Fatigue Delamination Crack Growth in GFRP Composite Laminates: Mathematical Modelling and FE Simulation

被引：3

作者：

Ijaz, Hassan ^{[1
]}

Saleem, Waqas ^{[1
]}

Zain-ul-Abdein, Muhammad ^{[1
]}

Taimoor, Aqeel Ahmad ^{[2
]}

Bin Mahfouz, Abdullah Salmeen ^{[3
]}

机构：

[1] Univ Jeddah, Dept Mech Engn, Jeddah, Saudi Arabia

[2] King Abdulaziz Univ, Dept Chem & Mat Engn, Jeddah, Saudi Arabia

[3] Univ Jeddah, Dept Chem & Mat Engn, Jeddah, Saudi Arabia

来源：

INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | 2018年 / 2018卷

关键词：

INTERFACE MODELS; DAMAGE; FRACTURE; IDENTIFICATION;

D O I：

10.1155/2018/2081785

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Glass fibre-reinforced plastic (GFRP) composite laminates are used in many industries due to their excellent mechanical and thermal properties. However, these materials are prone to the initiation and propagation of delamination crack growth between different plies forming the laminate. The crack propagation may ultimately result in the failure of GFRP laminates as structural parts. In this research, a comprehensive mathematical model is presented to study the delamination crack growth in GFRP composite laminates under fatigue loading. A classical static damage model proposed by Allix and Ladeveze is modified as a fatigue damage model. Subsequently, the model is implemented in commercial finite element software via UMAT subroutine. The results obtained by the finite element simulations verify the experimental findings of Kenane and Benzeggagh for the fatigue crack growth in GFRP composite laminates.

引用

页数：8

共 30 条

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