PREDICTION OF LOW-VELOCITY IMPACT DAMAGE IN THIN CIRCULAR LAMINATES

被引：110

作者：

SHIVAKUMAR, KN ^{[1
]}

ELBER, W ^{[1
]}

ILLG, W ^{[1
]}

机构：

[1] NASA,LANGLEY RES CTR,FATIGUE & FRACTURE BRANCH,HAMPTON,VA 23665

来源：

AIAA JOURNAL | 1985年 / 23卷 / 03期

关键词：

COMPOSITE MATERIALS - Failure - LAMINATED PRODUCTS - MATERIALS TESTING - Impact - PLASTICS; REINFORCED - Structural Analysis;

D O I：

10.2514/3.8933

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Clamped circular composite plates made of quasi-isotropic graphite/epoxy laminate were analyzed for static equivalent impact loads. The analysis was based on the minimum total potential energy method and used the von Karman strain-displacement equations. A step-by-step incremental transverse displacement procedure was used to calculate plate load and ply stresses. The ply failure region and modes (splitting and fiber break) were calculated using the Tsai-Wu and the maximum stress criteria, respectively. Reduced moduli were then used in the failed region in subsequent increments of analyses. The analysis predicted that the failure would initiate as splitting in the bottom-most ply and then progress to other plies.

引用

页码：442 / 449

页数：8