自适应非奇异快速终端滑模固定时间收敛制导律

doi:10.13700/j.bh.1001-5965.2018.0621

北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (6): 1059-1070.doi: 10.13700/j.bh.1001-5965.2018.0621

自适应非奇异快速终端滑模固定时间收敛制导律

赵国荣¹, 李晓宝², 刘帅², 韩旭²

1. 海军航空大学参谋部, 烟台 264001;
2. 海军航空大学岸防兵学院, 烟台 264001

收稿日期:2018-10-29 出版日期:2019-06-20 发布日期:2019-06-18
通讯作者: 赵国荣 E-mail:grzhao6881@163.com
作者简介:赵国荣博士,教授。主要研究方向:飞行器控制与导航技术;李晓宝男,博士研究生。主要研究方向:飞行器导航制导与控制。
基金资助:
国家自然科学基金（61473306）

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

ZHAO Guorong¹, LI Xiaobao², LIU Shuai², HAN Xu²

1. University Staff, Naval Aviation University, Yantai 264001, China;
2. Coastal Defence Academy, Naval Aviation University, Yantai 264001, China

Received:2018-10-29 Online:2019-06-20 Published:2019-06-18

摘要/Abstract

摘要： 针对机动目标的末制导拦截问题，设计了一种带攻击角度约束的非奇异快速终端滑模固定时间收敛制导律。与有限时间收敛终端滑模制导律相比，所提制导律能够确保弹目视线（LOS）角和弹目视线角速率在固定时间内是收敛的，并且收敛时间是独立于制导系统初始条件的，可以根据制导律参数预先给定。构造了一种新型的非奇异快速终端滑模面，有效解决了奇异性问题，同时通过合理地改变滑模面与弹目视线角跟踪误差的趋近律指数，使得制导系统比现有的固定时间收敛控制具有更快的收敛速率。此外，设计了一种自适应律，针对目标机动引起的未知扰动进行估计，使得制导律的设计无需预先知道任何关于目标机动的信息。通过仿真实验验证了所提制导律能够使导弹成功拦截机动目标，并且与现有制导律相比，具有更快的系统收敛速率、更高的拦截精度及更短的拦截时间。

关键词: 制导律, 攻击角度约束, 自适应控制, 固定时间收敛, 非奇异快速终端滑模

Abstract: 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.

Key words: guidance law, impact angle constraint, adaptive control, fixed-time convergence, nonsingular fast terminal sliding mode

中图分类号:

V448.133

赵国荣, 李晓宝, 刘帅, 韩旭. 自适应非奇异快速终端滑模固定时间收敛制导律[J]. 北京航空航天大学学报, 2019, 45(6): 1059-1070.

ZHAO Guorong, LI Xiaobao, LIU Shuai, HAN Xu. Adaptive nonsingular fast terminal sliding mode guidance law with fixed-time convergence[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2019, 45(6): 1059-1070.

