Improved Rhenium Thrust Chambers for In-Space Propulsion

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$900,000.00
Award Year:
2012
Program:
SBIR
Phase:
Phase II
Contract:
NNX12CA25C
Award Id:
n/a
Agency Tracking Number:
104787
Solicitation Year:
2010
Solicitation Topic Code:
S3.04
Solicitation Number:
n/a
Small Business Information
4914 Moores Mill Road, Huntsville, AL, 35811-1558
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
799114574
Principal Investigator:
John Scott O'Dell
Principal Investigator
(256) 851-7653
scottodell@plasmapros.com
Business Contact:
Timothy McKechnie
President
(256) 851-7653
timmck@plasmapros.com
Research Institute:
Stub




Abstract
Radiation-cooled, bipropellant thrust chambers are being considered for the ascent/descent engines and reaction control systems for NASA missions such as Mars Sample Return and Orion MPCV. Currently, iridium-lined rhenium combustion chambers are the state-of-the-art for in-space engines. NASA's Advanced Materials Bipropellant Rocket (AMBR) engine, a 150-lbf iridium-rhenium chamber produced by Plasma Processes and Aerojet, recently set a hydrazine specific impulse record of 333.5 seconds. To withstand the high loads during terrestrial launch, rhenium chambers with improved mechanical properties are needed. Recent EL-FormTM results have shown considerable promise for improving the mechanical properties of rhenium by producing a multi-layered deposit comprised of a tailored microstructure, i.e., Engineered Re. During Phase I, an AMBR size chamber was produced to demonstrate formation of the Engineered Re material in both the throat and barrel regions. Tensile tests showed the Engineered Re material had a yield strength greater than 40ksi at room temperature. In addition, Engineered Re deposits were produced on multiple mandrels at one time, i.e., multi-component process demonstration. During Phase II, the Engineered Re processing techniques will be optimized. Detailed characterization and mechanical properties test will be performed. Optimization of the multi-component fabrication technique will result in a 30% or higher reduction in chamber fabrication costs. The most promising techniques will be selected and used to produce an Engineered Re AMBR size combustion chamber for testing at Aerojet.

* information listed above is at the time of submission.

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