A comparison of finite element buckling analysis predictions and experimental results for riveted aircraft fuselage panels

摘要

The prediction of the behaviour and the ultimate load for compressively stiffened aircraft shell structures is a very important non-linear analysis problem for engineers. Herein, finite element analysis and experimental tests are carried out for the buckling of aircraft stiffened fuselage panels. The calculated finite element results for both flat and curved bulbed-T panels correlated well with the experimental results. A change of mode shape is observed for the curve panel, which is very imperfection sensitive. This study reveals that the finite element code used, 'ABAQUS' is capable of modelling the behaviour of the buckling phenomenon for small aircraft fuselage panels.