摘要
基于损伤力学理论,引入一种分式形式的损伤演化方程,研究飞机带板连接件的疲劳寿命预测方法。根据材料手册中的标准试件疲劳试验数据,确定损伤演化方程中的参数。利用有限元软件Ansys分析得到带板连接件的应力分布。通过几种典型载荷情况下的应力计算,揭示外载荷与钉孔边危险点应力呈线性的特性,从而很方便地根据载荷谱得到危险点应力谱,并进行塑性修正。最后分别利用损伤力学闭合解法和数值解法得到谱载荷作用下带板连接件的疲劳寿命。
Based on damage mechanics theory,a damage evolution equation of fractional form was introduced to study the fatigue life prediction method of the joint plate on a certain aircraft.According to the fatigue test result of standard specimens,parameters in the damage evolution equation were determined.Then,stress distribution of the joint plate was obtained by Ansys finite element software.Results of stress analysis of several typical load situations revealed a linear relationship between load and stress of the dangerous point.Thereby,stress spectrum of the dangerous point was obtained conveniently based on the load spectrum,and appropriate stress plastic amendment was carried.Fatigue life of the joint plate under load spectrum was obtained by closed form solution and numerical solution of damage mechanics,respectively.
出处
《机械强度》
CAS
CSCD
北大核心
2011年第3期443-449,共7页
Journal of Mechanical Strength
关键词
损伤力学
疲劳寿命预估
谱载荷
数值解法
连接件
Damage mechanics
Fatigue life prediction
Spectrum loading
Numerical solution
Joint plate
