飞机结构部件疲劳寿命预测技术研究  

Fatigue life prediction research on aeroplane structures component

作　　者：崔建国[1,2] 赵朋元[1] 董世良[2] 刘利秋[1] 石鹏[2] 谭峰[2] 

机构地区：[1]沈阳航空航天大学自动化学院,辽宁沈阳110136 [2]沈阳飞机设计研究所,辽宁沈阳110135

出　　处：《沈阳航空航天大学学报》2011年第3期43-47,共5页Journal of Shenyang Aerospace University

基　　金：航空科学基金(项目编号:2010ZD54012);辽宁省教育厅科研基金(项目编号:2008544);国防基础科研计划项目(项目编号:A0520110023)

摘　　要：为解决飞机结构部件疲劳寿命有效预测的难题,以实现视情维修,提升飞机的安全性与可靠性,本文以某型军用飞机某一关键结构部件———水平尾翼为具体研究对象,对其进行疲劳寿命预测技术研究。采用飞机结构疲劳寿命专用试验平台,对飞机水平尾翼进行长期疲劳寿命试验,得到疲劳寿命真实试验数据,运用模糊相关理论及强化函数,建立混合疲劳寿命预测模型,应用此模型对飞机水平尾翼疲劳寿命进行预测研究。试验结果表明,所设计的模型预测准确性较传统M iner模型有了很大提高,具有很好的工程实用价值。Accurate prediction of fatigue life for aeroplane structures is a difficult problem.For condition-based maintenance and improve the aeroplane security and reliability,it is important that the fatigue life prediction research is done in the aeroplane structures.In the paper,the specific object of fatigue life prediction technology research is the pivotal aeroplane structural compo-nent-aeroplane stabilizer.With the true data of fatigue life experiment which results from the long-term fatigue tests on the special test platform for aeroplane structures fatigue,applying the fuzzy theory and fortified function,a mixed fatigue life predic-tion model is established based on membership function.The model is then used to predict the aeroplane structure fatigue life.The experiment shows that this model could effectively predict the aeroplane structure fatigue life.It decreases the prediction error of the traditional model to a certain degree.Therefore,it has a perfect engineering value.

关 键 词：疲劳寿命 模糊理论 混合模型 水平尾翼 寿命预测 

分 类 号：V215.52[航空宇航科学与技术—航空宇航推进理论与工程]