| PROPOSAL NUMBER: | 04 X6.05-9407 |
| SUBTOPIC TITLE: | In-Space Propulsion (Chemical/Thermal) |
| PROPOSAL TITLE: | Integrated Advanced Monopropellant CMC Thruster / Thermal Stand-Off Assembly |
SMALL BUSINESS CONCERN
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Fiber Materials Inc
5 Morin St
Biddeford, ME 04005-4497
(207)282-5911
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ralph A Langensiepen
rlangensiepen@fibermaterialsinc.com
5 Morin St
Biddeford, ME 04005-4497
(207)282-5911
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
High performance non-toxic monopropellants offer significant benefits relative to the current state-of-the-art. The benefits of these advanced monopropellants (AMP) include improved safety, a 50% reduction in density, and a 20% improvement in specific impulse (ISP). AMP propulsion represents a significant challenge for thruster components and assemblies due to the higher temperatures and the chemical constituents of the exhaust. This proposed program, with the support of Aerojet Redmond, will develop, design and fabricate an integrated ceramic matrix composite (CMC) thruster assembly comprised of the thermal stand-off (TSO), combustion chamber, and nozzle. The TSO will mitigate heat soak-back to the propellant valve utilizing an insulating CMC operating with a combustion environment greater than 2000oC. A phased design plan will be used for developing the integrated thruster assembly and results confirmed by test firing under representative conditions. A TSO prototype will be fabricated and the thermomechanical and thermochemical properties tested and analyzed during the Phase I program. The Phase II will utilize the TSO, materials development and conceptual design from the Phase I to develop an integrated CMC TSO - combustion chamber and nozzle assembly. A successful program will provide technology benefits resulting from improved performance, reduced cost and improved manufacturability.
POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Manned space missions will benefit from the higher performance and reduced toxicity afforded by advanced monopropellant (AMP) systems. Future Mars and Lunar landing craft will also require effective AMP solutions for attitude control systems (ACS). Docking manuevers will be enhanced with higher performance ACS.
POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercial launch vehicles and satellites will benefit from the higher performance and reduced toxicity of AMP thrusters in ACS and delta V applications.