航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
3期
66-68,72
,共4页
损伤力学%有限元方法%损伤演化%参数反演%铆接结构
損傷力學%有限元方法%損傷縯化%參數反縯%鉚接結構
손상역학%유한원방법%손상연화%삼수반연%류접결구
damage mechanics%finite element method%damage evolution%inversion of parameters%riveted structure
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。
利用飛機鉚接試驗件疲勞試驗數據,結閤損傷力學與有限元方法,通過MATLAB調用ABAQUS進行損傷縯化方程參數的遺傳優化反縯。將反縯得到的損傷縯化方程用于飛機結構疲勞壽命預估中,對機翼矇皮锪窩形式的鉚接結構進行瞭壽命計算和分析,併與試驗數據作對比,證明瞭方法的可行性。
이용비궤류접시험건피로시험수거,결합손상역학여유한원방법,통과MATLAB조용ABAQUS진행손상연화방정삼수적유전우화반연。장반연득도적손상연화방정용우비궤결구피로수명예고중,대궤익몽피홀와형식적류접결구진행료수명계산화분석,병여시험수거작대비,증명료방법적가행성。
Based on the fatigue test data of aircraft riveted structure test pieces ,the inversion of parame-ters in a damage evolution equation is done withthe damage mechanics-finite element method by MAT-LAB 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 .Nu-merical results showthat this method is effective .