Box beam simulating dry wing structure of high L/D hypersonic flight vehicle was fabricated and tested under simulated flight conditions; design techniques used to minimize thermal stresses are presented together with experimental results demonstrating structural integrity; structure used brazed honeycomb sandwich skin panels and corrugated plate webs of D-43 columbium and Haynes-25 superalloy; deleterious temperature differences were reduced by combining use of insulation with detail design arrangements; conclusions and review of test results.


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    Titel :

    Design and testing of hot redundant structure concept for hypersonic flight vehicle


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    McCown, J.W. (Autor:in) / Barrett, W.F. (Autor:in) / Norton, A.M. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Design and testing of a hot redundant structure concept for a hypersonic flight vehicle.

    BARRETT, W. F. / MCCOWN, J. W. / NORTON, A. M. | AIAA | 1966


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    W. Williamson | NTIS | 1987


    Hypersonic Flight Testing

    V. K. Smith / R. K. Matthews / J. R. Maus | NTIS | 1994


    Hypersonic flight testing

    WILLIAMSON, W. | AIAA | 1992