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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    Titel :

    Stiffened Carbon/Carbon Compression Panels


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.04.1992



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




    Stiffened steel compression panels : a design approach

    Dwight, J. B. / Little, G. H. | TIBKAT | 1974


    An approach to stiffened steel compression panels

    Dwight, J. B. / Little, G. H. / Rogers, N. A. | TIBKAT | 1973


    Stress distribution in stiffened panels under compression

    Sechler, E.E. | Engineering Index Backfile | 1937