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  

Research on Compression Buckling and Failure Characteristics of Composite Fuselage Cap-stringer Stiffened Panel

作　　者：李真[1] 程立平[2] LI Zhen;CHENG Liping(Institute of Aircraft Structural Strength Engineering,Shanghai Aircraft Design and Research Institute,Shanghai 201210,China;Laboratory of Composite Structural Strength,China Aircraft Strength Research Institute,Xi’an 710065,China)

机构地区：[1]上海飞机设计研究院飞机结构强度工程技术所,上海201210 [2]中国飞机强度研究所复合材料结构强度研究室,西安710065

出　　处：《航空工程进展》2021年第4期123-130,共8页Advances in Aeronautical Science and Engineering

基　　金：民机科研项目(MJ-2015-F-038)

摘　　要：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。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-stringer stiffened panel under compression load are studied by engineering analysis,finite element 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 3 m×2 m panel test are completed under compression load and pressure load.The engineering analysis method and finite element analysis method 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.

关 键 词：复合材料 机身壁板 帽型长桁 压缩载荷 稳定性 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]