摘要
用一类疲劳危险部位的寿命代替全机疲劳寿命的方法,对某型飞机的寿命做了定量分析,并基于考虑材料记忆特性的局部应力应变法,对某型飞机的疲劳危险部位进行了标准谱下的寿命计算,计算结果与试验结果较吻合。最后采用局部应力应变法及修正的Manson-Coffin公式,得到了基于飞参数据载荷谱的某型飞机危险部位的实际寿命,并与基于标准谱的疲劳寿命做了对比,为某型飞机的单机寿命监控奠定了基础。
This paper made a quantitative analysis of life for an airplane based on the method which is using the fatigue life of a class of dangerous parts instead of the whole machine,meanwhile fatigue life of dangerous parts for an airplane has been analyzed quantitatively based on local stress-strain approach which considered the memory characteristic of the material and the calculated results is matching the experimental results.Finally,with the local stress-strain approach and the modified Manson-Coffin formula,the actual fatigue life of dangerous parts for an airplane has been received based on the actual flight data spectrum and life monitoring of individual an airplane has been found according to the results.
出处
《新技术新工艺》
2011年第9期63-66,共4页
New Technology & New Process
