基于三维CST建模方法的两层气动外形优化策略  

Two-level aerodynamic shape optimization strategy based on three-dimensional CST modeling method

作　　者：粟华[1] 龚春林[1] 谷良贤[1] 

机构地区：[1]西北工业大学航天飞行动力学技术重点实验室,西安710072

出　　处：《固体火箭技术》2014年第1期1-6,22,共7页Journal of Solid Rocket Technology

基　　金：武器装备预研基金(9140A20100111HK0318);西北工业大学基础研究基金(JC20120215)

摘　　要：针对复杂构型飞行器气动外形优化的几何描述和计算效率问题,提出了一种基于通用三维类别/形状函数变换参数化方法的两层设计空间气动外形优化策略。采用B样条函数代替Bernstein多项式进行展开并引入侧向轮廓描述函数,将原二维类别/形状函数向三维扩展,基于部件组合设计思想,建立了三维飞行器几何外形的完整描述形式。结合类别/形状函数和B样条函数的参数化特点,引入设计空间分层优化思想,将设计参数划分为全局尺寸参数和局部调整参数,在减少优化时间的同时尽可能地保持原设计空间复杂度。采用X-33高超声速飞行器作为建模和优化算例,结果表明,三维CST方法能以较少设计参数表达复杂外形,具有基础参数少,设计复杂度可调,外形表达能力强,参数化过程稳定的优势;两层气动外形优化策略具有良好的设计空间搜索能力,并可显著降低计算消耗。A new twolevel aerodynamic shape optimization structure using a universal threedimensional class shape transfor mation（CST） parameterization technology was presented for the geometry modeling and computational efficiency problem of complex configuration aircraft aerodynamic shape optimization.The original twodimensional CST method was expanded to threedimensions using Bspline instead of Berustein polynomial and lateral profile function, and a full threedimensional aircraft geometrical shape description forms was given basedon components buildup technology.According to the characteristics of class function/shape func tion and Bspline, a twolevel design space aerodynamic shape optimization method was introduced by dividing the design variable into global sizing parameter and local adjust parameter, which can save optimization time while keeping the original design space complexity as much as possible.The X33 hypersonic aircraft optimization result shows that this method has advantages of less basal design variable, adjustable design variable, high geometrical shape expression ability and stable parametric process, and the twolevel design space aerodynamic shape optimization method has the abilities of excellent design space exploration and high computational efficiency.

关 键 词：气动外形优化 参数化 类别函数/形状函数 两层优化 B样条 部件组合 

分 类 号：V421[航空宇航科学与技术—飞行器设计]