四边固支复合材料矩形平板轴压失稳的解析解  

Buckling Analytic Solution of CCCC Rectangular Composite Laminates under Axial Compression Load

作　　者：苏雁飞 赵占文 张彬 SU Yan-fei;ZHAO Zhan-wen;ZHANG Bin(The First Aircraft Institute of the Aviation Industry Corporation of China,Xi’an 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,西安710089

出　　处：《强度与环境》2022年第2期28-33,共6页Structure & Environment Engineering

基　　金：航空科学基金(2017ZD03020)。

摘　　要：为了得到四边固支(CCCC)复合材料矩形平板的轴压稳定性计算公式,首先构造了一种满足边界条件的位移函数,应用能量法得到了一种在四边固支边界下复合材料矩形层压板临界失稳载荷计算的解析解。该解析解所得失稳载荷与有限元方法和参考文献的计算结果相差小于5.5%,与试验值结果误差小于5%,位移函数所得波形与有限元结果吻合良好,本文方法可用于四边固支不同长宽比复合材料矩形平板在轴压载荷下的失稳载荷计算。In order to obtain the local buckling load of rectangular composite laminates with four sides clamped(CCCC)under axial compression load,a deflection function satisfying the boundary conditions is created,then the critical buckling load is derived using the energy method.It is found that the local buckling load given by analytical solution is not greater than 5.5%compared with the finite element simulation and conference results,and less than 5%compared with test results,and the shape of buckling wave matches well,and.The analytical solution presented can be used for calculate the local buckling load of CCCC rectangular composite laminates with any ratio of length to width under axial compression load.

关 键 词：固支 复合材料 层压板 轴压 稳定性 

分 类 号：V214.3[航空宇航科学与技术—航空宇航推进理论与工程]