期刊
JOURNAL OF AIRCRAFT
卷 48, 期 2, 页码 495-502出版社
AMER INST AERONAUT ASTRONAUT
DOI: 10.2514/1.C031106
关键词
-
A procedure is proposed for the assessment of the damage tolerance and collapse of stiffened composite panels using a single-stringer compression specimen. The dimensions of the specimen are determined such that the specimen's nonlinear response and collapse are representative of an equivalent multistringer panel in compression. Experimental tests are conducted on specimens with and without an embedded delamination. A shell-based finite element model with intralaminar and interlaminar damage capabilities is developed to predict the postbuckling response as well as the damage evolution from initiation to collapse.
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