Abstract: Composite I-beam is an essential load-bearing component in aircraft structure, and its instability behavior and damage characteristics under compressive load are the key points in engineering design. In order to study the compression performance and failure modes of composite I-beams, axial compression tests and numerical simulation calculations were carried out. The improved Hashin criterion was selected to determine the intra-layer damage, the cohesive adhesive element was introduced to simulate the inter-layer damage, and a stiffness degradation model based on the failure phenomenon of composite materials was used to reduce the material stiffness. In the model, the effects of fiber deflection and flange lateral support on the material performance after compression failure were comprehensively considered. The calculated load-displacement curve, load-strain curve, failure mode and failure load are in good agreement with the test results, which verifies the accuracy of the finite element model. Based on the experimentally verified model, a parametric analysis of the I-beam section was carried out, and the influence of the aspect ratio and flange width-thickness ratio on the buckling performance and bearing capacity of the composite I-beam was investigated, providing a reference for engineering structure optimization and selection.
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2022, Vol. 36 
