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用ANSYS三维实体单元SOLID45建立机翼基准有限元模型并计算其自由振动的前6阶模态频率.用均匀设计方法将结构参数分组并分别计算各组结构参数对应的模态频率,建立高斯径向基函数响应面模型.用最小二乘法则拟合系数并检验响应面拟合精度,对基准模型的结构参数施加摄动量建立待修正有限元模型.用响应面模型和基准模型计算所得模态频率的相对误差建立适应度函数的表达式,将混沌搜索机制引入粒子群算法对结构参数的摄动量进行寻优计算,搜索所得优化解代入即得修正后模型,将修正后模型与基准模型在测试频段内段外的模态频率近似度进行比较,证实了修正后模型的有效性.
The finite element model of the wing was built with ANSYS three-dimensional solid element SOLID45 and the first 6 modes of free vibration were calculated.The structural parameters were grouped by uniform design method and the modal frequencies corresponding to the structural parameters of each group were calculated respectively to establish the Gaussian path Response surface model to the basis function. Fitting coefficient using the least squares method and testing the fitting accuracy of the response surface, the perturbation to the structural parameters of the reference model to establish the finite element model to be amended. Using the response surface model and the reference model to calculate the resulting modal The relative error of frequency is used to establish the expression of fitness function. The chaos search mechanism is introduced into the particle swarm optimization algorithm to optimize the perturbation of structural parameters, and the optimized solution of search is substituted into the corrected model. The corrected model is compared with the reference model in The comparison of modal frequency approximations outside the test frequency band confirms the validity of the modified model.