摘要
利用飞机铆接试验件疲劳试验数据,结合损伤力学与有限元方法,通过MATLAB调用ABAQUS进行损伤演化方程参数的遗传优化反演。将反演得到的损伤演化方程用于飞机结构疲劳寿命预估中,对机翼蒙皮锪窝形式的铆接结构进行了寿命计算和分析,并与试验数据作对比,证明了方法的可行性。
Based on the fatigue test data of aircraft riveted structure test pieces ,the inversion of parameters in a damage evolution equation is done withthe damage mechanics-finite element method by MATLAB and ABAQUS .Then this equation is applied to estimate the fatigue life of aircraft structures ,and do the calculation as well as the analysis of lifespan of the countersink riveted structure in wing skins .Numerical results showthat this method is effective .
出处
《航空计算技术》
2014年第3期66-68,72,共4页
Aeronautical Computing Technique
关键词
损伤力学
有限元方法
损伤演化
参数反演
铆接结构
damage mechanics
finite element method
damage evolution
inversion of parameters
riveted structure
