复合材料机身帽型长桁加筋壁板压缩屈曲及失效特性研究

大型客机机身壁板材料现已广泛采用碳纤维复合材料，研究壁板的屈曲及失效特性对提高结构设计效率具有重要的意义。采用工程分析、有限元分析和试验三种方法研究压缩载荷下复合材料机身帽型加筋壁板的屈曲载荷、失效载荷和失效模式；通过工程方法和有限元方法研究压缩载荷下壁板的屈曲形式和载荷，采用 Von Karman 法修正的柱失稳方法研究壁板在压缩载荷下的承载能力；依靠先进的机身壁板多轴载荷试验系统完成 3 m×2 m 机身壁板的压缩载荷试验、压缩充压复合载荷试验，验证并完善工程和有限元分析方法。结果表明：屈曲分析时需要对工程分析和有限元方法进行修正，失效分析时采用修正的柱失稳方法的分析结果比试验结果略保守。

Research on compression buckling and failure characteristics of composite fuselage cap-stiffened panel

Carbon fiber reinforced polymer (CFRP) is widely used in the design of aircraft fuselage panel, it is important to study the buckling and failure characteristics of panel to improve the efficiency of structural design. The compression buckling load, failure mode and failure load of composite cap-stiffened panel under compression load are studied by analysis and panel test. The buckling modes and loads of panels under compression are studied by engineering method and finite element method. The loading capacity of the panel under compression load is studied by the column instability method modified by von Karman method. Based on the advanced multi-load panel test rig, the 3m×2m panel test are completed under compression load and pressure load. the analysis methods are verified and modified by test. The results show that the engineering analysis and finite element method need to be modified in buckling analysis, and the results of the modified column instability method are slightly conservative than the test results.