Adaptive terminal sliding mode guidance law with impact angle and fieldof-view constraints

被引：0
|
作者：
Li X.-B. [1 ]
Zhao G.-R. [2 ]
Liu S. [1 ]
Wen J.-X. [1 ]
机构：
[1] School of Coast Defence, Naval Aviation University, Yantai
[2] University Staff, Naval Aviation University, Yantai
来源：
Kongzhi yu Juece/Control and Decision | 2020年 / 35卷 / 10期
关键词：
Adaptive control; Barrier Lyapunov function; Field-of-view angle constraint; Finite-time convergence; Guidance law; Impact angle constraint; Nonsingular terminal sliding mode;
D O I：
10.13195/j.kzyjc.2019.0058
中图分类号：
学科分类号：
摘要：
To solve the terminal guidance problem of missiles intercepting maneuvering targets, a guidance law with impact angle and field-of-view constraints is designed based on the finite-time sliding mode control theory. Firstly, the terminal guidance problem is transformed into the stability problem of the guidance system with state constraints. And, a new nonsingular terminal sliding mode surface and a time-varying barrier Lyapunov function are given, and a terminal sliding mode guidance law is proposed. In addition, an adaptive estimation of the upper bound of the target acceleration is designed for the uncertainty of the target maneuver. Then, the stability theory proves that the state variables of the guidance system are finally finite-time convergence, and field-of-view constraint will not be violated in the whole guidance process based on the design characteristics of the time-varying barrier Lyapunov function and sliding mode surface. Compared with the existing guidance laws considering field-of-view constraint, the guidance law has no command conversion, which can accelerate the convergence rate of the guidance system and enhance the robustness of the guidance system. Finally, simulation experiments verify the effectiveness of the guidance method. © 2020, Editorial Office of Control and Decision. All right reserved.
引用
收藏
页码：2336 / 2344
页数：8
相关论文
共 21 条
  • [1] Park B G, Kim T H, Tahk M J., Biased PNG with terminal-angle constraint for intercepting nonmaneuvering targets under physical constraints, IEEE Transactions on Aerospace and Electronic Systems, 53, 3, pp. 1562-1572, (2017)
  • [2] Zhang Y A, Huang J, Sun Y P., Generalized weighted optimal guidance laws with impact angle constraints, Acta Aeronautica et Astronautica Sinica, 35, 3, pp. 848-856, (2014)
  • [3] Dun X B, Li J L, Cai J Z., Optimal guidance law for intercepting high-speed maneuvering targets, Journal of National University of Defense Technology, 40, 1, pp. 176-182, (2018)
  • [4] Yang C D, Chen H Y., Nonlinear H∞ robust guidance law for homing missiles, Journal of Guidance, Control, and Dynamics, 21, 6, pp. 882-890, (1998)
  • [5] Hua W H, Chen X L., Nonlinear bounded-control differential game guidance law for variable-speed missiles, Control and Decision, 26, 12, pp. 1886-1890, (2011)
  • [6] Guo J G, Han T, Zhou J, Et al., Second-order sliding-mode guidance law with impact angle constraint, Acta Aeronautica et Astronautica Sincia, 38, 2, pp. 215-224, (2017)
  • [7] Zhao B, Zhou J, Lu X D, Et al., Adaptive integral sliding mode guidance law considering impact angel constraint, Control and Decision, 32, 11, pp. 1966-1972, (2017)
  • [8] Song J H, Song S M, Zhou H B., Adaptive nonsingular fast terminal sliding mode guidance law with impact angle constraints, International Journal of Control, Automation and Systems, 14, 1, pp. 99-114, (2016)
  • [9] Sun L H, Wang W H, Yi R, Et al., A novel guidance law using fast terminal sliding mode control with impact angle constraints, ISA Transactions, 64, pp. 12-23, (2016)
  • [10] Huang J, Zhang Y A, Liu Y X., A biased proportional guidance algorithm for moving target with impact angle and field-of-view constraints, Journal of Astronautics, 37, 2, pp. 195-202, (2016)
123