高超声速无人机末端能量管理段无动力返回制导方案  

Unpowered Return Guidance Scheme for the Terminal Area Energy Management of Hypersonic UAV

作　　者：王震[1] 李春涛[1] 王双双 苏子康 戴飞 Wang Zhen;Li Chuntao;Wang Shuangshuang;Su Zikang;Dai Fei(College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Unit 94804 of PLA,Shanghai 200040,China)

机构地区：[1]南京航空航天大学自动化学院,南京211106 [2]中国人民解放军94804部队,上海200040

出　　处：《战术导弹技术》2021年第5期71-81,共11页Tactical Missile Technology

基　　金：国家自然科学基金(61903190);航空科学基金(2019ZA052006)。

摘　　要：针对某高超声速无人机在到达末端能量管理段窗口时,位置、能量、航向角变化范围大等问题,提出了一种基于多轨迹调度的制导方法,使其以期望状态进入自动着陆窗口。基于质点三自由度模型,建立了该飞行器的动压和高度的动力学模型,设计了最陡、最浅和标称下滑动压剖面,推演出能量走廊和标称下滑高度剖面。提出了航向校准圆柱半径、位置、进场方式等优化机制,设计多条地面轨迹和大动压制导、标称制导、小动压制导三种制导策略。最后根据初始能量选择制导策略,根据根据初始位置与航向角选择地面轨迹,实现无人机以期望状态进入自动着陆窗口。Aiming at the large variation range of position,energy,and heading angle when a hypersonic UAV reaches the terminal area energy management(TAEM),a guidance method based on multi-trajectory scheduling is proposed to make it enter the automatic landing interface in a desired state.Based on the three-degree-of-freedom model of mass point,the dynamic model of the dynamic pressure and height of the aircraft is established,the steepest,shallowest and nominal sliding dynamic pressure profiles are designed,and the energy corridor and nominal sliding height profiles are deduced.The optimization mechanism of heading alignment cylinder radius,position,approach method is proposed,and multiple ground trajectories and three guidance strategies are designed,which are large dynamic pressure guidance,nominal guidance and small dynamic pressure guidance.Finally,the guidance strategy is selected according to the initial energy,the guidance strategy is selected according to the initial position and heading angle,so that the UAV enters the automatic landing interface in the desired state.

关 键 词：末端能量管理 能量走廊 动压剖面 能量耗散 轨迹制导 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]