Abstract: Based on the moment distribution method, the buckling analysis theory of fiber-metal reinforced civil aircraft plate structure under axial compression load is studied, the compressive strength of the civil aircraft plate structure is analyzed and calculated, and a theoretical prediction model for the ultimate strength of the civil aircraft plate structure after buckling is proposed. By comparing with the compressive strength failure test results of fiber-metal reinforced plate structure of civil aircraft, the theoretical predicted values of the model are in good agreement with the experimental values, with a deviation of 3.01%. The accuracy of the strength prediction model established is verified. In addition, the buckling and post-buckling load-bearing capacities of fiber-metal reinforced civil aircraft plate structure were analyzed by using the finite element method, and the stress concentration area and failure process of the plate were simulated. The results show that the plate structure have ideal post-buckling load-bearing capacities after local buckling. This study can provide some theoretical basis and experimental data for the material selection of reinforced civil aircraft plate structure configuration, the improvement of technological performance and the prediction of the compression strength value of fiber metal reinforced civil aircraft plate structure, and can replace the compression test of large structural parts of the plate structure and reduce the cost and cycle of the pre-research experiment in the stage of civil aircraft pre-research and design.

Key words: compressive strength forecast, fiber metal stiffened siding, reinforced civil aircraft panel, composites