Fixed-time convergent guidance law considering autopilot dynamics

被引：0
|
作者：
Zhang K. [1 ]
Yang S. [1 ]
Li B. [2 ]
Liu C. [1 ]
机构：
[1] Department of Missile Engineering, Shijiazhuang Campus of Army Engineering University, Shijiazhuang
[2] Department of Scientific Research, Army Engineering University, Nanjing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2019年 / 40卷 / 11期
关键词：
Autopilot dynamics; Backstepping control; Disturbance observer; Fixed-time convergence; Guidance law; Impact angle constraint; Terminal sliding mode control;
D O I：
10.7527/S1000-6893.2019.23227
中图分类号：
学科分类号：
摘要：
A new guidance law considering the impact angle constraint, autopilot dynamic characteristics, and fixed-time convergence is designed for the guidance problem of attacking maneuvering targets. First, based on nonsingular terminal sliding mode control and fixed-time stability theory, the backstepping method is used to design the guidance law. In the process of the design, a nonsingular terminal sliding mode surface with fixed-time convergence is designed. Based on fixed-time control and sliding mode control, the virtual control law is designed and a nonlinear first-order filter is constructed to solve the problem of "differential expansion" in the traditional backstepping design. Based on the super-twisting algorithm and fixed-time stability theory, a fixed-time convergence sliding mode disturbance observer is designed to estimate the target maneuvering and other interferences. Then, based on the Lyapunov stability theory, the fixed-time stability of the guidance law is proved, and the expression for convergence time is given. Finally, the effectiveness of the proposed guidance law is verified by simulation analysis. Compared with the existing guidance laws, the proposed guidance law has higher guidance precision and angle constraint accuracy, faster system convergence speed, and less energy consumption. © 2019, Press of Chinese Journal of Aeronautics. All right reserved.
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