复合材料层合板疲劳寿命形状参数与门槛值分析方法  

Analysis method of life shape parameter and fatigue threshold of composite laminates

作　　者：李嘉骞 沈海军[2] LI Jiaqian;SHEN Haijun(COMAC Shanghai Aircraft Manufacturing Co.,Ltd, Shanghai 201324, China;School of Aerospace Engineering and Applied Mechanics, Tongji University, Shanghai 200092, China)

机构地区：[1]中国商飞上海飞机制造有限公司,上海201324 [2]同济大学航空航天与力学学院,上海200092

出　　处：《国防科技大学学报》2021年第3期38-44,共7页Journal of National University of Defense Technology

摘　　要：复合材料性能具有较大的分散性,在表征复合材料疲劳寿命时,必须考虑分散性的影响。以M21C复合材料开孔层合板为研究对象,采用Sendeckyj等效静强度模型和随机变量函数的概率分布方法推导了复合材料层合板疲劳寿命形状参数和剩余强度形状参数的关系,通过试验和统计的方法获得了M21C复合材料开孔层合板的疲劳寿命形状参数和疲劳门槛值,对载荷放大系数以及低载截除水平的确定提供了数据支持。Special consideration must be applied in the analysis of fatigue life of composite materials due to its high scattering in mechanical property.The relationship between fatigue life Weibull shape parameter and residual strength shape parameter of M21C open-hole composite laminates were deduced based on the Sendeckyj equivalent static strength model and probability distribution of functions of random variables.The fatigue life shape parameter and fatigue threshold of M21C open-hole composite laminates were obtained through element tests and statistic analysis,which can provide support for the determination of LEF(load enhancement factor)and truncation levels for low loads of M21C composite material system.

关 键 词：M21C复合材料 疲劳寿命形状参数 载荷放大系数 疲劳门槛值 

分 类 号：TN95[电子电信—信号与信息处理]