Postbuckling behaviour of a blade-stiffened composite panel loaded in uniaxial compression

被引：88

作者：

Falzon, BG ^{[1
]}

Stevens, KA ^{[1
]}

Davies, GO ^{[1
]}

机构：

[1] Univ London Imperial Coll Sci Technol & Med, Dept Aeronaut, London SW7 2BY, England

来源：

COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING | 2000年 / 31卷 / 05期

关键词：

stiffened composite panel; buckling;

D O I：

10.1016/S1359-835X(99)00085-8

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

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.

引用

页码：459 / 468

页数：10

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