宇航学报

宇航学报 ›› 2022, Vol. 43 ›› Issue (5): 649-664.doi: 10.3873/j.issn.1000-1328.2022.05.010

• 制导、导航、控制与电子 • 上一篇    下一篇

考虑约束的高超声速飞行器制导与控制一体化设计

唐建，齐瑞云，姜斌
  

  1. 1. 南京航空航天大学自动化学院，南京 211106；2. 南京航空航天大学先进飞行器导航、控制与健康管理工业和信息化部重点实验室，南京 211106
  • 收稿日期:2021-02-03 修回日期:2021-09-02 出版日期:2022-05-15 发布日期:2022-05-15
  • 基金资助:
    国家自然科学基金（61873127, 62020106003）

Integrated Guidance and Control of Hypersonic Vehicle Considering Constraints

TANG Jian, QI Ruiyun, JIANG Bin   

  1. 1. College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China;2. Key Laboratory of Navigation, Control and Heath management Technologies of Advanced Aerocraft, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
  • Received:2021-02-03 Revised:2021-09-02 Online:2022-05-15 Published:2022-05-15

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摘要： 针对高超声速飞行器上升段飞行过程中强耦合、强非线性同时要求满足过程约束的特点，提出了一种结合级联控制方法和控制障碍函数的新型三维制导控制一体化算法。首先通过对速度子系统设计控制障碍函数约束算法来满足飞行器的过程约束要求，然后利用反步法、动态逆控制方法设计其余子系统的控制器，两者共同组成制导控制一体化控制器。考虑到飞行器在上升过程中容易遭遇阵风扰动的问题，设计非线性干扰观测器以增强算法的鲁棒性。最后通过李雅普诺夫函数证明了系统的稳定性，并且通过仿真验证了该新算法能够在满足高超声速飞行器上升段过程约束的同时，实现飞行器的三维跟踪控制。

关键词: color:#000000, font-family:", sans serif", ,tahoma,verdana,helvetica, font-size:12px, font-style:normal, font-weight:400, line-height:18px, text-decoration:none, ">高超声速飞行器；制导与控制一体化；级联控制；干扰观测器；控制障碍函数color:#000000, font-family:", sans serif", ,tahoma,verdana,helvetica, font-size:12px, font-style:normal, font-weight:400, line-height:18px, text-decoration:none, ">

Abstract: Aiming at the characteristics of strong coupling, strong nonlinearity and requirements to meet path constraints during the ascent phase of hypersonic vehicle, a new integrated three dimensional guidance and control algorithm combining cascade control method and the control barrier function is proposed. Firstly, the control barrier function constraint algorithm is designed for the velocity subsystem to meet the path constraints of the vehicle, and then, the backstepping method and dynamic inverse control method are used to design controllers of other subsystems. Both of them constitute the integrated guidance and control controller. Considering the problem that the vehicle is prone to encounter wind disturbances during ascent, a nonlinear disturbance observer is designed to enhance the robustness of the algorithm. Finally, the stability of the system is proved by the Lyapunov function, and simulations verify that the new algorithm can realize the three dimensional tracking control of the hypersonic vehicle while meeting the path constraints in the ascent phase.

Key words: Hypersonic vehicle, Integrated guidance and control, Cascade control, Disturbance observer, Control barrier function

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