基于显式有限元的复合材料加筋板后屈曲分析方法研究  

Research on post-buckling for composite stiffened panel based on explicit FEM

作　　者：袁坚锋 Yuan Jianfeng(Shanghai Aircraft Design and Research Institute of COMAC, Shanghai, 201210, China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2021年第4期73-76,共4页Machine Design and Manufacturing Engineering

摘　　要：通过非线性屈曲理论建立了复合材料加筋板有限元分析模型,采用三维界面单元模拟蒙皮和筋条的脱粘,应用二维Hashin失效准则模拟复合材料的失效,通过ABAQUS/Explicit显式求解器研究了复合材料加筋板在压缩载荷下的屈曲和后屈曲行为及破坏过程,并与试验结果进行了对比。结果表明,有限元模拟与试验结果在屈曲载荷、破坏载荷及破坏模式方面均吻合得很好。Combined with correlative test,based on the constitutive equations of composite,the property of buckling and post-buckling of composite stiffened-panel is deeply researched by ABAQUS/Explicit method.The in-plane and interface damages are simulated by 2-D element with Hashin failure criterion and 3-D cohesive element.The results of prediction are also compared with those of test.The comparison shows that buckling load,failure load and failure mode of FEA and test match well.

关 键 词：有限元分析 复合材料 加筋板 后屈曲 

分 类 号：V222[航空宇航科学与技术—飞行器设计]