A new continuous adaptive finite time guidance law against highly maneuvering targets

被引：35
作者：
Guo, Jianguo [1 ]
Li, Yifei [1 ]
Zhou, Jun [1 ]
机构：
[1] Northwestern Polytech Univ, Inst Precis Guidance & Control, Xian 710072, Shaanxi, Peoples R China
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2019年 / 85卷
基金：
中国国家自然科学基金;
关键词：
Guidance law; Sliding mode control; Adaptive; Finite time convergence; Lyapunov stability theory; SLIDING-MODE GUIDANCE; ATTITUDE-CONTROL; SPACECRAFT; CONTROLLER;
D O I：
10.1016/j.ast.2018.08.018
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A novel continuous adaptive finite time guidance (CAFTG) law is proposed for homing missiles. Firstly, three-dimensional nonlinear dynamics describing the pursuit situation of the missile and the target are introduced to obtain the mathematical model of engagement. Secondly, in order to improve the accuracy of interception, a nonlinear disturbance observer with finite time convergence is employed to estimate the acceleration of a target and compensate the guidance law. A continuous guidance scheme with robustness is constructed via sliding mode control theory, which guarantees finite time convergence by Lyapunov stability theory. Finally, simulations are conducted on the nonlinear dynamic models and results demonstrate the effectiveness of proposed guidance method. (C) 2018 Elsevier Masson SAS. All rights reserved.
引用
收藏
页码：40 / 47
页数：8
相关论文
共 40 条
[1]   DUAL-MODE DISTURBANCE-ACCOMMODATING POINTING CONTROLLER FOR HUBBLE-SPACE-TELESCOPE [J].
ADDINGTON, SI ;
JOHNSON, CD .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 1995, 18 (02) :200-207
[2]  
[Anonymous], 2013, IEEE T AEROSP ELECT
[3]   NONLINEAR ADAPTIVE MODEL-FOLLOWING CONTROL [J].
BALESTRINO, A ;
DEMARIA, G ;
ZINOBER, ASI .
AUTOMATICA, 1984, 20 (05) :559-568
[4]   A new observer-based chattering-free sliding mode guidance law [J].
Behnamgol, Vahid ;
Vali, A. R. ;
Mohammadi, A. .
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 2016, 230 (08) :1486-1495
[5]   Multi-objective robust initial alignment algorithm for Inertial Navigation System with multiple disturbances [J].
Cao, Songyin ;
Guo, Lei .
AEROSPACE SCIENCE AND TECHNOLOGY, 2012, 21 (01) :1-6
[6]   Disturbance-Observer-Based Control and Related Methods-An Overview [J].
Chen, Wen-Hua ;
Yang, Jun ;
Guo, Lei ;
Li, Shihua .
IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, 2016, 63 (02) :1083-1095
[7]   Impact Angle Constrained Sliding Mode Guidance Against Maneuvering Target With Unknown Acceleration [J].
Cho, Dongsoo ;
Kim, H. Jin ;
Tahk, Min-Jea .
IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, 2015, 51 (02) :1310-1323
[8]   Design of three-dimensional nonlinear guidance law with bounded acceleration command [J].
Du, Runle ;
Meng, Kezi ;
Zhou, Di ;
Liu, Jiaqi .
AEROSPACE SCIENCE AND TECHNOLOGY, 2015, 46 :168-175
[9]  
Ghawghawe S. N., 1996, IEEE T AERO ELEC SYS, V32, P268
[10]   Sliding Mode Control for Mismatched Uncertain Systems Using an Extended Disturbance Observer [J].
Ginoya, Divyesh ;
Shendge, P. D. ;
Phadke, S. B. .
IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, 2014, 61 (04) :1983-1992
1234