吻切锥乘波构型参数化设计与正交试验分析  

Parameterized design and orthogonal experiment analysis of osculating-cone waverider

作　　者：陈小庆[1] 侯中喜[1] 何烈堂[1] 李健[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2010年第4期385-389,400,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(10302031)

摘　　要：为了获得外形控制参数对吻切锥乘波构型性能的影响程度,通过分析吻切锥乘波构型的生成特点和生成方法,在其参数化设计的基础上,运用正交试验设计方法分析了各个控制参数乘波构型性能的影响,确定了对气动性能和容积率影响较大的参数,为进一步合理确定优化空间和优化策略提供指导。运用CFD方法对典型外形进行了性能分析,结果显示:吻切锥乘波构型具有较高升阻比,下表面中心区流动均匀,可为高超声速飞行器机身/进气道一体化提供参考。作为应用,基于正交试验结果设计了以吻切锥乘波构型作为前体的一个高超声速飞行器,验证了设计方法的合理性。To obtain the shape parameter effect on the aerodynamic performance of osculating cone（OC） waverider,based on the study of OC waverider characteristics and generation method,the design process was parameterized and orthogonal experiment was introduced to analyze each control parameter effect on the performance of OC waverider.The parameters that greatly influence OC waverider performance were determined,which can be used to determine the optimized design space and optimization strategy appropriately.CFD tool is used to analyze the aerodynamic performance of waverider configuration.Results show that the configuration can offer not only high L/D ratio but also the uniform flow field at the lower surface which can be used in the design of airframe/engine integration.As an example,an air-breathing,OC waverider based hypersonic vehicle was designed to illustrate the rationality of design method.

关 键 词：吻切锥乘波构型 机身/进气道一体化 数值仿真 正交试验设计 

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]