乘波构型优化设计与实验  

Optimized Design and Experimental Study of Waverider Configuration

作　　者：许少华[1] 侯中喜[1] 陈小庆[1] 夏智勋[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：《国防科技大学学报》2008年第4期1-5,52,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(10302031);国家863基金资助项目(2006AA756050)

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重要参考外形之一,设计中需要综合考虑升阻比、容积率和容积等要求。本文开展了锥导乘波构型的参数化建模设计,采用改进的多目标遗传优化算法,完成了以升阻比、容积率和容积为多目标的乘波构型优化设计;在KD-01高超声速炮风洞中完成了不同攻角缩比模型的气动力实验,并同CFD计算结果进行了比较分析。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 is an important designing reference in the design of hypersonic high L/D vehicle. L/D, volumetric efficiency and volumetric are factors to be considered in the designing process. A parameter design model of cone derived waverider was established in this paper and an improved multi-object Genetic Algorithm was chosen as the optimized algorithm. Lift to Drag ratio, volumetric and volumetric efficiency were chosen as optimized objective functions in the multi-object optimization of the cone derived waverider. The optimized model was designed and experiments of attack state＇s wind tunnel at KD-01 hypersonie gun wind runnel were conducted. The experimem results were compared with those of CFD. It shows that the model has good IJD performance and can maintain high L/D at certain angle of attack＇ s scope. The CFD results and experiment results are almost identical. The research result is helpful for the hypersonic glide aircraft＇ s 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]