An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

doi:10.21629/JSEE.2020.01.17

Journal of Systems Engineering and Electronics ›› 2020, Vol. 31 ›› Issue (1): 168-184.doi: 10.21629/JSEE.2020.01.17

收稿日期:2019-04-11 出版日期:2020-02-20 发布日期:2020-02-25

An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

Wenjie ZHANG¹(), Shengnan FU²(), Wei LI¹(), Qunli XIA^1,*()

¹ School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
² School of Mechatronical Engineering, Beijing Institute of Technology, Beijing 100081, China

Received:2019-04-11 Online:2020-02-20 Published:2020-02-25
Contact: Qunli XIA E-mail:bit_zhangwenjie@outlook.com;1041500186@qq.com;lion_lee1994@126.com;1010@bit.edu.cn
About author:ZHANG Wenjie was born in 1992. He received his B.E. degree from Beijing Institute of Technology in 2015. He is currently a doctoral student in School of Aerospace Engineering, Beijing Institute of Technology. His main research interests include flight vehicle design, guidance and control. E-mail: bit_zhangwenjie@outlook.com|FU Shengnan was born in 1993. She received her B.E. degree from Beijing Institute of Technology in 2014. She is currently a doctoral student in School of Mechatronical Engineering, Beijing Institute of Technology. Her main research interests include flight vehicle design, guidance and control. E-mail: 1041500186@qq.com|LI Wei was born in 1994. He received his B.E. degree from Beijing Institute of Technology in 2015. He is currently a doctoral student in School of Aerospace Engineering, Beijing Institute of Technology. His main research interests include flight vehicle design, guidance and control. E-mail: lion_lee1994@126.com|XIA Qunli was born in 1971. He is a Ph.D. and an adjunct professor in Beijing Institute of Technology. His research interests are control and guidance technology. E-mail: 1010@bit.edu.cn
Supported by:
the Joint Equipment Fund of the Ministry of Education(6141A02022340);This work was supported by the Joint Equipment Fund of the Ministry of Education (6141A02022340)

摘要/Abstract

Abstract:

An integral sliding mode guidance law (ISMGL) combined with the advantages of the integral sliding mode control (SMC) method is designed to address maneuvering target interception problems with impact angle constraints. The relative motion equation of the missile and the target considering the impact angle constraint is established in the longitudinal plane, and an integral sliding mode surface is constructed. The proposed guidance law resolves the existence of a steady-state error problem in the traditional SMC. Such a guidance law ensures that the missile hits the target with an ideal impact angle in finite time and the missile is kept highly robust throughout the interception process. By adopting the dynamic surface control method, the ISMGL is designed considering the impact angle constraints and the autopilot dynamic characteristics. According to the Lyapunov stability theorem, all states of the closed-loop system are finally proven to be uniformly bounded. Simulation results are compared with the general sliding mode guidance law and the trajectory shaping guidance law, and the findings verify the effectiveness and superiority of the ISMGL.

Key words: impact angle constraint, integral sliding mode, maneuvering target, Lyapunov stability, dynamic characteristic

. [J]. Journal of Systems Engineering and Electronics, 2020, 31(1): 168-184.

Wenjie ZHANG, Shengnan FU, Wei LI, Qunli XIA. An impact angle constraint integral sliding mode guidance law for maneuvering targets interception[J]. Journal of Systems Engineering and Electronics, 2020, 31(1): 168-184.

图/表 23

参考文献 60

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Case	Guidance law	$t_f$ /s	$r(t_f)$ /m	$q(t_f)$ /($^\circ$ )
	ISMGL	25.07	0.29	30.28
1	GSMGL	25.07	0.49	30.60
	TSGL	26.85	1.50	30.31
	ISMGL	29.15	0.22	29.98
2	GSMGL	29.16	0.48	28.15
	TSGL	31.19	1.63	30.21

Parameter	Initial flight path angle $\theta _M (0) /(^{\circ})$
Parameter	0	30	60	90
$t_f / \text{s}$	29.07	29.06	29.14	29.29
$r(t_f) / \text{m}$	0.09	0.06	0.20	0.30
$q(t_f) / (^\circ)$	29.96	29.91	29.88	30.02

An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

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