基于FEA的复合材料结构极限承载失效预测  

Failure Prediction of Composite Structures Based on FEA

作　　者：章凌 赵优存 李祎[2] 杨帆 崔浩[2] ZHANG Ling;ZHAO Youcun;LI Yi;YANG Fan;CUI Hao(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;Northwestern Polytechnical University,Taicang 215513,China)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]西北工业大学民航学院,太仓215513

出　　处：《宇航总体技术》2023年第5期29-37,共9页Astronautical Systems Engineering Technology

基　　金：国家自然基金面上项目(12072289)。

摘　　要：针对复合材料层合板失效分析,基于经典层合板理论与一阶剪切变形理论,通过层合板等效刚度以及各单层板的应力应变建立了一种并行多尺度方法,并基于此方法采用FORTRAN语言编写了子程序,通过与试验结果以及有限元分析(Finite Element Analysis,FEA)软件内嵌的复合材料失效模型进行对比,证实了并行多尺度方法的可行性,实现了对复合材料层合板在多种工况情况下的渐进损伤分析。For the failure analysis of composite laminates,this paper establishes a parallel multiscale method based on classical laminate theory by equivalent stiffness of the laminate and stress-strain of each single layer plate.Based on this method,a subroutine is written in FORTRAN language.By comparing with experimental results and the composite material failure model embedded in Finite Element Analysis(FEA)software,the feasibility of the parallel multiscale method is verified,and the progressive damage analysis of composite laminates under various working conditions is realized.

关 键 词：复合材料 并行多尺度方法 渐进损伤分析 

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]