control systems, controlled moment gyros (CMG), and pointing systems for satellite-to-earth and satellite-to-satellite space optical communications (SOC).   While all applications offered advantages for CJS compared to gimbal alternatives, a major result from our Phase I commercialization study was that the highest payoff Phase II demonstration for NASA and other commercial applications would focus on a CJS simultaneously sized for two applications:  small satellite CMG and small satellite optical communications.  Since the SOC application is more demanding and this emerging application offers more terrestrial and space applications, this application will serve as our demonstration target for Phase II.  Additionally, since the SOC application has demanding vibration isolation requirements (especially for deep space communications) and since the BT-CEM team has very advanced expertise in this area, our Phase II demonstration will include development and integration of a vibration isolation system (VIS). Some key CJS-SOC features include:  More than 30&#37; improvement in pointing accuracy and precision compared to 2 axis gimbal systems; Integrated vibration isolation system to meet deep space optical communication systems; Also sized for small CMG application; Wide field of regard; Scalable to large flywheel applications; Maximum use of COTS components; Exploits team core capabilities in vibration isolation systems and high precision, high accuracy point systems.
NASA Glenn Research Center (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 single-facesheet Variable Conductance Heat Pipe (VCHP) radiator, operating near 450K, to support the Technology Demonstration Unit (TDU) for surface power and 100kW-class electric vehicles.  ACT will utilize the experience gained during previous Phase I and Phase II VCHP radiator programs for NASA GRC to increase the specific power of the radiator and reduce the overall cost.  A trade study will be conducted to compare single-facesheet and dual-facesheet VCHP radiator designs and the ability to directly bond a GFRC facesheet to a titanium heat pipe will be demonstrated.  A complete preliminary design for a single-facesheet VCHP radiator for the non-nuclear system will be developed at the end of the Phase I program.
Converting in-situ resources into propellants, energy storage reactants, or other useful products at the site of exploration, known as in-situ resource utilization (ISRU), instead of transporting these supplies from Earth can significantly reduce the cost and risk of human exploration while at the same time enabling new mission concepts and long term exploration sustainability. NASA needs innovative gasification reactors to convert trash into useful intermediate products such as carbon dioxide and water, which can ultimately be used to make methane and oxygen for propulsion and energy generation applications.  Unfortunately, partial oxidation reactors and incinerators that might be used to reduce trash to useful products operate at high temperatures and also create ash, tar and other undesirable by-products.  TDA Research has developed a low temperature (&lt; 135 degrees C) ozone oxidation process that efficiently and cleanly converts trash into carbon dioxide and water.  These intermediate products can then be delivered to a Sabatier reactor for the production of methane and oxygen.  However, our reactor was designed for use on the moon or Mars whereas future spacecraft will need systems able to function in zero-g and micro-g environments.  Therefore, TDA proposes to develop a trash gasification reactor that uses our ozone oxidation process and will work in the absence of gravity.  In this project we will conduct the analysis and experiments to design the reactor.
NASA plans to use intelligent planetary rovers to improve the productivity and safety of human explorers. A key challenge in using robots for human exploration is orienting remote personnel about robot operations, as latency and communication constraints make eyes-on monitoring impractical. Summary measures are needed to identify what progress the robot has made and, when progress is impeded, to indicate what went wrong. Trending measures also are needed that determine how well robotic assets are being utilized and identify opportunities to improve robot productivity. TRACLabs and Brigham Young University propose to develop software for anytime summarization to orient personnel quickly about the performance of planetary robots operating remotely, when data are limited, interrupted, or delayed. Thus an anytime summary must support personnel in understanding the operational situation without relying on vigilance monitoring. 

We successfully completed all Phase I objectives. We designed an approach for developing an anytime summarization web application. We identified candidate use cases to support Intelligent Robotics Group (IRG) tests. We designed and prototyped algorithms to summarize robot performance. We designed a web application with a graphical narrative interface (GNI) for exploring anytime summaries for different uses and perspectives. This web application integrates these interface clients with a performance data server and with the IRG Exploration Ground Data System (xGDS). In Phase II we will implement this Phase I design as a web application for anytime summarization. This software will compute and present information about robot performance including key performance indicators, significant events affecting performance, and expected performance under different operational conditions. It will build a new performance database for use by web clients, such as the GNI. This web application will be evaluated for use with NASA robots as part of the IRG xGDS.
