Abstract: A finite element model of stiffened composite structure is established with ABAQUS. The buckling behavior is analyzed by the Linear Eigenvalue Method under axial compression. The critical buckling loads are computed using the modes. The buckling loading capabilities are affected by various factors, which include stiffener parameters, panel parameters and boundary conditions. Simulation result shows that the buckling loads are obviously affected by the height and numbers of stiffeners, the thickness and sequence of panel layers, and the boundary conditions.

Key words: aviation composite, stiffened laminate, axial compression, buckling load-carrying capacity