反折式二元超声速进气道研究  

Research of 2-D reflective supersonic inlet

作　　者：柳长安[1] 南向军[1] 闫志勇[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2014年第1期45-49,共5页Journal of Rocket Propulsion

基　　金：国家863项目(2010AA702308)

摘　　要：X-51A采用带两级压缩楔面的反折式进气道设计方案,这是一体化权衡设计的结果,要求进气道设计综合各方面因素进行多目标优化。从发动机设计角度出发对类似于x-51A的反折式二元进气道进行了研究,合理选择了进气道的设计变量并运用多目标粒子群优化算法(MOPSO)对带两级压缩楔面的反折式二元进气道按总压恢复系数、流量系数及出口马赫数三个目标函数进行了多目标优化设计,计算中性能指标参数评估基于Euler方程求解得到。通过优化计算得到了带两级压缩楔面的反折式进气道相关性能指标参数最优变化关系及结构方案,可为后续进气道与飞行器一体化权衡提供设计参考。The design scheme of reflective supersonic inlet with two-stage compression wedge surfaces was adopted by X-51A vehicle. It is a compromise scheme, in which the multi-objective opti- mization is required in the inlet design. Proceeding from engine design, the 2-D reflective supersonic inlet similar to the X-51A＇s inlet is studied in this paper. In this study, the optimization variables were reasonably chosen based on the inlet design parameters, and the multi-objective optimization design of the reflective supersonic inlet with two-stage compression wedge surfaces was executed with the multi-objective particle swarm optimization method （MOPSO） according to the total pressure recovery coefficient, flux coefficient and exit Mach number, which were gotten by solving the 2-D inlet Euler flow equations. Through the optimization, the performance index parameter optimal changing rela- tionship and structure of the supersonic inlet with two-stage compression wedge surfaces were achieved, which can help designers understand their design project and make their decisions better.

关 键 词：反折式进气道 多目标优化 粒子群优化算法 EULER方程 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]