Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints  

作　　者：Wan Zhiqiang Zhang Bocheng Du Ziliang Yang Chao 

机构地区：[1]School of Aeronautic Science and Engineering, Beihang University [2]Beijing Aeronautical Science & Technology Research Institute of COMAC

出　　处：《Chinese Journal of Aeronautics》2014年第2期259-265,共7页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (No. 11172025 and No. 91116005)

摘　　要：An aeroelastic two-level optimization methodology for preliminary design of wing struc- tures is presented, in which the parameters for structural layout and sizes are taken as design vari- ables in the first-level optimization, and robust constraints in conjunction with conventional aeroelastic constraints are considered in the second-level optimization. A low-order panel method is used for aerodynamic analysis in the first-level optimization, and a high-order panel method is employed in the second-level optimization. It is concluded that the design of the abovementioned structural parameters of a wing can be improved using the present method with high efficiency. An improvement is seen in aeroelastic performance of the wing obtained with the present method when compared to the initial wing. Since these optimized structures are obtained after consideration of aerodynamic and structural uncertainties, they are well suited to encounter these uncertainties when they occur in reality.An aeroelastic two-level optimization methodology for preliminary design of wing struc- tures is presented, in which the parameters for structural layout and sizes are taken as design vari- ables in the first-level optimization, and robust constraints in conjunction with conventional aeroelastic constraints are considered in the second-level optimization. A low-order panel method is used for aerodynamic analysis in the first-level optimization, and a high-order panel method is employed in the second-level optimization. It is concluded that the design of the abovementioned structural parameters of a wing can be improved using the present method with high efficiency. An improvement is seen in aeroelastic performance of the wing obtained with the present method when compared to the initial wing. Since these optimized structures are obtained after consideration of aerodynamic and structural uncertainties, they are well suited to encounter these uncertainties when they occur in reality.

关 键 词：Aeroelasticity Preliminary design Robust optimization Structure optimization UNCERTAINTY 

分 类 号：V224[航空宇航科学与技术—飞行器设计]