High Chamber Pressure, Light Weight Thrusters
National Aeronautics and Space Administration
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Small Business Information
Plasma Processes, Inc.
4914 Moores Mill Road, Huntsville, AL, 35811-1558
Socially and Economically Disadvantaged:
AbstractThe performance liquid propellant engines can be significantly improved by increasing both combustion temperature and pressure and reducing engine weight. State of the art Bi-propellant engines are metallic; the highest temperature combustion chambers are made of iridium/rhenium metals. Utilizing carbon-carbon composites for thrust chamber structures can reduce component weight by as much as 90%. Unfortunately carbon composites suffer from unacceptably high oxidation rates. Lining carbon-carbon chambers with a thin layer of iridium or iridium/rhenium is an innovative way to provide the oxidation barrier necessary to enable the use of carbon-carbon composites. This proposal evaluates using metal-lined carbon-carbon to produce high pressure, light weight thrust chambers.
* information listed above is at the time of submission.