摘要
精确分析和预测连接耳片结构的疲劳寿命对保证飞机安全具有重要意义。采用损伤力学—有限元全耦合方法对飞机上典型连接耳片结构进行分析,得到该结构的疲劳损伤演化过程和疲劳寿命;将分析结果与疲劳寿命工程估算方法——名义应力法进行比较,证明损伤力学—有限元全耦合方法应用于结构寿命预测的可行性,并将损伤力学—有限元全耦合方法与线性Miner准则、损伤全解耦方法进行对比分析。结果表明:损伤力学有限元全耦合方法,其计算结果是唯一的、确定的,比运用线性Miner准则和损伤全解耦方法所得的结果更准确,弥补了名义应力法的不足。
Accurate analysis and forecast fatigue life of the lug are of important significance to guarantee the safety of plane.The damage mechanics-finite element full-couple method is used to analyze the lug,that is a typical connection structure in plane,and the process of fatigue damage evolution and fatigue life are obtained.Then the results are compared with the fatigue life calculated by engineering estimation method-nominal stress method,and the feasibility that damage mechanics full couple method is applied to structure life prediction is confirmed.Finally,the method is compared with the linear Miner criterion and damage decoupling method.The comparison results show that the result calculated by damage mechanics-finite element full-couple method is unique and determined,and more accurate than the results by linear Miner criterion and damage decoupling method.It can be a complement of the nominal stress method.
出处
《航空工程进展》
2013年第1期54-59,共6页
Advances in Aeronautical Science and Engineering
关键词
损伤力学
全耦合
有限元
疲劳损伤累积
疲劳寿命
名义应力法
damage mechanics
full-couple
finite element
fatigue damage accumulation
fatigue life
nominal stress method
