基于应力场强方法的多轴高周疲劳寿命分析及应用  

The prediction of mutiaxial high cycle fatigue based on stress field intensity

作　　者：王明春[1] 宋恩鹏[1] 赵清华[1] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2015年第4期10-13,共4页Aircraft Design

基　　金：中国人民解放军总装备部项目(402060104)

摘　　要：在多轴高周疲劳临界面的基础上,将应力场强方法计算的某一临界尺度内的平均应力作为控制疲劳损伤的特征应力,进而建立一种新的基于应力场强的多轴高周疲劳寿命估算方法,结合某型飞机中央翼1墙法兰盘部位全机疲劳试验,将该方法计算结果与名义应力法、McDiarmid法、Susmel法及全机疲劳试验结果进行比较,结果表明,该方法可以较好地预测多轴高周疲劳寿命。On the basis of the multiaxial high cycle fatigue critical plane,the average stress in a critical scale calculated by the method of stress field intensity is used as the characteristic stress for fatigue damage control,and then a new life assessment method of multiaxial high cycle fatigue based on stress field intensity is established.To the full scale fatigue test of the flange on the wall of central fuselage of a certain aircraft,results calculated by the new method are compared with the results calculated by methods of nominal stress method,McDiarmid method,Susmel method and the results of full scale fatigue test.The comparative result shows that this new method can primely predictive life of multiaxial high cycle fatigue.

关 键 词：应力场强法 临界距离法 临界面 多轴疲劳 疲劳寿命 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]