A ceramic matrix composite thermal protection system for hypersonic vehicles

Journal Article · Thu Jul 01 00:00:00 EDT 1993 · SAMPE Quarterly (Society of Aerospace Material and Process Engineers); (United States)

OSTI ID:5552532

Riccitiello, S R; Love, W L; Pitts, W C ^[1]

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1. NASA, Ames Research Center, Moffett Field, CA (United States) Eloret Inst., Sunnyvale, CA (United States)

The next generation of hypersonic vehicles (NASP, SSTO) that require reusable thermal protection systems will experience acreage surface temperatures in excess of 1100 C. More important, they will experience a more severe physical environment than the Space Shuttle due to non-pristine launching and landing conditions. As a result, maintenance, inspection, and replacement factors must be more thoroughly incorporated into the design of the TPS. To meet these requirements, an advanced thermal protection system was conceived, designated 'TOPHAT'. This system consists of a toughened outer ceramic matrix composite (CMC) attached to a rigid reusable surface insulator (RSI) which is directly bonded to the surface. The objective of this effort was to evaluate this concept in an aeroconvective environment, to determine the effect of impacts to the CMC material, and to compare the results with existing thermal protection systems. 10 refs.

• Research Organization: National Aeronautics and Space Administration, Moffett Field, CA (United States). Ames Research Center
• OSTI ID: 5552532
• Journal Information: SAMPE Quarterly (Society of Aerospace Material and Process Engineers); (United States), Vol. 24:4; ISSN 0036-0821
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
CERAMICS
THERMAL STRESSES
COMPOSITE MATERIALS
IMPACT TESTS
THERMAL SHIELDS
MATERIALS
MATERIALS TESTING
MECHANICAL TESTS
SHIELDS
STRESSES
TESTING
360606* - Other Materials- Physical Properties- (1992-)