INTERLAMINAR STRESSES IN GENERAL LAMINATES WITH STRAIGHT FREE EDGES

被引：22
|
作者：
LIN, CC [1 ]
HSU, CY [1 ]
KO, CC [1 ]
机构：
[1] AERONAUT RES LAB,TAICHUNG 407,TAIWAN
来源：
AIAA JOURNAL | 1995年 / 33卷 / 08期
关键词：
D O I：
10.2514/3.12569
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
An efficient analytical method for calculating interlaminar stress distribution near the straight free edges of generally stacked laminates under different types of loading conditions is presented. The variation of stresses for each ply are established according to boundary-layer equilibrium equations. All traction boundary conditions at free edges and traction continuity at ply interfaces are satisfied. Although the emphasis is placed on assessing the behavioral characteristics of interlaminar stresses for unsymmetric laminates, numerical examples for symmetric cases are also presented and compared with available data for demonstrating the efficiency and accuracy of this method. All results show high-stress gradients of interlaminar normal and shear stresses near the free edge.
引用
收藏
页码：1471 / 1476
页数：6
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