Panels with integral stiffeners made with woven fabric in two-dimensional, cross-ply layups. Local skin buckling does not cause collapse of panels, and ultimate failure occurs at loads 10 to 20 percent above buckling loads. For panels subjected to in-plane loading, separation of stiffeners from panel skins was not problem. High-temperature structural applications on advanced aircraft and spacecraft include leading edges, fairings, and control surfaces.


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    Title :

    Stiffened Carbon/Carbon Compression Panels


    Contributors:

    Published in:

    Publication date :

    1992-04-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English






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