Small Business Innovation Research/Small Business Tech Transfer
High Chamber Pressure, Light Weight Thrusters, Phase I
Project Introduction
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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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Responsible Program:
- Small Business Innovation Research/Small Business Tech Transfer
Project Management
Program Director:
Program Manager:
Principal Investigator:
Project Duration
Start: Jan 2010
End: Jul 2010
Technology Maturity (TRL)
| Start: | 3 |
| Current: | 4 |
| Estimated End: | 4 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TX01 Propulsion Systems
- TX01.1 Chemical Space Propulsion
- TX01.1.3 Cryogenic
Target Destination
Earth
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