超声速飞行器减阻盘与逆向喷流组合构型减阻防热性能研究  

Research on drag and heat flux reduction efficiency of supersonic vehicle with combination of aerodisk and opposing jet

作　　者：许阳 XU Yang(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《飞行力学》2023年第1期77-85,共9页Flight Dynamics

摘　　要：为降低超声速飞行器气动力和热载荷,采用数值方法对应用减阻盘与逆向喷流组合构型的钝体飞行器的气动性能进行了研究。首先,对仿真计算模型和数值计算方法进行了简要介绍。然后,进行了网格无关性校验和数值方法校验。最后,开展了仿真验证,分析了喷嘴直径比、减阻杆长径比、减阻盘直径比和逆向喷流总压比对减阻和防热性能的影响规律。研究结果表明:增加喷嘴直径比,减阻和防热效率均增大;增加减阻杆长径比,减阻和防热效率均先减小后增大;减阻盘直径比对减阻和防热性能影响不大;增加逆向喷流总压比可以显著改善防热性能,但会降低减阻效率。适当选取减阻盘与逆向喷流参数,最优构型可达到40.9%的减阻效率,同时防热效率达到72.2%。To reduce the aerodynamic force and thermal load of the supersonic vehicle, the aerodynamic performance of blunt body vehicles with a combination of aerodisk and the opposing jet was studied by numerical method. Firstly, the simulation model and numerical calculation method were introduced briefly. Then, the grid independence verification and numerical method verification were carried out. Finally, the simulation verification was carried out, and the effects of the nozzle diameter ratio, the length-to-diameter ratio of the aerospike, the diameter ratio of the aerodisk, and the total pressure ratio of the opposing jet on the drag and heat flux reduction efficiency were analyzed. The results show that with the increase of nozzle diameter ratio, drag and heat flux reduction efficiency increase. When the length-to-diameter ratio of the aerospike is increased, the drag and heat flux reduction efficiency decreases at first, and then increases. The diameter ratio of the aerodisk has little effect on the drag and heat flux reduction efficiency. Increasing the total pressure ratio of the opposing jet can significantly improve the heat flux reduction efficiency, but it will reduce the drag reduction efficiency. The optimal configuration can achieve a drag reduction efficiency of 40.9% and a heat flux reduction efficiency of 72.2% when the parameters of aerodisk and opposing jet are properly selected.

关 键 词：超声速流动 减阻盘 逆向喷流 减阻 防热 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V41