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High Chamber Pressure, Light Weight Thrusters

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX10CF23P
Agency Tracking Number: 094826
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: S3.08
Solicitation Number: N/A
Timeline
Solicitation Year: 2009
Award Year: 2010
Award Start Date (Proposal Award Date): 2010-01-29
Award End Date (Contract End Date): 2010-07-29
Small Business Information
4914 Moores Mill Road
Huntsville, AL 35811-1558
United States
DUNS: 799114574
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Tim McKechnie
 Principal Investigator
 (256) 851-7653
 timmck@plasmapros.com
Business Contact
 Timothy McKechnie
Title: President
Phone: (256) 851-7653
Email: 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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