空空导弹过失速翻转后向发射方法  

Air-to-air missile post-stall flip backward launch method

作　　者：刘程鹏 宋文萍[1] 高昌昊 韩少强[1,3] 王跃 韩忠华 Chengpeng LIU;Wenping SONG;Changhao GAO;Shaoqiang HAN;Yue WANG;Zhonghua HAN(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Xi’an Modern Control Technology Research Institution,Xi’an 710065,China;College of Computer Science,Sichuan University,Chengdu 610065,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]西安现代控制技术研究所,西安710065 [3]四川大学计算机学院,成都610065

出　　处：《航空学报》2024年第20期229-241,共13页Acta Aeronautica et Astronautica Sinica

摘　　要：为缩短近距格斗导弹越肩发射的响应时间,实现空空导弹在近距格斗时对于后方目标的快速打击,提出了一种利用导弹在大/超大攻角下的静不稳定性,并辅助喷流直接力控制、末段主动舵偏控制的空空导弹快速后向发射方法。为研究所提出的新发射方法中预置舵偏、喷流直接力、末段主动舵偏控制策略的影响,发展了基于动态嵌套网格的耦合主动舵偏控制策略的高精度计算流体力学/飞行动力学数值模拟方法。数值模拟结果表明,所提出的方法可以在1.53 s内完成导弹的快速重新定向并在翻转末段保持姿态稳定可控。新方法可以将越肩发射的重新定向时间缩短至传统方法的约1/10。To shorten the response time of air-to-air missile and realize rapid attack on backward target in close combat,a rapid backward-launching method of short-range air-to-air missile is developed,which takes advantage of the static instability of missile at large/very large angle of attack,auxiliary jet direct force control and active rudder deflection control.To simulate the influence of preset rudder deflection,jet direct force and active rudder deflection control strategy in the new launching method,a high-precision computational fluid dynamics/flight dynamics numerical simulation method coupling with active rudder deflection control strategy is developed based on the dynamic Chimera grid.Numerical simulation results show that the proposed method can achieve rapid reorientation of the missile in 1.53 s,and maintain a stable and controllable attitude at the end of the flipping phase.The new method can reduce the response time of over-the-shoulder launch to about 1/10 of the traditional method.

关 键 词：空空导弹 越肩发射 过失速重新定向 气动/运动/控制耦合 动态嵌套网格 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] TJ760[兵器科学与技术—武器系统与运用工程]