High Performance Bipropellant Space Engines

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$100,000.00
Award Year:
2007
Program:
SBIR
Phase:
Phase I
Contract:
NNJ07JB06C
Award Id:
83839
Agency Tracking Number:
066580
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
4914 Moores Mill Road, Huntsville, AL, 35811
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
799114574
Principal Investigator:
John O'Dell
Principal Investigator
(256) 851-7653
scottodell@plasmapros.com
Business Contact:
Timothy McKechnie
President
(256) 851-7653
timmck@plasmapros.com
Research Institution:
n/a
Abstract
Advanced bipropellant engines are needed for ARES/ORION vehicle maneuvering and future deep space science missions. Currently, an iridium-lined rhenium combustion chamber is the state-of-the-art for in-space propulsion applications. An example of an in-space engine that incorporates an iridium-lined rhenium thruster is Aerojet's HiPAT apogee engine. This engine uses monomethyl-hydrazine (MMH, CH3N2H3) as fuel and nitrogen tetroxide (N2O4, specifically MON-3) as oxidizer. To increase performance of bipropellant engines, improved chamber materials are needed that will allow higher operating conditions (pressure and temperature) and better resistance to oxidation. Therefore, Plasma Processes, Inc. and its partner, Aerojet, propose to develop hafnium oxide-iridium lined rhenium combustion chambers that will simplify engine design and allow higher operating conditions. As a result, a lower cost, higher performance bipropellant space engine will be produced.

* information listed above is at the time of submission.

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