Numerical-expeimental investigation on post-buckled stiffened composite panels

F.Caputo; R.Esposito; P.Perugini

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Numerical-expeimental investigation on post-buckled stiffened composite panels

机译：后屈曲加劲复合板的数值试验研究

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The present work deals with a numerical-experimental investigation into the post-bucking behavior of two demonstrators representative of the bottom skin panel of an unpressurized aircraft fuselage: one represents an undamaged reference structure, the other includes debonding and impact damage. Tests have been developed for static compression loading up to the ultimate load. The recorded data from five transducers and One strain gauge have been utilized to obtain numerical-experimental correlation.

机译：目前的工作是对两个演示者的弯曲后的行为进行数值实验研究，该演示者代表了未加压飞机机身的底部蒙皮面板：一个代表未损坏的参考结构，另一个代表脱胶和撞击损坏。已经针对静态压缩载荷直至极限载荷进行了测试。来自五个换能器和一个应变仪的记录数据已用于获得数值实验相关性。

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来源
《Composite Structures》 |2002年第3期|p.347-357|共11页
作者
F.Caputo; R.Esposito; P.Perugini;
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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类工程材料学;
关键词
stiffened panels; post-buckling; impact damage; dyanic;

机译：加劲板后屈曲冲击破坏;Dyanic;

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6. Cross-Influence between Intra-Laminar Damages and Fibre Bridging at the Skin–Stringer Interface in Stiffened Composite Panels under Compression [O] . Angela Russo, Andrea Sellitto, Salvatore Saputo, 2019

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7. Mechanisms and modelling of stringer debonding in post-buckled carbon-fibre composite stiffened panels [O] . Bloodworth Victoria Margaux 2008

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Numerical-expeimental investigation on post-buckled stiffened composite panels

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