Behavior of compression-loaded composite panels with stringer terminations and impact damage

被引：2

作者：

Jegley, DC ^{[1
]}

机构：

[1] NASA, Langley Res Ctr, Struct Mech Branch, Struct Div, Hampton, VA 23681 USA

来源：

JOURNAL OF AIRCRAFT | 1998年 / 35卷 / 06期

关键词：

D O I：

10.2514/2.2390

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The results of an analytical and experimental study of graphite-epoxy stiffened panels with impact-damaged stringer terminations are presented. Five stitched graphite-epoxy panels with stiffeners with a gradual reduction in either thickness or height were examined. Panels were analyzed using finite element analysis and tested by loading them in axial compression to a predetermined load. The panels were then subjected to impact damage and loaded to failure. Axial midplane strains, surface strains, interlaminar strains, and failure results are discussed.

引用

页码：942 / 948

页数：7