基于响应面法的机翼气动/结构一体化优化设计研究  

Research of aerodynamic-structure integrative optimization design of wing based on response surface methodology

作　　者：刘金辉[1] 乔志德[1] 杨旭东[1] 郝国芬[2] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室 [2]河北工程技术高等专科学校计算中心,河北沧州061001

出　　处：《空气动力学学报》2006年第3期300-306,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(10402036);航空科学基金资助项目(04A53005)

摘　　要：基于响应面法进行了机翼气动/结构一体化优化设计研究,流动控制方程为三维欧拉方程,采用有限体积法进行数值求解,应力和结构变形采用有限元方法计算,静气动弹性分析采用强耦合迭代方式,响应面模型采用二次多项式来构造。以跨音速M6机翼为初始机翼,进行了多目标、多约束情形下的气动/结构综合优化设计,优化后所得到的新机翼具有更佳的气动/结构综合性能,升阻比增加了9.25%,而重量减轻了4.84%;响应面模型精度满足设计要求,拟合误差均不超过1%;这说明本文所发展气动/结构综合优化设计方法是成功且有效的,具有广泛的应用前景。In this paper , the method of aerodynamic-structure integrative optimization design of wing based on the Response Surface Methodology（RSM） is proposed. The governing equation is 3D Euler equations, which is solved by the finite volume method. The stress and the structural deformation is calculated by Finite Element Method（FEM） and the aeroelastic analysis is performed by Tight Coupling Method（TCM）. The quadratic polynomials are employed to construct response surface model. M6 transonic wing is choosed as the base wing. Aerodynamic -structure integrative optimization design under multi-objective is performed. The results show that lift-to-drag ratio was increased 9.25 % and structural weight was reduced 4.84 %. The fitting error of response surface was less than 1%, which show that RSM was accurate enough to satisfy the engineering requirement. It can be concluded that the present method is effective and feasible, and is very attractive for muhidisciplinary optimization design due to its high design capability.

关 键 词：响应面法 欧拉方程 有限元方法 静气动弹性 多目标优化设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]