The finite element displacement procedure is used to compute the instability load for a general shaped, orthotropic sandwich construction shell. For general shaped shells, failure usually occurs by means of collapse at a limit point rather than through bifurcation. Both a linear bifurcation buckling load and a geometric nonlinear analysis collapse load are computed for the nose radome of a large aircraft. The analytical solutions are compared with static test results, showing the nonlinear collapse load to be in excellent agreement.


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    Titel :

    Shell Instability Analysis Using the Finite Element Method


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    National Business Aircraft Meeting and Engineering Display ; 1974



    Erscheinungsdatum :

    01.02.1974




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch






    A discrete element procedure for thin-shell instability analysis.

    GALLAGHER, R. H. / GELLATLY, R. A. / MALLETT, R. H. | AIAA | 1967



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