参考文献

[1] 蔡洪,胡正东,曹渊.具有终端角度约束的导引律综述[J].宇航学报,2010,31(2):315-323.CAI H,HU Z D,CAO Y.A survey of guidance law with terminal impact constraints[J].Journal of Astronautics,2010,31(2):315-323(in Chinese).
[2] PARK B G,KIM T H,TAHK M J.Biased PNG with terminal-angle constraint for intercepting nonmaneuvering targets under physical constraints[J].IEEE Transactions on Aerospace and Electronic System,2017,55(3):1562-1572.
[3] SHINAR J,SHIMA T,KEBKE A.On the validity of linearized analysis in the interception of reentry vehicles[C]//Proceedings of the AIAA Guidance,Navigation,and Control Conference.Reston:AIAA,1998:1050-1060.
[4] 张友安,黄诘,孙阳平.带有落角约束的一般加权最优制导律[J].航空学报,2014,35(3):848-856.ZHANG Y A,HUANG J,SUN Y P.Generalized weighted optimal guidance law with impact angle constraints[J].Acta Aeronautica et Astronautica Sincia,2014,35(3):848-856(in Chinese).
[5] 刘延芳,齐乃明,夏齐,等.基于非线性模型的大气层内拦截弹微分对策制导律[J].航空学报,2011,32(7):1171-1179.LIU Y F,QI N M,XIA Q,et al.Differential game guidance law for endoatmospheric interceptor missiles based on nonlinear model[J].Acta Aeronautica et Astronautica Sincia,2011,32(7):1171-1179(in Chinese).
[6] 周卫东,陈沿逵,熊少锋.带攻击角度约束的无抖振滑模制导律设计[J].北京航空航天大学学报,2016,42(2):669-676. ZHOU W D,CHEN Y K,XIONG S F.Chattering-free sliding mode guidance law with impact angle constraint[J].Journal of Beijing University of Aeronautics and Astronautics,2016,42(2):669-676(in Chinese).
[7] ATES U A.Lyapunov based nonlinear impact angle guidance law for stationary targets[C]//Proceeding of the AIAA Guidance,Navigation,and Control Conference.Reston:AIAA,2015:1-14.
[8] ZHANG Y X,SUN M W,CHEN Z Q.Finite time convergent guidance law with impact angle constraint based on sliding control[J].Nonlinear Dynamics,2012,7(3):619-625.
[9] HE S M,LIN D.Adaptive nonsingular sliding mode based guidance law with terminal angular constraint[J].International Journal of Aeronautical and Space Sciences,2014,15(2):146-152.
[10] 杨锁昌,张宽桥,陈鹏.带攻击角度约束的自适应终端滑模制导律[J].北京航空航天大学学报,2016,42(8):1566-1574.YANG S C,ZHANG K Q,CHEN P.Adaptive terminal sliding mode guidance with impact angle constraint[J].Journal of Beijing University of Aeronautics and Astronautics,2016,42(8):1566-1574(in Chinese).
[11] SONG J H,SONG S M,ZHOU H B.Adaptive nonsingular fast terminal sliding mode guidance law with impact angle constraints[J].International Journal of Control,Automation and Systems,2016,14(1):99-114.
[12] POLYAKOV A.Nonlinear feedback design for fixed-time stabilization of linear control systems[J].IEEE Transactions on Automatic Control,2012,57(8):2106-2110.
[13] ZUO Z Y.Nonlinear fixed-time consensus tracking for second-order multi-agent networks[J].Automatica,2015,54:305-309.
[14] LI H J,CAI Y L.On SFTSM control with fixed-time convergence[J].IET Control Theory and Applications,2017,11(6):766-773.
[15] ZHANG Y,TANG S J,GUO J.Adaptive terminal angle constraint interception against maneuvering targets with fast fixed-time convergence[J].International Journal of Robust and Nonlinear Control,2018,28(8):2996-3014.
[16] SUN S,ZHOU D,HOU W T.A guidance law with finite time convergence accounting for autopilot lag[J].Aerospace Science and Technology,2013,25(1):132-137.
[17] ZHAO B,ZHOU J.Smooth adaptive finite time guidance law with impact angle constraints[J].International Journal of Aerospace Engineering,2016,2016:5730168.
[18] YANG L,YANG J Y.Nonsingular fast terminal sliding-mode control for nonlinear dynamical systems[J].International Journal of Robust Nonlinear Control,2011,21(16):1865-1879.
[19] KUMAR S R,RAO S,GHOSE D.Nonsingular terminal sliding mode guidance with impact angle constraints[J].Journal of Guidance,Control,and Dynamics,2014,37(4):1114-1130.
[20] XIONG S F,WANG W H,SONG S,et al.Extended state observer based impact angle constrained guidance law for maneuvering target interception[J].Journal of Aerospace Engineering,2015,29(14):2589-2607.

自适应非奇异快速终端滑模固定时间收敛制导律

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

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