Small Business Innovation Research/Small Business Tech Transfer
High Chamber Pressure, Light Weight Thrusters, Phase I
Project Description
The 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.
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Anticipated Benefits
Rocket nozzles for satellites and military. Metal lined carbon composite technology has applications for crucibles, heat pipes, propulsion subcomponents, x-ray targets, sputtering targets, turbines, rotors, furnaces, power generation Mars Ascent Vehicle, Altair Ascent Module, reaction control systems, in-space propulsion, attitude control, orbit maintenance, repositioning of satellites/spacecraft, and descent/ascent engines, nuclear power/propulsion, microgravity containment crucibles and cartridges.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Marshall Space Flight Center
(MSFC)
|
Supporting Organization | NASA Center | Huntsville, Alabama |
Primary U.S. Work Locations
-
Alabama
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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.