Sentix and Brigham Young University propose the research and development of embedded payload intelligence for inflight optimization of surveillance, reconnaissance, and scientific missions. The current proposal leverages a substantial body of scientific and experimental knowledge derived from the Tactical Seeability&amp;#153; System developed by Sentix' staff and BYU researchers to provide fully automated, optimal optical sensing over rugged 3D terrain. Discriminating features of our target capability include the following: 1.) A modular, sensor and platform agnostic framework for preflight and inflight modeling and optimization of performance in data acquisition missions, 2.) Mission impact modeling relating sensor payload configuration (states) to "sensing value" for the mission. 3.) An optimizer for the configuration of the aircraft and payload. 4.) An online estimator of current mission impact arising from the actual, achieved sensing, which can be used to inform a re-planning process for corrections to flight trajectories and payload configuration.
The evolution of the National Airspace System via the Next Generation Air Transportation System program depends on enabling new operational concepts to increase efficiency. Decreasing the spacing between aircraft on takeoff and landing would increase the throughput of airports.  On-board sensing capability for wake vortices could allow aircraft to operate with reduced spacings. Wake vortices can be detected by a lidar located on the aircraft, but such a system needs to be small, lightweight, rugged, and require minimal maintenance. The Phase I program showed the feasibility of an intrinsically low-cost, coherent lidar that would be suitable for deployment on commercial airliners for axial wake vortex detection. The Low-Cost Lidar Test Bed was used to demonstrate measurement of aerosol returns. The program also assessed the feasibility of using the lidar for remote detection of clear air turbulence and volcanic ash clouds.  The program developed a conceptual design for a prototype system that would be fabricated and ground tested in the Phase II program.  The Phase II program will design and fabricate an engineering prototype compact coherent Doppler lidar and demonstrate it by measuring ambient wind fields at nearby venues.
The MAI-400SS Space Sextant is a precision attitude determination and control system for CubeSats and Nanosats.  The MAI-400SS enables future CubeSat missions with precision fine pointing (0.1deg) and dynamic slewing as will be required for imaging operations of ground targets.  A flight control computer, 2 Star Trackers, 3 reaction wheels and 3 electromagnets are incorporated in a 4" x 4" x 3" (3/4U) CubeSat sized module.   The system is based on the highly successful MAI-400 miniADACS and extends its performance capability to the 0.1deg range by incorporation of 2 star cameras and attitude determination software.  Phase I developed the software algorithms and prototyped the star cameras and electronics.  Phase II consists of a development program culminating with a system at TRL 7.  The technology is significant because it extends the capability of current low cost Nanosats to tactical imaging and other missions requiring fine pointing and dynamic retargeting, missions hitherto restricted to large and expensive spacecraft.  The MAI-400SS will facilitate rapid development of low cost satellites by providing a turnkey system which would be capable of determining and controlling spacecraft attitude automatically; simplifying operations and enabling rapid mission development as envisioned by ORS.
Exploration crews for long duration space flights have continually expressed a need for more chances to learn to work together as a team prior to flight. Together with the need to retain proficiency with limited places to practice, we propose to build a virtual environment that is both website-accessible and scientifically-rooted team. The resulting training system will enable crews to maintain a high state of cognitive readiness for team-based skills, such as coordinated fire suppression.
Need:  NASA faces challenges in imaging and characterizing faint astrophysical objects within the glare of brighter stellar sources. Achieving a very low background requires control of both scattered and diffracted light. 
Significance of the Innovation: Aligned arrays of carbon nanotubes have recently been recognized as having world-leading optical absorption, far above competing state of the art materials.   The nanotube array's diffuse reflectance (10-7) was demonstrated at two orders of magnitude lower than commercially available low reflectance carbons (10-5).  The integrated total reflectance 0.045&#37;, bested the field of competing materials, which are typically &gt;1&#37; at optical wavelengths. However, these arrays were produced on silicon, so they have limited utility for aerospace applications. NanoLab identified the potential to grow these arrays on flexible substrates, and proposed a Phase I effort to explore their properties.
