SiC Matrix Composites for High Temperature Hypersonic Vehicle Applications

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$591,631.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
NNX11CB63C
Award Id:
n/a
Agency Tracking Number:
094869
Solicitation Year:
2009
Solicitation Topic Code:
A2.01
Solicitation Number:
n/a
Small Business Information
CA, Huntington Beach, CA, 92648-1208
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
798073391
Principal Investigator:
Robert Shinavski
Principal Investigator
(714) 375-4085
robert.shinavski@htcomposites.com
Business Contact:
Wayne Steffier
President
(714) 375-4085
wayne.steffier@htcomposites.com
Research Institution:
Stub




Abstract
Durable high temperature materials are required for reusable hypersonic structural thermal protection systems. In particular, temperatures exceeding 2700ºF, and approaching 3000ºF, are targeted for capable structural materials that can survive stresses on the order of 10 ksi (70 MPa) for at least 100 hours in an oxidizing environment. Such materials have been identified as an enabling material for future hypersonic vehicles As this application is structural, a strong degree of damage tolerance is desired, and thus ceramic matrix compositesare the primary choice due to the desire for reduced weight, high temperature strength and oxidation resistance. Silicon carbide fiber-reinforced silicon carbide matrix (SiC/SiC) composites are believed to be the most suitable solution due to meeting the requirementswith the limitations of creep at the highest temperatures/loads, and oxidative attack at stresses that exceed the materials proportional limit. The proposed effort will define the temperature-stress limit of SiC/SiC composites, and examine methods to further extend this limit.

* information listed above is at the time of submission.

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