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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    Title :

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


    Additional title:

    J Spacecraft Rockets


    Contributors:
    McCown, J.W. (author) / Barrett, W.F. (author) / Norton, A.M. (author)

    Published in:

    Publication date :

    1966


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    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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