宽速域高超声速飞机进气道不起动一体化保护控制  

Integrated Protection Control for Unstart of the Wide Speed Range Hypersonic Vehicle Inlet

作　　者：李家鑫 李旦伟 刘凯 吴国强[3] 吴志刚 LI Jiaxin;LI Danwei;LIU Kai;WU Guoqiang;WU Zhigang(School of Aeronautics and Astronautic,Sun Yat-sen University,Shenzhen 518107,China;Shenyang Aircraft Design&Research Institute,Shenyang 110035,China;School of Aeronautics and Astronautic,Dalian University of Technology,Dalian 116024,China)

机构地区：[1]中山大学航空航天学院,深圳518107 [2]沈阳飞机设计研究所,沈阳110035 [3]大连理工大学航空航天学院,大连116024

出　　处：《宇航学报》2023年第7期1034-1041,共8页Journal of Astronautics

基　　金：国家自然科学基金(U2141229);航空科学基金(2019ZC063001)。

摘　　要：针对宽速域高超声速飞机机动飞行任务过程中容易出现进气道不起动问题,研究开展了基于最佳进气道优化的飞行/推进一体化保护控制方法研究。该方法可依据飞行状态对进气道流场最优攻角进行实时优化,并基于极点配置策略完成攻角与燃烧室扩张比联合调节,实现飞行/推进一体化进气道保护控制。仿真结果表明,一体化保护控制方法与传统进气道不起动保护控制方法相比,在相同设计前提下可提升进气道不起动稳定裕度,降低进气道不起动风险,避免进气道不起动对宽速域高超声速飞机飞行任务造成的不利影响。The inlet unstart problem of the wide speed range hypersonic vehicle during maneuvering flight is a key problem that must be considered in flight control design.An integrated flight/propulsion protection and control method based on optimal inlet optimization is developed in this paper.The method can optimize the angle of attack of the inlet flow field in real-time according to the flight condition,and the joint adjustment of the angle of attack and the expansion ratio of the combustion chamber is completed by the pole placement strategy.The simulation results show that compared with the traditional unstart protection control method,the integrated protection control method can improve the unstart stability margin of the inlet under the same design premise,reduce the unstart risk of the inlet,and avoid the adverse effects of the unstart of the inlet on the flight mission of the wide speed range hypersonic vehicle.

关 键 词：宽速域飞机 进气道不起动 一体化控制 流场优化 

分 类 号：V249.122.2[航空宇航科学与技术—飞行器设计]