SiC Matrix Composites for High Temperature Hypersonic Vehicle Applications

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX11CB63C
Agency Tracking Number: 094869
Amount: $591,631.00
Phase: Phase II
Program: SBIR
Awards Year: 2011
Solicitation Year: 2009
Solicitation Topic Code: A2.01
Solicitation Number: N/A
Small Business Information
CA, Huntington Beach, CA, 92648-1208
DUNS: 798073391
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Robert Shinavski
 Principal Investigator
 (714) 375-4085
 robert.shinavski@htcomposites.com
Business Contact
 Wayne Steffier
Title: President
Phone: (714) 375-4085
Email: 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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