composite, post-buckling, progressive damage analysis, cohesive zone model, finite element model, engineering calculation method, Motor vehicles. Aeronautics. Astronautics, TL1-4050

Post-buckling analysis methods of fiber-reinforced T section stiffened composite panels were investigated. In this paper, the Finite Element Model was presented. In the model, the progressive damage analysis (PDA) and the cohesive zone model (CZM) were used to simulate the damage progression in skin and stiffener and interface failure between them. Therefore, the failure mode and buckling load and damage load were obtained. Besides, the engineering calculation method was also improved to get buckling load and damage load. Finally, an excellent agreement was found between the analytical prediction and the experimental data, and the effectiveness of these two analysis methods was also verified.