A method of forming a thermal protection system for high speed aircraft is described. The method includes mechanically working an uncured ablator material into a first surface of a felt layer such that the ablator material penetrates a distance into a thickness of the felt layer thereby forming an region that has a mixture of felt and ablator material, adding additional uncured ablator material to the worked ablator material, and curing the combined ablator material.


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    Titel :

    Hybrid ablative thermal protection systems and associated methods


    Beteiligte:

    Erscheinungsdatum :

    2019-05-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B64G Raumfahrt , COSMONAUTICS



    HYBRID ABLATIVE THERMAL PROTECTION SYSTEMS AND ASSOCIATED METHODS

    BREWER BRYAN CLARK / MOBERS PATRICK JACOB | Europäisches Patentamt | 2016

    Freier Zugriff

    Ablative thermal protection systems

    Pittman, C. M. / Vosteen, L. F. | NTRS | 1971


    Ablative thermal protection systems

    Vaniman, J. / Fisher, R. / Wojciechowski, C. et al. | NTRS | 1983


    Ablative thermal protection systems modeling

    Duffa, Georges | TIBKAT | 2013