ANALYSIS OF DELAMINATION INITIATION IN POSTBUCKLED DROPPED-PLY LAMINATES

被引:52
作者
DAVILA, CG [1 ]
JOHNSON, ER [1 ]
机构
[1] VIRGINIA POLYTECH INST & STATE UNIV,DEPT AEROSP & OCEAN ENGN,BLACKSBURG,VA 24061
关键词
Aircraft materials - Compression testing - Finite element method - Graphite fibers - Plastic laminates;
D O I
10.2514/3.49019
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The compression strength of dropped-ply, graphite-epoxy laminated plates for the delamination mode of failure is studied by a finite element analysis and corroborated with experiments. The compression strength of the 2.54-cm-wide specimens, which exhibited a linear response to delamination initiation, is greater than the compression strength of the 7.62-cm-wide specimens with the same layup, which exhibited a nonlinear response to delamination. Analyses confirm that the influence of the geometric nonlinearity on the response of the 2.54-cm-wide dropped-ply laminate is insignificant, but this nonlinearity is very significant in the response of its 7.62-cm-wide counterpart. For the 7.62-cm-wide dropped-ply laminate, the decrease in compression strength is associated with the redistribution and intensification of the severe interlaminar stress gradients occurring at the dropoff to a location closer to the knife-edge support.
引用
收藏
页码:721 / 727
页数:7
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