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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    Title :

    Shell Instability Analysis Using the Finite Element Method


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    National Business Aircraft Meeting and Engineering Display ; 1974



    Publication date :

    1974-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English






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