摘要
为研究拉伸载荷下碳纤维/环氧树脂层合板的疲劳性能,开展了4种应力水平下的T300/6511碳纤维平纹织物层合板的拉-拉疲劳实验,得到了不同应力水平下层合板的疲劳寿命。采用超声波C扫和扫描电子显微镜(SEM)观察断口形貌及内部损伤,讨论复合材料疲劳损伤发展积累过程和断裂机理。通过复合材料疲劳有限元分析模型,模拟了复合材料织物层合板疲劳损伤积累和失效过程,绘制了S-lg N曲线,分析发现模型预测的疲劳寿命及失效模式与实验结果吻合良好。疲劳加载时,层合板两侧自由边的表面首先出现基体开裂和分层损伤,随后诱发基体与纤维间界面破坏,损伤加剧,并迅速向内侧扩展;最后大量纤维和基体断裂,损伤贯穿整个截面,导致疲劳断裂。
In order to study the fatigue properties of carbon fiber/epoxy laminates under tensile load,the tensile-tensile fatigue tests of T300/6511 carbon fiber plain woven fabric laminates under four stress levels were carried out.The fatigue damage accumulation and failure process of composite fabric laminates were simulated by using a composite material fatigue finite element analysis model.The S-lgN curve was drawn,and it was found that the fatigue life and failure mode which the model predicted matched well with the experimental results.Under fatigue loading,the surface of the free edges on both sides of the laminates first exhibits matrix cracks and delamination,and then the interface failure between the matrix and fibers induces,which causes the damage exacerbation and rapid expansion towards the inner side.Finally,a large number of fibers and matrix fractures,the damage covers the entire cross-section,which leads to fatigue fracture.
作者
汪莹
李敏
李桃山
刘逸众
聂明明
WANG Ying;LI Min;LI Tao-shan;LIU Yi-zhong;NIE Ming-ming(Airforce Aviation Repair Institute of Technology,Changsha 410124,China;Changsha 5712 Aircraft Industry Co.,Ltd.,Changsha 410113,China)
出处
《塑料科技》
CAS
北大核心
2023年第8期37-42,共6页
Plastics Science and Technology
基金
湖南省自然科学基金科教联合基金项目(2020JJ7078
2020JJ7076)。
关键词
层合板
拉伸疲劳
疲劳损伤
有限元
Laminates
Tensile fatigue
Fatigue damage
Finite element
作者简介
联系人:汪莹,1281825435@qq.com。
