大攻角条件下的二维进气道型面优化设计  

Optimum design for 2-D inlet while large AOA considered

作　　者：李理[1] 陈小庆[1] 杨涛[1] 张青斌[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2009年第4期418-421,426,共5页Journal of Solid Rocket Technology

基　　金：国防科大国际合作研究项目资助(飞行器多目标设计GJ07-01-01)

摘　　要：基于一维气体动力学,以进气道前体楔面楔角为优化设计参数,以总压恢复系数、流量系数最大及阻力系数最小为优化目标,对二维进气道外型面进行了优化设计,并综合考虑了大攻角条件下的位于背风面与迎风面上进气道面临的不同来流条件。在优化设计中,采用改进后的NSGA-Ⅱ遗传算法。在问题求解中,对NSGA-Ⅱ算法的交叉算子及优选策略进行了改进。优化结果表明,总压恢复系数与阻力系数的优化结果具有一致性,即二者可同时达到最优;第一级楔角的大小对流量系数的影响显著。对优化结果进行了数值模拟,数值模拟结果表明,文中设计的型面构型满足设计要求。该设计方法可用于二维进气道型面考虑攻角条件下的初步设计。Based on one-dimension aero dynamics, the external compression surface of 2-D inlet was optimized aiming at maximum total pressure recovery and mass flow capture ratio, and minimum drag coefficient. The wedge angles were taken as optimum characters in this optimum design. In the design, the difference is considered of flow field between windward side and leeward side for the missile with a large angle of attack. A genetic algorithm, NSGA- Ⅱ, is adopted here. And the NSGA- Ⅱ method is improved by adopting a new crossover operator. The optimum design result shows that the value variation trend of total pressure recovery is in ac- cordance with drag coefficient and the flow rate is tightly associated with the value of first wedge angle. Numeral simulation result of the inlet shows that it is acceptable. Such a method is reasonable and can be adopted in preliminary inlet design while large angle of attack considered.

关 键 词：进气道 外压式 优化设计 遗传算法 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]