应用局部应力应变法预测机匣疲劳寿命  

CYLINDRICAL CASE FATIGUE LIFE PREDICTION BY LOCAL STRAIN APPROACH

作　　者：尚伟钧[1] 廖学军[1] 许棠[1] 

机构地区：[1]南京航空学院

出　　处：《航空动力学报》1991年第1期41-45,共5页Journal of Aerospace Power

摘　　要：本文在用有限元对带孔圆筒机匣进行了弹塑性分析的基础上 ,设计了带孔薄板等效模拟试件 ,试图作为取代圆筒机匣低循环疲劳寿命预测和试验的等效模拟构件 ,为此对带孔圆筒机匣与带孔薄板等效模拟试件同时进行了低循环疲劳寿命预测和试验 ,取得了满意的结果。通过对上述结果分析对比 ,找出了设计真实构件的等效模拟试件准则 ,为今后复杂构件的低循环疲劳寿命预测 ,设计等效模拟试件提供了依据。A finite element elastic-plastic stress-strain analysis is completed for the cylindrical case with a hole.According to the stress-strain analysis the equivalent simulation members of thin plate with holes are designed to replace the cylindrical case in the fatigue life predictions and tests.The low cycle fatigue life predictions and tests have been accomplished with the local strain approach for the cylindrical cases and the equivalent simulation members.The results prove that the equivalent simulation is feasible.Finally the design criterion of the equivalent simulation members is found out.Therefore this work provides a basis for designing equivalent simulation members to replace the complex members in the low cycle fatigue life predictions and tests.

关 键 词：机匣 疲劳寿命 应力应变法 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]