典型飞机结构腐蚀损伤模拟件修理前后疲劳寿命研究

摘要

The fatigue life of the simulative components for typical aircraft corrosion failure key structures before and after overhaul was thoroughly investigated using the accelerated corrosion test and fatigue test combination methods. The results showed that compared with the original simulative components, the mean fatigue life and the lower one-sided 95 percent confidence limit of the corroded ones before and after overhaul decrease 16. 9%, 47. 4% and 21. 4%, 28. 9%, respectively. The fatigue life dispersivity of the corroded simulative components is obviously higher than that of the original ones, but it is distinctly improved after overhaul.%采用加速腐蚀试验与疲劳试验相结合的方法,对典型飞机腐蚀失效关键结构模拟件腐蚀修理前后的疲劳寿命进行了研究.结果表明,与未腐蚀状态相比,含腐蚀损伤模拟件的疲劳寿命均值和95％置信度下的单侧置信下限分别降低16.9％和47.4％,经过腐蚀修理后其疲劳寿命均值和95％置信度下限的单侧置信分别下降21.4％和28.9％.含腐蚀损伤模拟件的疲劳寿命分散性显著增大,但经过修理后疲劳寿命分散性得到明显改善.