The use of high strength and modulus of advanced filamentary composites to reduce the structural weight of aerospace vehicles was investigated. Application of the technology to space shuttle components was the primary consideration. The mechanical properties for the boron/epoxy, graphite/epoxy, and polyimide data are presented. Structural testing of two compression panel components was conducted in a simulated space shuttle thermal environment. Results of the tests are analyzed. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Evaluation of a Metal Fuselage Panel Selectively Reinforced with Filamentary Composites for Space Shuttle Application


    Beteiligte:
    W. F. Wennhold (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    217 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch