Adaptive nonsingular fast terminal sliding mode guidance law with fixed-time convergence

被引：0
|
作者：
Zhao G. [1 ]
Li X. [2 ]
Liu S. [2 ]
Han X. [2 ]
机构：
[1] University Staff, Naval Aviation University, Yantai
[2] Coastal Defence Academy, Naval Aviation University, Yantai
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2019年 / 45卷 / 06期
基金：
中国国家自然科学基金;
关键词：
Adaptive control; Fixed-time convergence; Guidance law; Impact angle constraint; Nonsingular fast terminal sliding mode;
D O I：
10.13700/j.bh.1001-5965.2018.0621
中图分类号：
学科分类号：
摘要：
To deal with the terminal guidance problem of missiles for intercepting maneuvering targets, a nonsingular fixed-time convergent fast terminal sliding mode guidance law is developed with impact angle constraints. Compared with finite-time convergent terminal sliding mode guidance laws, the proposed guidance law ensures that the line of sight (LOS) angle and the LOS angular rate are fixed-time convergent. The convergence time is independent of the initial states of the guidance system and can be set in advance by the guidance law's parameters. Compared with conventional fixed-time convergent control, a novel nonsingular terminal sliding mode is designed to solve the singularity problem and the faster convergence rate is guaranteed by regulating the index of the approaching laws of the sliding surface and the LOS angle error. Besides, an adaptive law for unknown upper bound estimation of the target acceleration is presented and a priori information on the target acceleration is not required to be known. Finally, simulation results show that the missile can intercept the maneuvering targets effectively with the proposed guidance law. Besides, comparison with the existing guidance laws indicates that the faster convergence rate of the guidance system, the shorter intercept time and the higher intercept accuracy are achieved by the proposed guidance law. © 2019, Editorial Board of JBUAA. All right reserved.
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页码：1059 / 1070
页数：11
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