A CERAMIC-MATRIX COMPOSITE THERMAL PROTECTION SYSTEM FOR HYPERSONIC VEHICLES

The next generation of hypersonic vehicles (NASP, SSTO) that require r eusable thermal protection systems will experience acreage surface tem peratures in excess of 1100-degrees-C More important, they will experi ence a more severe physical environment than the Space Shuttle due to non-pristine launching and landing conditions. As a result, maintenanc e, inspection, and replacement factors must be more thoroughly incorpo rated into the design of the TPS. To meet these requirements, an advan ced thermal protection system was conceived, designated ''TOPHAT '' Th is system consists of a toughened outer ceramic matrix composite (CMC) attached to a rigid reusable surface insulator (RSI) which is directl y 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 exist ing thermal protection systems.