The goal of the proposed effort is to demonstrate feasibility of using selective laser melting (SLM, an emerging manufacturing technique) to manufacture a subscale combustion chamber liner that features an advanced regenerative cooling technique that combines high performance with low pressure drop.  SLM enables the ability to "print" the advanced regenerative liner in mere hours, despite the liner's inherent flow passage complexity.  This reduction in manufacturing lead time, combined with the fact that SLM manufacturing costs are driven almost exclusively by the amount of raw powder used during fabrication, results in a substantial cost reduction for future regeneratively-cooled rocket engines.  Considering that the proposed regenerative cooling approach features heat transfer coefficients 3-10 times higher and pressure drops 2-10 times lower than traditional axial channels, the proposed effort demonstrate one of the highest performing, lowest cost combustion chambers in the world.
Research suggests that: (1) orbital debris has reached the point that, even with no future launches, collisions among large-body debris will lead to unstable growth in debris, and (2) removing as few as five large objects each year can stabilize debris growth. For large-body active debris removal (LB-ADR), new technologies are required to safely capture the target debris. The interactions of these complex electromechanical systems (eg. imaging systems, robotic arms and grippers) and controllers pose challenges best addressed by hardware-in-the-loop (HWIL) testing. Given the risks inherent in non-cooperative spacecraft proximity operations and the firm requirement that ADR missions do not themselves produce additional debris, realistic ground-based testing is required for risk reduction.

Our approach to HWIL contains two major advancements: (1) novel robotic technologies that overcome the limitations of existing test facilities, and (2) carefully designed spacecraft models capable of thoroughly evaluating every aspect of a capture system. The LASR Lab was built around HOMER, an omnidirectional robot designed and built specifically to emulate the 6-DOF relative-motion trajectories of spacecraft. The Phase I effort validated HOMER's capabilities and reduced to hardware the Dynamic Payload Pendulum (DPP), an actively controlled pendulum that provides the equivalent of a 5-DOF air-bearing. Together, they permit large-scale motion with accurate contact dynamics. Having identified rocket boosters as ideal LB-ADR targets, we investigated the model features necessary for realistic testing of grappling and sensing systems and for accurate dynamic response on the DPP. Leveraging the developments of Phase I and concurrent work on autonomous, vision-based navigation systems at the LASR Lab, we propose to simultaneously advance the TRL of the ground-test facility and the nav systems by performing an end-to-end simulation of an approach and capture of multiple rocket bodies.
A major component of airframe noise for commercial transport aircraft is the deployed landing gear.  The noise from the gear originates due to complex, unsteady bluff body flow separation from gear components and the subsequent multiple interactions of unsteady wakes with downstream undercarriage elements.  The object of this SBIR effort is to develop and advance a novel 'plasma fairing' technology for quieting landing gear noise.  The concept deals with the use of single dielectric barrier discharge (SDBD) plasma actuators to reduce noise associated with bluff body separation around the gear.  SDBD plasma actuators will be employed either in the form of spanwise-orientated actuators or plasma streamwise vortex generators (PSVGs) to suppress surface pressure fluctuations, and consequently flow-induced noise, on a representative landing gear model.  Our Phase I effort will involve a combination of numerical and experimental studies to be conducted at Innovative Technology Applications Company, LLC and the University of Notre Dame, respectively, in order to advance the design and optimization of 'plasma fairings' from a simple geometry (tandem circular cylinder) to a more complex/realistic landing gear geometry (e.g., the Gulfstream G550 nose gear).  A combination of DES numerical simulations and wind tunnel experiments is expected to provide a clear demonstration of the plasma fairing performance for noise reduction, while providing a clear path forward for Phase II.
Paragon Space Development Corporation&amp;#174; (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). Utilizing 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 robust design solution 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 I effort includes laboratory tests to determine the feasibility of employing the all-ceramic SOFC design as both an electrolyzer cell and an ESR to improve single pass utilization of the feed stock and deter carbon deposition. 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 while in transit.
