Post-buckling simulation of an integral aluminum fuselage panel subjected to axial compression load

Results from an experimental and analytical study of a curved stiffened panel subjected to axial compression load are presented. Nonlinear analysis was carried out and validated by the experimental results. An integral panel has been designed with the same overall size and weight as the build-up structure. The results on post-buckling load from finite element calculation indicate that the damage mode of the integral panel is the stress of the skin exceeding the yield level, and the damage mode of the build-up panel is buckling waves cross the stringers on oblique angle, which is different from the integral panel. Furthermore, the capacity of compressive load on the integral panel is superior to the one of build-up panel, and the critical compressive load has increased by 18.4%.