带划痕缺陷的碳纤维增强树脂复合材料疲劳寿命研究  

Fatigue Life Research on Carbon Fiber Enforced Resin Composites with Notch Defects

作　　者：张学薇 汪振兴 吴堂珍[1] 龚明程 ZHANG Xuewei;WANG Zhenxing;WU Tangzhen;GONG Mingcheng(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2023年第1期41-46,61,共7页Helicopter Technique

摘　　要：针对带有划痕的3238A/CF3052碳纤维复合材料,从试验和计算角度分别探究其疲劳剩余强度性能,并预测疲劳寿命。考虑材料组分、划痕深度、应力比等因素的影响,同时将缺陷尺寸效应引入模型,建立含缺陷尺寸效应的疲劳寿命理论。通过试验结果与模拟结果的对比,验证了理论的有效性,并分析材料的疲劳寿命规律。利用有限元软件对有划痕材料进行模拟,得到材料应力分布,并进一步计算寿命曲线,结果与试验结果一致,表明能够有效预测材料疲劳寿命。A numerical and experimental study of the notch effect on strength and fatigue life of the carbon fiber composite 3238A/CF3052 was presented.Considering fiber component,notch depth and stress ratio,the fatigue life theory with defect size effect were proposed.The validity of the theory was verified by the comparison of experimental and calculation results,and the fatigue life of the composite was analyzed and discussed.Simulation was also applied to obtain the stress distribution of notched materials,and further the fatigue life curve.The simulation results were consistent with the experimental results,indicating that the fatigue life of defected material could be effectively predicted.

关 键 词：复合材料 划痕缺陷 疲劳寿命 剩余强度 尺寸效应 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] V215.5