期刊
COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING
卷 31, 期 5, 页码 459-468出版社
ELSEVIER SCI LTD
DOI: 10.1016/S1359-835X(99)00085-8
关键词
stiffened composite panel; buckling
The postbuckling behaviour of a panel with blade-stiffeners incorporating tapered flanges was experimentally investigated. A new failure mechanism was identified for this particular type of stiffener. Failure was initiated by mid-plane delamination at the free edge of the postbuckled stiffener web at a node-line. This was consistent with an interlaminar shear stress failure and was calculated from strain gauge measurements using an approximate analysis based on lamination theory and incorporating edge effects. The critical shear stress was found to agree well with the shear strength obtained from a three-point bending test of the web laminate. (C) 2000 Elsevier Science Ltd. All rights reserved.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据