SNAP BUCKLING OF DELAMINATED COMPOSITES UNDER PURE BENDING

被引：18

作者：

KARDOMATEAS, GA

机构：

[1] School of Aerospace Engineering, Georgia Institute of Technology, Atlanta

来源：

COMPOSITES SCIENCE AND TECHNOLOGY | 1990年 / 39卷 / 01期

关键词：

D O I：

10.1016/0266-3538(90)90033-2

中图分类号：

TB33 [复合材料];

学科分类号：

摘要：

Delaminated composites under pure bending can undergo snap buckling under certain conditions of applied bending load and geometrical configuration. The phenomenon is demonstrated experimentally and is investigated theoretically by an energy procedure. The geometric non-linearities are included in the formulation. First, a theoretical analysis is performed to model the behavior of the system and define the conditions for snap buckling. The predicted buckling loads are then compared with experimentally obtained data from pure bending loading of Kevlar epoxy specimens with internal delaminations. Good agreement is obtained between the experimental and theoretical results. © 1990.

引用

页码：63 / 74

页数：12

共 15 条

[1]

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[2]

BRITVEK SJ, 1973, STABILITY ELASTIC SY

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