飞机结构关键件设计改进后的疲劳寿命评定技术

 结合某型飞机重要疲劳关键件起落架梁设计改进后的寿命评定，建立了在不进行全尺寸试验的情况下，对设计改进结构进行寿命评定的方法。即在结构改进前后关键疲劳薄弱部位细节应力分析的基础上，通过该疲劳关键部位的模拟试件在改进前后应力谱下的寿命分析和疲劳对比试验，综合评定结构改进后的寿命增加系数，参照改进前该结构的全尺寸疲劳试验结果，确定设计改进后该关键件的疲劳寿命。用上述方法完成了对某型飞机重要疲劳关键件起落架梁改进后的寿命评定，其结果也应用到了该型飞机结构的定延寿。

Technique about Evaluating the Fatigue Life of the Improved Main Components in Aircraft

This paper takes example for evaluating the life of the improved undercarriage b eam which is a main fatigue component in a kind of plane, and describes the meth od about evaluating the fatigue life of the improved components in the case of l ack of whole size testing. This method bases on the detail stress analysis of th e main fatigue parts between the improved component and the unimproved component , and evaluates synthetically the coefficient of life increase of the improved c omponent by analyzing the life of the simulator specimen of this component in th e case of each load spectrum and the fatigue compare testing, and ascertains the fatigue life of this improved main component by consulting the result of the wh ole size testing about this unimproved component. The life evaluating of the und ercarriage beam which is a main fatigue component in a kind of plane is complete d by this method. The result was applied to this kind of plane.