A spacecraft thermal control system must keep the vehicle, avionics and atmosphere (if crewed) within a defined temperature range. Since water is non-toxic and good for heat transport, it is typically used as the coolant that circulates within the crew cabin boundary. This loop then interfaces with another low freeze point fluid, such as ammonia, for transport of heat to a radiator where the temperatures can be considerably below the freezing point of water.  The volumetric expansion during freeze usually prevents its use in external systems since freezing will damage the components. Yet, if the system can accommodate the forces generated by freezing, then selectively allowing parts of a heat exchanger to freeze can be used to passively increase the turn-down of the heat rejection from radiators.  TDA Research, Inc. has been developing freezable water/ice phase change heat exchangers for several years that offer several advantages: they can eliminate the need for a separate heavy Freon or ammonia loop; use the buildup of ice to regulate the rate of heat transfer, and the endotherm of melting ice can absorb peak loads from the spacecraft to reduce the size and mass of the radiator.  Therefore, TDA Research and the University of Colorado set out to demonstrate a lightweight and freeze tolerant water/ice heat exchanger to passively regulate the heat rejection rate from the water coolant loop of a manned spacecraft to its heat sink systems. The heat exchanger has no actively moving parts and is thus extremely reliable. In Phase I, we designed and built a self-regulating freezable heat exchanger that we put through 191 freeze/thaw cycles without damage and it has the capability to transfer the loads expected in crewed spacecraft.  In Phase II, we will design, build and test a large-scale freeze tolerant water/ice heat exchanger that forms the heart of a thermal control system that we will deliver to NASA.
The proposed innovation is an automated UAS mission planning system that will rapidly identify emergency (contingency) landing sites, manage contingency routing, and dynamically evaluate route changes for viability and safe operations in the NAS.  Specifically, RAMPS will feature a pre-flight contingency planning capability that rapidly determines viable alternate/emergency landing sites based on a UAS's contingency ability and safe routing restrictions.  RAMPS will include an in-flight dynamic contingency management capability that assesses ATC-requested re-routing and threats posed by weather to determine feasibility of modifications to the UAS flight trajectory.  RAMPS can operate as a recommender system, providing operators with a narrow list of best options to help facilitate timely decision-making.  RAMPS capabilities will provide UAS Operators with valuable time saving examination of a proposed route and possible contingency operations along that route &amp;#150; automating what has been an exceptionally tedious and lengthy manual process during mission planning.  The in-flight component of RAMPS will provide the UAS operator with a dynamic mission evaluation tool &amp;#150; exceptionally important when a reconnaissance and surveillance mission is introduced into the routing planning process.
Future flight vehicles may comprise complex flight surfaces requiring coordinated in-situ sensing and actuation.  Inspired by the complexity of the flight surfaces on the wings and tail of a bird, it is argued that increasing the number of interdependent flight surfaces from just a few, as is normal in an airplane, to many, as in the feathers of a bird, can significantly enlarge the flight envelope.  To enable elements of an eco-inspired Dynamic Servo-Elastic (DSE) flight control system, IFOS proposes a multiple functionality-sensing element analogous to a feather, consisting of a very thin (gauge 18 or 20) tube with strain sensors and algorithms for deducing the shape of the "feather" by measuring strain at multiple points.  It is envisaged that the "feather" will act as a unit of sensing and/or actuation for establishing shape, position, static and dynamic loads on flight surfaces and in critical parts.  IFOS proposes to develop advanced sensing hardware and software control algorithms to demonstrate the proposed DSE flight control concept.  The hardware development involves an array of optical fiber based sensorized needle tubes for attachment to key parts for dynamic flight surface measurement.
This joint STTR research effort between HJ Science &amp; Technology and the University of Texas at San Antonio seeks to establish a highly integrated mobile "lab-on-a-chip" platform &amp;#150; next generation "lab-on-a-robot" (LOAR) - capable of in-situ, high throughput, and simultaneous identification and characterization of universal classes of ions, molecules, and biomolecules for NASA in-situ planetary compositional analysis, and planetary and small body surface chemistry studies. The technology combines programmable microfluidic on-chip automation of sample processing, microchip capillary electrophoresis with contactless conductivity and optical detections, and integration with the next generation LOAR mobile platform in a miniaturized format.  Such a mobile platform for the miniaturized instrument will lay the groundwork for future NASA in situ robotic missions.  In Phase I, we have established the technical feasibility by demonstrating all key functionalities.  This includes the separation and detection of selective ions that are relevant to the aqueous chemistry and reactivity of the Martian surface material with a novel microfab-less microfluidic device and the demonstration of the on-chip automated sample processing capability with a novel microvalve platform.  The Phase II effort will include expanding and enhancing the performance capability of the novel microfab-less microfluidic device, integrating the on-chip automation technology to the microfluidic device and demonstrate the capability of the programmable on-chip automation of sample processing, and the design, construction, and test of a next generation LOAR prototype.
