复合材料帽形加筋壁板轴压屈曲与后屈曲性能  

Buckling and post-buckling performance of hat-stiffened composite panels under axial compression load

作　　者：汪厚冰[1] 陈昊[1] 雷安民[1] 魏宏艳[1] 陈丽敏[1] 李新祥[1] WANG Houbing;CHEN Hao;LEI Anmin;WEI Hongyan;CHEN Limin;LI Xinxiang(Aircraft Strength Research Institute of China,Xi＇an 710065,China)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《复合材料学报》2018年第8期2014-2022,共9页Acta Materiae Compositae Sinica

摘　　要：针对2种边界条件和3种板元宽度情况,采用几种屈曲方法对轴压载荷作用下的复合材料帽形加筋壁板进行了计算,得到了不同情况下的屈曲载荷,通过对复合材料加筋壁板几种计算方法的计算结果与试验结果的对比,得到一种更简单有效计算复合材料帽形加筋壁板轴压屈曲载荷的方法;依据帽形加筋壁板的结构特点和试验后的破坏模式,提出一种估算复合材料帽形加筋壁板轴压破坏载荷的方法,用该方法在几个项目上的计算结果与试验结果进行比较,发现两者较吻合,验证了复合材料帽形加筋壁板轴压承载能力估算方法的合理性,为结构设计人员在初始设计阶段对复合材料帽形加筋壁板轴压强度评估提供了一种简洁的途径。To analyze composite hat-stiffened panels,several calculation methods were adopted firstly for calculating the compression buckling performance of composite hat-stiffened panels under axial compression to obtain the buckling load under two boundary conditions and three widths of sample.The buckling loads of different calculation methods were obtained.The calculation results were compared with the test results in order to find out a simple and effective method of obtaining buckling load of hat-stiffened composite panels under axial compression.According to dense stiffener in hat-stiffened panel of current aircraft structure,the structure characters and failure patterns of hatstiffened composite panels,a simple calculation method was proposed to estimate the failure loads of hat-stiffened composite panels under axial compression.Calculation results accord with the test results well,which validates the rationality of engineering method.It is preferable accuracy to estimate the failure load of composite hat-stiffened panels by the engineering calculation method.

关 键 词：复合材料 帽形加筋壁板 屈曲 后屈曲 破坏载荷 

分 类 号：TB330.1[一般工业技术—材料科学与工程]