计算力学学报2012，Vol.29Issue(2)：284-289,6.
基于离散共轭方法的高超声速导弹气动外形优化设计
Aerodynamic configuration optimization design of hypersonic missile based on discrete adjoint method
摘要
Abstract
This paper studied the aerodynamic configuration optimization design of hypersonic missile.The NURBS parameterization method was constructed,and an efficient and simple moving grid method was completed.Discrete adjoint method based on Euler equations was built.All these methods along with optimization method were integrated into an aerodynamic optimization system that can process complex hypersonic configuration.The forebody of a missile was optimized,and the lift to drag ratio is increased by 11.2 percent.The shape of the optimized forebody is very close to that of double cone,and this shows that a double cone forebody helps to reduce the drag.Experiment shows that discrete adjoint method has very promising prospects in optimization design of hypersonic configuration.关键词
离散共轭/复杂外形/优化设计/高超声速/双锥Key words
discrete adjoint/complex configuration/optimization design/hypersonic/double cone分类
航空航天引用本文复制引用
左英桃,苏伟,高正红,黄礼铿..基于离散共轭方法的高超声速导弹气动外形优化设计[J].计算力学学报,2012,29(2):284-289,6.基金项目
西北工业大学科技创新基金资助 （）
