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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Developments in fibrous refractory composite insulation


    Additional title:

    Entwicklungen feuerfester Faserverbundwerkstoff-Isolation


    Contributors:
    Leisler, D.B. (author) / Smith, M. (author) / Goldstein, H.E. (author)

    Published in:

    Publication date :

    1981


    Size :

    4 Seiten, 9 Bilder, 1 Tabelle, 13 Quellen


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    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


    Transport and Installation of Fibrous Insulation

    Borck, S. / Falconer, F. L. / Loustau, R. V. | NTRS | 1983