基于响应面方法的高超声速飞行器一体化布局气动设计与优化  

Integrative Aerodynamic Design and Optimization of Hypersonic Vehicle Configurations Based on Response Surface Methodology

作　　者：李晓宇[1] 欧海英[1] 丁国昊[2] 李桦[2] 

机构地区：[1]海军航空工程学院青岛分院,青岛266041 [2]国防科技大学航天与材料工程学院,长沙410073

出　　处：《导弹与航天运载技术》2010年第2期8-11,共4页Missiles and Space Vehicles

摘　　要：建立了高超声速飞行器机体/推进系统一体化三维构型参数化模型,利用CFD数值计算开展了构型气动力的高精度数值试验并以此为基础建立了气动力响应面近似模型,以响应面近似模型作为气动力预测方法,结合遗传算法进行了高超声速飞行器三维构型的气动优化设计,获得了不同优化目标下的优化外形。An integrative 3D characteristic model is built up.A test to the aerodynamic characteristics of configuration is built with CFD analysis and an approximate model is built up for simulating.Based on the CFD results,response surface methodology（RSM） is used to build an aerodynamic characteristic model as an approximate model for aerodynamic analysis.Genetic algorithm is used for optimization of 3D configuration for hypersonic vehicle,and different optimization shapes of respective optimization targets are got.

关 键 词：高超声速飞行器 气动力预测 遗传算法 优化 

分 类 号：TJ760.12[兵器科学与技术—武器系统与运用工程]