This proposal responds to the request for pumps for pressure-fed
propulsion systems with a pistonless pump wherein a pressurant act
directly on the propellant(s) in a set of  pump chambers.  The pump
system will work for both in-space and spacecraft descent and ascent
systems, and it is applicable to nanosat launch vehicle (NLV)
technologies as well. When integrated into a full propulsion system,
this pump will increase payload mass fraction, reliability, safety, and
operating flexibility.  The same pump can be used for the main engine,
attitude control thrusters, and fuel transfer, since the pump provides
variable pressure at variable flow without using extra consumables. The
pistonless design avoids sliding seals, which can cause problems for
piston pumps. No precision components are needed, and all active
components can be redundant and/or contamination-tolerant.  For space
transportation or launch vehicle systems with liquid/supercritical
helium and/or multi-stage autogenous pressurization,  &amp;quot;system
Isp&amp;quot; including pressurant and tank mass can be intermediate between
gas-generator and staged combustion turbopump systems, but at much lower
cost and complexity than with either of those types. The pump has
already been designed, built and tested under lab conditions, pumping
kerosene, liquid nitrogen and water. The performance improvements due to
inclusion of the pump in various systems have already been analyzed.
The purpose of this SBIR is to bring the pistonless pump technology up
to a TRL 5 level and integrate it into a nanosat launch vehicle. The
work to be done consists of designing, building and testing pump
features for operation under vibration, acceleration and reduced
absolute pressure environments. The pump will then be integrated into a
prototype NLV first stage and a full duration ground test will be
conducted.  If the budget is sufficient,  we will conduct a flight test
to 50,000 ft. The flight test pump and data will be delivered to NASA