基于参数样条的旋成体局部气动外形优化设计  

Local Aerodynamic Shape Optimum Design for Axisymmetric Nose Based on Cubic Spline

作　　者：王唯[1] 陈志华[1] 

机构地区：[1]南京理工大学瞬态物理重点实验室,南京210094

出　　处：《弹箭与制导学报》2011年第3期177-179,共3页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：重点实验室基金;教育部博士点基金(20093219120047);南京理工大学科技发展基金(XKF09061)资助

摘　　要：基于高超音速空气动力学的特点,使用未经修正的牛顿正弦平方律完成了给定攻角条件下旋成体的气动力建模。运用三次参数样条拟合旋成体母线,获得了以型值点表示的母线方程,建立了型值点与气动特性之间的关系。最后以最小化气动阻力为优化目标,求解KKT方程,完成了旋成体气动外形的最优设计。Focused on the characteristic of hypersonic aerodynamic, an approximately model was developed and applied to study nose local aerodynamic shape design based on Newton sine-squared method. The generatrix of nose was fit by cubic spline and the relationship between the reference points and the aerodynamic was figured out. An optimum solution was presented to achieve the goal of minimize parameter Cx by solve Karush-Kuhn-Tucker function. A contrast between the optimum solution and commonly solution indicated that the method can approach the goal effectively.

关 键 词：优化方法 气动外形 样条曲线 

分 类 号：TJ012.3[兵器科学与技术—兵器发射理论与技术]