EXPERIMENTAL BUCKLING OF CYLINDRICAL COMPOSITE PANELS WITH ECCENTRICALLY LOCATED CIRCULAR DELAMINATIONS

被引：7

作者：

HORBAN, B

PALAZOTTO, A

机构：

[1] US Air Force Inst of Technology,, Wright-Patterson AFB, OH, USA, US Air Force Inst of Technology, Wright-Patterson AFB, OH, USA

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 1987年 / 24卷 / 04期

关键词：

COMPOSITE STRUCTURES - Structural Analysis;

D O I：

10.2514/3.25923

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An experimental investigation is carried out on the effects of circular delaminations (2, 3, and 4 in. in diameter) considering the buckling of Gr/Ep cylindrical panels. The results indicate a local instability within the delamination area followed by global panel buckling. The phenomenon of local instability (snap-through) varies with the delamination size.

引用

页码：349 / 352

页数：4

共 7 条

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