航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
5期
46-48
,共3页
有限元%动力学模型修正%振动测试%焊接
有限元%動力學模型脩正%振動測試%銲接
유한원%동역학모형수정%진동측시%한접
finite element method%dynamic model update%vibration analysis%welding structure
以焊接薄板动力学模型修正为目的,通过建立参数法修正模型,对含焊缝悬臂薄板动力学模型进行了修正。将焊缝用连续实体单元建模,焊缝部位的密度和弹性模量作为修正变量,以有限元数值解与模态振动测试结果误差最小化为优化目标,通过数值迭代运算,得到了模型修正参数的最优化解。结果证明模型修正精度较高,可有效降低焊接结构件有限元模型复杂度。
以銲接薄闆動力學模型脩正為目的,通過建立參數法脩正模型,對含銲縫懸臂薄闆動力學模型進行瞭脩正。將銲縫用連續實體單元建模,銲縫部位的密度和彈性模量作為脩正變量,以有限元數值解與模態振動測試結果誤差最小化為優化目標,通過數值迭代運算,得到瞭模型脩正參數的最優化解。結果證明模型脩正精度較高,可有效降低銲接結構件有限元模型複雜度。
이한접박판동역학모형수정위목적,통과건립삼수법수정모형,대함한봉현비박판동역학모형진행료수정。장한봉용련속실체단원건모,한봉부위적밀도화탄성모량작위수정변량,이유한원수치해여모태진동측시결과오차최소화위우화목표,통과수치질대운산,득도료모형수정삼수적최우화해。결과증명모형수정정도교고,가유효강저한접결구건유한원모형복잡도。
For the purpose of update of the dynamic model of the welding thin plate ,a dynamic model up-date technique is carried out ,which is based on the modal analysis test result about a thin welding canti-lever plate.The weld joint is modeled with continuous solid element and two variables are introduced:density and elasticity modulus parameters of material , an optimizing model is constructed for the model update question ,and solved by iterative algorithm .The optimal solution includes material density and e-lasticity modulus of the weld area .The technique is proved to be convenient and effective;the study is valuable for the issue of the dynamic model update of the welding structure in application and reduces the complex of modeling .