航空学报 > 1989, Vol. 10 Issue (8): 403-408

有限宽层合板边界效应影响拉伸强度的修正方法

李顺林, 肖军   

  1. 南京航空学院
  • 收稿日期:1988-09-06 修回日期:1900-01-01 出版日期:1989-08-25 发布日期:1989-08-25

A METHOD OF MODIFICATION TO ALLOW FOR THE EDGE-EFFECT OF THE LAMINATE OF FINITE WIDTH ON THE TENSILE STRENGTH

Li Shunlin, Xiao Jun   

  1. Nanjing Aeronautical Institute
  • Received:1988-09-06 Revised:1900-01-01 Online:1989-08-25 Published:1989-08-25

摘要:

本文分析了[0/90]_s,[45/-45]_s,以及π/4层合板的有限宽碳/环氧层合板在不同宽度下的拉伸强度。发现导致层合板过早破坏的原因,除了由于层间应力引起分层破坏外,主要是分层后的叠合铺层强度低于层合板强度;并给出了一般均衡对称的π/4层合板用有限宽试样测试拉伸强度时由于边界效应影响的修正方法。这是一种基于试验结果的经验方法。

关键词: 有限宽层合板, 边界效应, 拉伸强度, 复合材料, 层间应力

Abstract:

This paper presents an analysis of the tensile strength of [0/90]s,[45/- 45]s , and π/4 graphite/epoxy laminates of various finite width.It is found that, besides the delamination failure due to the interlaminar stresses, the main cause of the unduly-soon failure of the laminate lies in the fact that the strength of the delamination laminate is lower than that of the original laminate A method of modification is also given to allow for the edge-effect produced by using a specimen of finite width to measure the tensile strength of the general balanced symmetrical π/4 laminate This is an empirical approach based on the results of experiments.

Key words: laminate of finite width, edge-effect, tensile strength, composite material, interlaminar stress