北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (6): 701-704.

• 论文 • 上一篇    下一篇

含椭圆分层缝纫复合材料层板的局部屈曲研究

桂良进, 叶宁, 郦正能, 寇长河   

  1. 北京航空航天大学 飞行器设计与应用力学系
  • 收稿日期:1999-06-16 发布日期:2010-11-19
  • 作者简介:桂良进(1971-),男,江西星子人,博士生,100083,北京.
  • 基金资助:

    航空科学基金资助项目(96B51017)

Study on Local Buckling of Stitched Composite Laminates with an Elliptical Delamination

GUI Liang-jin, YE Ning, LI Zheng-neng, KOU Chang-he   

  1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1999-06-16 Published:2010-11-19

摘要: 建立了分析含椭圆分层的缝纫增强复合材料层板压缩屈曲问题的三维模型.通过应用瑞利-里兹法研究了分层椭圆几何参数和缝线等效弹性系数对压缩屈曲载荷的影响.分析结果表明,缝纫对提高临界曲屈载荷的作用十分明显,随着缝线等效弹性系数的增大,临界曲屈载荷迅速提高;分层椭圆的长轴垂直于载荷方向时,临界曲屈载荷最小,并且随长轴的长度增大时,临界曲屈载荷减小并逐渐收敛.

Abstract: Delamination buckling of stitched laminates can cause high interlaminar stresses which, in turn, lead to delamination growth. This study presents a three-dimensional model to analysis local buckling of stitched composite laminates with an embedded elliptic delamination near the surface. The effects of geometry parameters of ellipse and stitching thread on buckling loads are investigated by Rayleigh-Ritz energy method. The results show that stitching significantly improves critical buckling loads, the buckling loads increase rapidly with increase in equivalent elastic coefficient of stitching thread. The buckling loads are relatively large when the long axis of ellipse is vertical to the loading direction. With the increase in length of long axis, the buckling loads decrease and converge gradually.

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发