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.
Shell Instability Analysis Using the Finite Element Method
Sae Technical Papers
National Business Aircraft Meeting and Engineering Display ; 1974
1974-02-01
Conference paper
English
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