锥导乘波构型设计、优化与分析  

Design,optimization and analysis of cone derived waverider

作　　者：许少华[1] 侯中喜[1] 葛爱学[1] 陈小庆[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》2008年第4期448-453,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(10302031)

摘　　要：乘波构型是高超声速飞行器高升阻比气动布局设计的参考外形之一,设计中需要综合考虑升阻比、容积率和容积等要求。在锥导乘波构型参数化设计的基础上,采用工程估算和计算流体力学相结合的方法,通过正交试验设计分析了不同参数对目标影响的敏感性,合理选择设计参数优化区间,应用改进的多目标遗传算法对乘波构型进行了优化设计,针对优化外形开展了气动性能的数值模拟研究,并在高超声速炮风洞中完成了缩比模型的验证性实验。结果表明:优化设计外形具有良好的升阻比,且在一定攻角范围内升阻比较高,数值模拟和实验分析基本吻合。研究结果可为高超声速滑翔式飞行器的设计提供参考。Waverider configuration is an important approach in hypersonic high L/D vehicle＇s design. L/D, volume and volumetric efficiency needed to be considered in the designing process. Based on parameters design of cone derived waverider, engineering estimate method and computational fluid dynamics method were combined and orthogonal experiment was intro-duced to analyze each control parameter sensitivity on the waverider performance. Each parameter optimization scope was choosen. Improved multl-object genetic algorithm was adopted to optimize the waverider. The optimized shape aerodynamic efficiency was studied by numerical simulation. Scaled optimized model was designed. Wind tunnel experiments were conducted at KD-01 hypersonic gun wind tunnel to verify its aerodynamic efficiency. The result showed that the optimized shape had good L/D performance and can maintain high L/D at certain angle of attack. Numerical result agrees well with experiment. The result can be useful in hypersonic glide aircraft aerodynamic design.

关 键 词：乘波构型 优化设计 数值计算 风洞实验 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]