High Chamber Pressure, Light Weight Thrusters

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$100,000.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
NNX10CF23P
Agency Tracking Number:
094826
Solicitation Year:
2009
Solicitation Topic Code:
S3.08
Solicitation Number:
n/a
Small Business Information
Plasma Processes, Inc.
4914 Moores Mill Road, Huntsville, AL, 35811-1558
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
799114574
Principal Investigator:
Tim McKechnie
Principal Investigator
(256) 851-7653
timmck@plasmapros.com
Business Contact:
Timothy McKechnie
President
(256) 851-7653
timmck@plasmapros.com
Research Institution:
n/a
Abstract
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.

* information listed above is at the time of submission.

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