北京航空航天大学学报 ›› 1999, Vol. 25 ›› Issue (5): 565-568.

• 论文 • 上一篇    下一篇

复合材料夹层结构的逐渐破坏计算模型

张志民, 李晋秋, 郭艳阳   

  1. 北京航空航天大学 飞行器设计与应用力学系
  • 收稿日期:1998-12-14 发布日期:2010-11-19
  • 作者简介:男 64岁 教授 100083 北京
  • 基金资助:

    航空基础科学基金(98B51027)资助项目

Computational Model of Progressive Failure in Composite Sandwich Structures

Zhang Zhimin, Li Jinqiu, Guo Yanyang   

  1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1998-12-14 Published:2010-11-19

摘要: 建立了可以预测面内破坏、分层破坏和芯层破坏的复合材料夹层结构逐渐破坏模型.利用能量变分原理和非线性几何方程,以反对称失稳为例导出了考虑剪切效应夹层板的非线性稳定性控制方程组,并利用广义傅氏级数法对此高阶偏微分非线性方程组进行数值求解,在此基础上利用蔡-胡及最大剪应力强度理论及刚度退化规律得到复合材料夹层板的临界载荷、后屈曲路径、破坏过程和强度极限.

Abstract: Computational model of progressive failure in composite sandwich structures is built up to predict the face fracture,delamination failure and core failure. Nonlinear geometry equations and energy variational equation is estimated according to overall bulking of composite sandwich plates. The nonlinear stability governing equations of anti-symmetrical buckling of sandwich plate are deduced, considering the transverse shear deformation influence of core. In order to solve the governing equations, the method of generalized double Fourier series is employed. Tsai-Wu failure criteria and Maximum stress criteria are proposed to predict composite face-sheet failure,core failure and interlaminar failure. These failure criteria and stiffness reduction are used to obtain critical load,post-bulking behavior and limit load.

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