不同损伤尺寸铝合金结构疲劳寿命分散性研究  

Study on fatigue life dispersion of aluminum alloy structures with different damage sizes

作　　者：李小涛 崔荣洪[1] 李哲[1] LI Xiaotao;CUI Ronghong;LI Zhe(Aviation Engineering School,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]空军工程大学航空工程学院,西安710038

出　　处：《航空工程进展》2023年第5期54-60,共7页Advances in Aeronautical Science and Engineering

摘　　要：飞机损伤结构疲劳寿命分散系数是分析损伤结构疲劳寿命分散程度的重要参数。针对飞机常用铝合金材料,开展预置损伤试验件疲劳测试。采用相关系数比较法,判断损伤结构剩余疲劳寿命分布类型;通过断口观察和数据统计处理,分析损伤与疲劳寿命关系及含损伤结构剩余疲劳寿命分散性规律。结果表明:含损伤结构剩余疲劳寿命更加符合威布尔分布;含预置损伤结构较未预置损伤结构疲劳寿命下降明显,随预置损伤尺寸增加,结构剩余疲劳寿命逐步降低,剩余疲劳寿命分散性增大,不同初始损伤结构疲劳寿命分散性差异较大。本文研究为建立飞机不同损伤尺寸铝合金结构疲劳寿命分散系数模型提供参考依据。Fatigue life scatter factor of damaged aircraft structures is an important parameter to analyze their fatigue life dispersion degree.The fatigue test of prefabricated damage test pieces is carried out for aluminum alloy materials commonly used in aircraft manufacturing.The distribution type of residual fatigue life of damaged structures is determined by correlation coefficient comparison method.The relationship between damage and fatigue life and the dispersion of residual fatigue life of damaged structures are analyzed through fracture observation and statistical data processing.The results show that the residual fatigue life of damaged structures is more subject to Weibull distribu⁃tion.The fatigue life of structures with preset damage decreases significantly than that of structures without preset damage.With the increase of preset damage size,the residual fatigue life of structures gradually decreases,and the residual fatigue life dispersion increases.The fatigue life dispersion difference of structures with different initial damage is great.The present work provides a reference for establishing fatigue life scatter factor models of aluminum alloy structures with different damage sizes.

关 键 词：损伤 疲劳测试 剩余疲劳寿命 威布尔分布 分散性 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]