Early in the 1970's, a new low density insulation material was adopted to thermally protect the aluminum structure of the Space Shuttle from the high temperatures normally encountered during atmospheric entry. The thermal protection system was designed to be reused for at least 100 flights at 1260 Cel before replacement. All previous manned space-flight vehicles utilized ablative materials, which were used for only one entry. The material developed for the Shuttle, a rigidized fibrous insulation, was called reusable surface insulation (RSI). Its density and conductivity were optimized (minimum conductivity and weight) to keep the thermal protection system weight as low as possible, consistent with adequate mechanical properties to increase the resultant payload capability of the vehicle.


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    Titel :

    Developments in fibrous refractory composite insulation


    Weitere Titelangaben:

    Entwicklungen feuerfester Faserverbundwerkstoff-Isolation


    Beteiligte:
    Leisler, D.B. (Autor:in) / Smith, M. (Autor:in) / Goldstein, H.E. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1981


    Format / Umfang :

    4 Seiten, 9 Bilder, 1 Tabelle, 13 Quellen


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Fibrous refractory composite insulation

    Goldstein, H. E. / Smith, M. / Leiser, D. B. | NTRS | 1974


    Gas Permeability of Rigid Fibrous Refractory Insulations

    Jochen Marschall / Frank S. Milos | AIAA | 1998



    Gas permeability of rigid fibrous refractory insulations

    Marshall, Jochen / Milos, Frank | AIAA | 1997


    Phase change effects on fibrous insulation

    VAFAI, K. / SARKAR, S. | AIAA | 1984