基于CFD/CSD与Kriging插值模型的大展弦比复合材料机翼静气动弹性优化设计  

Static aeroelastic optimization of a high-aspect-ratio composite wing based on CFD/CSD and Kriging model

作　　者：卢文书[1] 王帅培 马元春[1] 

机构地区：[1]中航工业沈阳飞机设计研究所无人机部,沈阳110035 [2]西北工业大学力学与土木建筑学院,西安710129

出　　处：《应用力学学报》2015年第4期581-585,703-704,共5页Chinese Journal of Applied Mechanics

摘　　要：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。An approximation model of a high-aspect-ratio composite wing for the static aeroelastic optimization is established based on the CFD/CSD coupling method and Kriging approximate technology. The static aeroelastic optimization of the wing is performed by using two hybrid optimization algorithms under multi-objective and multi-constraint conditions. Results show that the fitting precision of the approximation model increases with increasing the number of sample point chosen in the experimental design process. The maximum fitting error of the approximation can be less than 1% when the number of sample point equals to 180. Compared to multi-objective genetic and sequential quadratic programming algorithm, the weight after optimization is reduced by 3.7% and the lift-to-drag ratio is increased by 0.13% by using the hybrid optimization algorithm of multi-islandgenetic and sequential quadratic programming under the approximation model. But its optimization speed is lower than the former. Based on the approximation model, the weight of the wing is reduced by 10.36% and the lift-to-drag ratio is increased by 2.04% after optimization by using the hybrid optimization algorithm of multi-island genetic and sequential quadratic programming. By using the approximation model, the running time of the optimization is only the 10.23% of the real finite element simulation optimization without the approximation model. The results demonstrate the feasibility of this method.

关 键 词：大展弦比复合材料机翼 静气动弹性优化 CFD/CSD 近似模型 混合优化算法 

分 类 号：V224[航空宇航科学与技术—飞行器设计]