北京航空航天大学学报 ›› 1998, Vol. 24 ›› Issue (5): 555-558.

• 论文 • 上一篇    下一篇

复合材料蜂窝夹芯板低速冲击后压缩强度估算

寇长河, 程小全, 郦正能   

  1. 北京航空航天大学 飞机器设计与应用力学系
  • 收稿日期:1997-09-25 发布日期:2010-11-18
  • 作者简介:男 58岁 高级工程师 100083 北京
  • 基金资助:

    航空科学基金(95B51066)资助项目

Prediction of the Compressive Strength for Composite Honeycomb Core Sandwich Panels after Low Speed Impact

Kou Changhe, Cheng Xiaoquan, Li Zhengneng   

  1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1997-09-25 Published:2010-11-18

摘要: 基于低速冲击后复合材料蜂窝夹芯板压缩破坏机理的实验研究,用当量分层来模拟Nomex蜂窝夹芯板的低速冲击损伤,假设当量分层区子层板的边界为固支,并且认为子层板失稳时夹芯板所承受的载荷为压缩破坏载荷.将计算结果与实验结果进行比较,表明了对面板无明显断裂的低速冲击损伤情况,用损伤当量法计算蜂窝夹芯板的剩余压缩强度是可行的.

Abstract: Based on the experimental study of compressive failure mechanisms on composite honeycomb core sandwich panels after low speed impact before, a equivalent delamination was used to replace the low speed impact damage of Nomex honeycomb core sandwich panels in this paper. It was postulated that the edge of sublaminate formed by the equivalent delamination is clamped. The load on which the sublaminate buckled was considered to be compressive failure load. Comparing the results of theory with experiment, it showed that the method of equivalent damage could be used to predict the residual compressive strength of honeycomb core sandwich panels, in the case that the facesheet of sandwich panels had no obvious cracks after low speed impact.

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