The volume of data that NASA collects has grown dramatically as new missions come on line with hundreds of terabytes of data of all types. Often, this involves semi-autonomous exploration to collect a representative set of different scenes and objects so that research scientists and mission controllers can decide what regions are of particular interest and should be explored further. The lack of bandwidth to transmit all this data back from deep space has prompted the need to determine what data is relevant, important, and interesting enough to be sent back immediately. A common understanding among potential consumers (including the general public) of what signifies as an image or sensor reading of value is needed. To make these decisions quickly, the data needs to be presented intuitively using a common semantic vocabulary that describes interesting or anomalous features or events (e.g., composition of a certain mineral above some threshold, visual evidence of terrain features created by moving water, or a volcanic eruption in real-time during an orbital pass) so that opportunities for further inspection and analysis are not lost to long transmission times. We propose a framework for onboard intelligent data understanding algorithms to mitigate this opportunity risk and improve collection efficiency and effectiveness by summarizing the data and enabling the download of a subset containing the most valuable portions called Discovery of Interesting Patterns and Semantic Analysis in Remote Space (DIPSARS). DIPSARS is a framework for semantically characterizing, detecting, and fusing interesting and anomalous 1D sensor measurements and 2D imagery onboard remote spacecraft and planetary rovers to conserve transmission bandwidth. We do this by summarizing data events so that mission controllers and research scientists can analyze representative feature data and provide instructive feedback to seize emergent opportunities for data collection.
NASA Glenn is examining small fission reactors for future space transportation and surface power applications.  The reactors would have an 8 to 15 year design life and should be available for a 2020 launch to support future NASA science missions.  Both 1 kWe thermoelectric and 3 kWe Stirling systems have been examined.  Heat pipes are being examined to transfer the thermal energy from the reactor to the electric conversion systems.  There are three types of wicks that can carry this power over the distance; grooved, sintered arterial and self-venting arterial.  Arterial heat pipes are the default design for spacecraft nuclear reactors; however, de-priming of the artery due to radiation is a serious potential problem.  Grooved and self-venting arterial heat pipes are less susceptible to de-priming since the liquid in the grooves is open to the vapor space and the self-venting arterial heat pipe has venting pores in the evaporator to allow trapped vapor to escape.  ACT's innovation was to examine the tradeoffs between the three heat pipe wicks and determine an optimum wick design that is suitable for fission reactor applications.  The Phase I project was successful in demonstrating that all three types of wicks can transport the necessary power.
DSS proposes to systematically mature, mitigate risk for; and perform hardware-based ground validations / demonstrations of a low-cost, high technology payoff, ISS-based flight experiment that will allow key relevant space-flight environmental validation of our innovative Roll-Out Solar Array (ROSA) technology.  The ROSA flex-blanket solar array technology provides game-changing affordability and performance, and delivers a performance paradigm shift in terms of: significantly lower cost, greater specific power, more compact stowage volume, higher structural performance, less complexity, and  more modularity / scalability than state-of-the-art solar arrays.  A critical aspect of readying the enabling ROSA technology for infusion into potential end-user applications is to increase the TRL to 7+ via test / analytical validation of hardware in a relevant spaceflight environment for: Deployment, Deployed Dynamics and Photovoltaic Power Production. The ISS provides a ready and cost-effective relevant space environment (zero-G, vacuum and solar illumination/thermal) test-bed for the validation of these key technology areas via the straightforward flight experiment proposed. The Phase 2 effort is intended to lead to the definition of a comprehensive and test-validated ISS-based ROSA experiment design and operations plan that will facilitate / accelerate an ISS experiment manifest / review / approval process to significantly shorten the time to flight. The program includes: comprehensive risk mitigation for the flight experiment that includes hardware-based testing / ground simulation of experiment operations (including ISS structure and robotic arm interfaces) with functional and flight-like experiment hardware and generation of documentation to facilitate ISS flight experiment board requirements, integration, operations and safety reviews.
Conceptual design tools for rotorcraft are used to size vehicles for intended flight operations, as well as reveal trends on the relative benefits certain configuration choices have on the resulting aircraft performance.  This information is useful for indicating potentially valuable areas for further technology development that would enhance rotorcraft capabilities.  These tools must therefore contain models of subcomponents that are sufficiently accurate to capture current rotorcraft technology performance metrics, but with suitably simplified models to permit rapid re-calculation as befits an optimization scheme.  If subcomponent models are insufficient or lacking, they may be built up using simplified models or empirical relations derived from more detailed, comprehensive codes.  This approach permits the rapid analysis turn-around required of a sizing program while still capturing the trending information available from the more detailed analysis tool.  In the proposed Phase I program, CDI plans to use its full-span free wake analysis tool, the CHARM Module, to investigate approaches for adding this analysis capability to rotorcraft conceptual design software, specifically to extend options for aerodynamic performance modeling, computation of handling qualities metrics, and assessment of acoustic emissions.  NASA has recently made available a sizing code named NDARC (for NASA Design and Analysis of Rotorcraft), which has a modular framework to permit the inclusion of different or additional subcomponent models in its operation as proposed here for development.  Phase I will investigate the addition of these features in that conceptual design code as a convenient demonstration of the viability of this approach.
