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基于CFD/CSD耦合计算方法和Kriging近似技术,建立了大展弦比复合材料机翼静气动弹性优化的近似模型。采用多岛遗传和序列二次规划混合优化算法以及多目标遗传和序列二次规划混合优化算法实现了机翼在多目标、多约束条件下的静气动弹性优化设计。优化结果表明:随着试验设计中抽样点个数的增加,近似模型的拟合精度越来越高,当设计样本点数为180时近似模型的最大拟合误差小于1%;在近似模型下,相对于多目标遗传和序列二次规划混合优化算法,采用多岛遗传和序列二次规划的混合优化算法优化时得到的重量小3.7%,升阻比大0.13%,但是寻优速度不如前者;结合近似模型,采用多岛遗传和序列二次规划的混合优化算法优化后机翼的重量减小了10.36%,升阻比增加了2.04%,采用近似模型优化时运行时间仅为不采用近似模型优化的10.23%,证明了该优化方法的可行性。
Based on CFD / CSD coupling calculation and Kriging approximation, an approximate model of static aerodynamic elasticity of a large aspect ratio composite wing is established. The multi-objective and multi-constrained optimization of the static-dynamic aerodynamic flexibility of the wing is achieved by using the multi-island genetic and sequence quadratic programming hybrid optimization algorithm and the multi-objective genetic and sequence quadratic programming hybrid optimization algorithm. The optimization results show that the fitting accuracy of the approximate model is getting higher and higher as the number of sampling points in the experimental design increases, and the maximum fitting error of the approximate model is less than 1% when the design sample points are 180. In the approximate model, Compared with multi-objective genetic and sequence quadratic programming hybrid optimization algorithm, the hybrid optimization algorithm using multi-island genetic and sequence quadratic programming has a small weight of 3.7% and a large lift-to-drag ratio of 0.13%, but the optimization speed is not as good as the former. Combining with the approximate model, the hybrid wing optimization algorithm with multi-island genetic algorithm and sequential quadratic programming method reduced the weight of the wing by 10.36% and increased the drag / drag ratio by 2.04%. The running time of the approximate model was only that the approximate model was not adopted The optimization of 10.23%, proved that the optimization method is feasible.