杨俊清,王俊,孟庆功.复合材料帽型加筋壁板轴压屈曲工程算法验证研究[J].民用飞机设计与研究,2019,(1):18-
复合材料帽型加筋壁板轴压屈曲工程算法验证研究
  
DOI:10.19416/j.cnki.1674-9804.2019.01.003
中文关键词:复合材料  帽型加筋壁板  压缩屈曲  工程计算方法
英文关键词:composite material  hat-stiffened panel  buckling load  engineering calculation method
基金项目:
作者单位
杨俊清,王俊,孟庆功 上海飞机设计研究院上海 201210 
中文摘要:计算复合材料加筋壁板轴向压缩屈曲载荷的方法会根据不同工况而各异。文章研究了四边简支、四边固支等边界条件下,考虑帽型加筋桁条底脚对蒙皮的支撑作用,按不同的厚度折算方式时,多种工程理论计算方法对复合材料帽型加筋壁板试验件轴向压缩屈曲载荷分析的适用性,并将工程理论计算结果与试验值进行了对比。计算结果表明,多种方法中只有四边固支,并假设桁条与蒙皮轴向刚度相等进行的加筋桁条底脚厚度折算时,最终计算的结果才与试验值吻合较好,误差在可接受范围。由于试验件批量若干,试验件的相关结构参数、铺层顺序以及边界条件具有典型性和代表性且与工程实际结构有相关性,故该方法对于飞机工程型号设计以及强度分析快速计算具有参考和借鉴意义。
英文摘要:The calculation method of stiffened composite panel buckling load varies with different load conditions. Considering different thick equivalence of hat-stiffened stringer foot for the skin, the applicability of several engineering calculation methods for buckling load of hat-stiffened composite panel with four edges simply supported and fixed supported subjected to axial compression was investigated, and calculation results were compared with experimental data in this paper. The results show that the method which considers four edges simply supported and provided, and the axial stiffness of stringer and skin were the same matches favorably well with experimental data and the error is within the tolerance scope. Since there are large number of the test panels, the test panel structure, stacking sequence of the laminate as well as the boundary conditions express typical, and representative characters, and pertinence with certain engineering structure. The calculation method has good reference for aircraft program design and quick strength analysis.
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