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。
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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第8期B403-B408,共6页
Acta Aeronautica et Astronautica Sinica
关键词
层合板
边界效应
拉伸
强度
修正
laminate of finite width, edge-effect, tensile strength, composite material, interlaminar stress.