Cryogenic fluid management (CFM) is a critical technical area that is needed for the successful development for future space exploration.  A key challenge is the storability of LH2, LCH4, and LOX propellants for long durations.  The storage tanks must be well insulated to prevent over pressurization and venting, which lead to unacceptable propellant losses for long-duration missions to Mars and beyond. Aspen Aerogels validated the key process step for a next generation aerogel manufacturing technology to enable the fabrication of thin, low density aerogel materials.  Multi-Layer Aerogel Insulation (MLAI) system prototypes were prepared using sheets of these aerogel materials that have superior thermal performance exceeding that of the current state of the art insulation for space application, MLI, across the vacuum range tested (0.01 &amp;#150; 100 millitorr).  The exceptional properties of this system include a new breakthrough in high vacuum cryogenic thermal insulation, providing a durable material with excellent thermal performance at a reduced cost when compared to longstanding state-of-the-art MLI systems.  During the Phase II Program, further refinement and qualification/system-level testing of the MLAI system will be performed for use in cryogenic storage applications.
&lt;p&gt;Funds are distributed to each NASA Center to support emerging technologies and creative initiatives that leverage Center talent and capabilities. NASA scientists and engineers will lead projects and partnerships among Centers and with other agencies, research laboratories, academia and private industry are encouraged.&lt;/p&gt;
This proposal introduces an innovative sensor to advance ground collision avoidance for UAS platforms by providing real-time height maps for hazard anomaly detection. This sensor will also  provide enhanced vision to overcome reduced visibility in fog, drizzle and light rain and the detection of hazards/obstacles on runways for landing and takeoff applications. 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  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 II 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 II, a technology readiness level of 5 will be achieved.
A significant challenge in scaling micro-propulsion devices up to 100s of Watts as well as scaling macro devices down to sub-kiloWatt level is the lack of a compatible neutralizer technology in the meso scale.  Sub-kiloWatt EP systems require cathode technology that can produce sufficient current while consuming little or no gas or power.  The most promising technology for meso-scale neutralizers is field emission.  In field emission, electrons are extracted directly from a cold bulk solid material by an intense applied electric field at the solid-vacuum interface with no gas flow and no heating required.  While many methods have been proposed to incorporate field-emission neutralizers in EP systems, the inherent fragility of the technology &amp;#150; specifically the reliance on solid structures with nanometer-radius tips &amp;#150; ensures that device failure due to tip degradation will be a near certainty for any application depending on field emission cathodes. The goal of research proposed here is to develop arrays of field-emission neutralizers for use in sub-1-kW EP that eliminate tip degradation not through attempts to minimize tip wear, but instead by incorporating self-assembling nanostructures that can repeatedly re-generate damaged emitter tips in space and fully restore the functionality of a damaged or degraded device.
Hybrid-Electric distributed propulsion (HEDP) is becoming widely accepted and new tools will be required for future development.  This Phase I SBIR proposal creates a turbo-electric, hybrid electric propulsion system sizing and weight synthesis tool specifically designed for use in an MDAO framework.  It will offer significant flexibility regarding placement of the propulsive devices for top-level hybrid design, including over-wing, under-wing, split-wing, fuselage pylon-mounted, and other configurations.  The user will supply power required, fan speed, fan torque, TOGW estimation, desired power split between engines and batteries, and selection for propulsion system locations.  Sizing and weight analysis for electric motors, generators, speed controllers, gearboxes, cables, transformers, batteries, and cooling systems will be considered including structural considerations for heavily modified aircraft components for each system.  The outputs will be hybrid electric propulsion system weight, sizes for the sub-system components, and revised HEDP specific TOGW calculation.  The overall goal of this proposal is to provide a tool within a framework for top-level and conceptual hybrid electric propulsion studies.  Additionally, the fidelity of the current NASA models is based on empirical-data and extrapolations.  This proposed tool will employ physic-based models with empirical corrections, when needed.  A Phase II and future commercialization plan have been identified.
