Using refractory ceramic materials to protect hot structures from aerothermal dynamic environments is not new. Such materials were considered for use on the first intercontinental ballistic missiles. A nose cap made of sintered refractory ceramic zirconium oxide tiles, was developed for the Dyna-Soar Project. Carbon-carbon laminates have been used extensively in missile applications and were on the Apollo thermal protection system. In the mid-tolate 1960's carbon and ceramic-material systems exhibited severe shortcomings as reusable thermal and structurally efficient systems. Ceramics in general were extremely brittle with high modulus, relatively low strength, and sensitivity to thermal shock. Carbon systems were subject to oxidation although oxidation rates were relatively low. Successful approaches to solving these mahor deficiencies, because of the military's need for high temperature ceramic materials, resulted in consideration of both refractory ceramics and carbon material systems for use as a thermal protection for hypersonic flight vehicles.
Early development of ceramic fiber insulation for the space shuttle
Fruehe Entwicklung von Keramikfaser-Isolation fuer den Raumgleiter
American Ceramic Society Bulletin ; 60 , 11 ; 1196-1200
1981
5 Seiten, 7 Bilder, 5 Tabellen, 3 Quellen
Aufsatz (Zeitschrift)
Englisch
HOCHTEMPERATURTECHNIK , VERBUNDWERKSTOFF , KERAMIK , HITZEBESTAENDIGKEIT , WAERMESCHUTZ , WAERMELEITFAEHIGKEIT , RAUMFAHRZEUG , TEMPERATURVERTEILUNG , OBERFLAECHENTEMPERATUR , THERMISCHE EIGENSCHAFT , SILICIUMDIOXID , GLASFASER , FASERVERSTAERKTER KUNSTSTOFF , EPOXIDHARZ , TEMPERATURABHAENGIGKEIT , KOHLENSTOFFASER
Development of Nonmetallic External Insulation Thermal Protection Systems for Space Shuttle
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