Through-thickness connection of matrix cracks in laminate composites for propellant tank

被引：7

作者：

Yokozeki, T ^{[1
]}

Ishikawa, T

Aoki, T

机构：

[1] Japan Aerosp Explorat Agcy, Tokyo 1810015, Japan

[2] Univ Tokyo, Tokyo 1438656, Japan

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2005年 / 42卷 / 04期

关键词：

D O I：

10.2514/1.11173

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Matrix crack accumulation in multiple plies of composite laminates is experimentally investigated to assess the through-thickness connection of matrix cracks, which is closely related to propellant leakage problems of composite tanks. Cracking patterns in [0/theta(2)/90](s) laminates reveal that layup angles have a significant effect on crack induction mechanisms in contiguous plies. Matrix crack propagation behaviors in the fiber direction of 0 ply induced by 90-ply cracks are investigated in terms of energy release rates using parametric-oriented finite element analysis based on an oblique coordinate system. The effect of cryogenic conditions on crack induction in contiguous plies is also studied, and discussions on through-thickness connection of matrix cracks in composite laminates are provided.

引用

页码：647 / 653

页数：7

共 16 条

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