The proposed research pursues a path for reducing structural weight, increasing structural performance, and reducing fabrication cost while also minimizing maintainability.  The approach, which is a based on selective reinforcement, is a change in the basic design philosophy and will result in the development of a hybrid material form.  The selective reinforcement approach allows the structural design requirements to define the material form.  This is the reverse of the typical development flow path used for building structures.  This backward path results in more efficient material forms that are of greater value to structural engineers.  Specifically, the proposed effort will combine a metal matrix composite (MMC) prepreg tape feedstock with an advanced fiber placement process.  The combination of these technologies will lead to enhanced metallic structures through selective reinforcement (SR), which consists of adding a high-performance material to structures to achieve local stiffening and strengthening.
Systima will develop an innovative light weight self-pressurizing pump (SPP) technology to provide a constant-pressure supply of monopropellant to a spacecraft or tactical propulsion system. The SPP does not require a helium tank and higher operating pressure have a negligible impact on the system mass.  Since the SPP has a lower weight than comparable propellant pressurization systems, it provides an opportunity for reducing launch costs, increasing spacecraft or tactical system payload capacity and significantly enhancing delta velocity/?V.  This technology can be used with hydrazine, HAN-based, or ADN-based propellants as there are no known limitations on the monopropellant that can be used in the system.  The self-pressurizing lightweight pump for advanced monopropellants offers significant advantages in applications where a large ?V is required, such as large spacecraft or in applications where high-pressure is needed, such as liquid ACS or DACS thrusters.   The Phase I and Phase II SBIR will focus on development of the system for operation with the HAN-based monopropellant AF-M315E.
Fault to Failure Progression (FFP) signature modeling and processing is a new method for applying condition-based signal data to detect degradation, to identify fault modes, and to produce system estimates for State of Health (SoH) and Remaining Useful Life (RUL). The base technology has been applied for prognostic purposes for various government-sponsored programs, but FFP signature modeling and processing has not been applied for the area of Fault Management, nor does it include such features as fault dictionaries, lookup tables, and management algorithms. The technology includes Ridgetop-designed and developed algorithms to do the following: (1) perform Kalman Filtering to reduce noise; (2) transform sensor signal data to reveal underlying (hidden) FFP signatures; (3) normalize units-of-measure dependent signal data into dimensionless FFP signatures to facilitate re-use and reduce the time to characterize and define new FFP signatures; (4) define and use model definitions that reduce memory requirements and support fast and accurate processing and calculations; (5) two forms of trajectory curve characterization, both straight-line and curvilinear; (6) a fast yet accurate, graphics-based mathematical routine to adapt an FFP model to received data; (7) amplitude and time updates similar to Extended Kalman Filtering to estimate how long it will take an adapted FFP model to reach a defined failure threshold; and (8) produce SoH and RUL estimates that rapidly converge to the estimated time-to-failure (TTF) solution. The FFP signature modeling and processing will include additional innovation to support FM to minimize application-specific programming, those include algorithms to simplify fault identification and isolation.
We propose to develop and commercialize a new class of aperiodic multilayer coating that is designed to provide high normal-incidence reflectance over a wide spectral band-pass in the extreme ultraviolet (EUV) region, specifically from 9 to 14 nm. A broad-band reflective coating working at these wavelengths will enable, for the first time, the construction of high-resolution imaging spectrometers for solar physics utilizing diffraction gratings operating near normal incidence in this range, akin to previous instruments utilizing normal-incidence optics working at longer EUV wavelengths (i.e., lambda&gt;17 nm) such as the Hinode/EIS satellite instrument and the EUNIS sounding rocket instrument. The development of high-resolution, normal-incidence grating spectrometers operating in the 9&amp;#150;14 nm range will in turn allow for detailed investigations of important solar emission lines, such as those from Fe XVIII &amp;#150; XXIII, that can provide unique diagnostics of high temperature plasma associated with solar flares and active regions. The successful development of efficient, broad-band EUV multilayers for the 9&amp;#150;14 nm region as we propose will thus enable future flights of the EUNIS rocket to target this band, and will also enable the development of high resolution spectrometers that can meet the science requirements of future NASA satellite missions, such as RAM, Solar-C and others that are currently being contemplated.