An overview of fatigue models for composite laminate materials

被引：18

作者：

Azinan, Nabilah ^{[1
]}

Halim Kadarman, A. ^{[1
]}

Sidhu, Junior Sarjit Singh ^{[1
]}

机构：

[1] Univ Sains Malaysia, Sch Aerosp Engn, Engn Campus, Nibong Tebal 143005, Pulau Pinang, Malaysia

来源：

MECHANICS OF ADVANCED MATERIALS AND STRUCTURES | 2022年 / 29卷 / 25期

关键词：

Matrix cracking; aircraft structure; stiffness degradation model; composite laminates; delamination; STIFFNESS DEGRADATION MODEL; REINFORCED POLYMER COMPOSITES; RESIDUAL STRENGTH DEGRADATION; IMPACT-DAMAGE DETECTION; THERMOMECHANICAL CONSTITUTIVE THEORY; ELECTRICAL-RESISTANCE CHANGE; LIFE PREDICTION METHODOLOGY; TRANSVERSE MATRIX CRACKING; CARBON-FIBER COMPOSITES; CROSS-PLY LAMINATE;

D O I：

10.1080/15376494.2021.1929591

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

Composite laminate materials are used extensively in various applications particularly in aircraft structures. During operation, the aircraft's structure will experience mechanical responses due to environmental degradation or external damages. This mechanical loading may cause damages to further develop in the composite laminate materials. Thus, numerous attempts from previous researchers to develop theories to investigate the damage that appears in composite laminate materials under loading conditions. Therefore, this review paper presents an overview of theoretical models that have been used to investigate the effects on stiffness due to the damage mechanism in composite laminate materials under fatigue loading conditions specifically.

引用

页码：4389 / 4411

页数：23

共 284 条

[1] In-situ monitoring of damage in CFRP laminates by means of AC and DC measurements [J].