Shell Instability Analysis Using the Finite Element Method

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.