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A ceramic matrix composite thermal protection system for hypersonic vehiclesThe 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.
Document ID
19930069711
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Riccitiello, Salvatore R.
(NASA Ames Research Center Moffett Field, CA, United States)
Love, Wendell L.
(NASA Ames Research Center Moffett Field, CA, United States)
Pitts, William C.
(Eloret Inst. Sunnyvale, CA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Publication Information
Publication: SAMPE Quarterly
Volume: 24
Issue: 4
ISSN: 0036-0821
Subject Category
Composite Materials
Accession Number
93A53708
Distribution Limits
Public
Copyright
Other

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