Abstract
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.
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