Design of integral sliding mode guidance law based on disturbance observer

doi:10.23919/JSEE.2023.000111

Journal of Systems Engineering and Electronics ›› 2024, Vol. 35 ›› Issue (1): 186-194.doi: 10.23919/JSEE.2023.000111

• CONTROL THEORY AND APPLICATION • Previous Articles

Design of integral sliding mode guidance law based on disturbance observer

Jianping ZHOU¹^,²(), Wenjie ZHANG³^,*(), Hang ZHOU¹(), Qiang LI⁴(), Qunli XIA¹()

¹ School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
² School of Informatic Engineering, Mianyang Techers’ College, Mianyang 62100, China
³ Beijing Institute of Electronic System Engineering, Beijing 100854, China
⁴ Beijing Institute of Space Long March Vehicle, Beijing 100076, China

Received:2022-03-14 Online:2024-02-18 Published:2024-03-05
Contact: Wenjie ZHANG E-mail:6043105@qq.com;l013763956@qq.com;1797779122@qq.com;liqiang2568837@126.com;1010@bit.edu.cn
About author:
ZHOU Jianping was born in 1977. He received his B.E. degree from Chongqing University in 2000, and M.E. degree from University of Electronic Science and Technology of China in 2008. He is a Ph.D. candidate in Beijing Institute of Technology. His research interests are missile guidance and control. E-mail: 6043105@qq.com

ZHANG Wenjie was born in 1992. He received his Ph.D. degree from Beijing Institute of Technology in 2020. He is currently working in Beijing Institute of Electronic System Engineering. His main research interests include flight vehicle design, guidance, and control. E-mail: l013763956@qq.com

ZHOU Hang was born in 1998. He received his B.E. degree from Beijing Institute of Technology in 2020. He is a master candidate in Beijing Institute of Technology. His research interests are missile guidance and control technology. E-mail: 1797779122@qq.com

LI Qiang was born in 1986. He received his B.E. degree from Beijing Institute of Technology in 2009, and Ph.D. degree from Beijing Institute of Technology in 2015. He is an senior engineer in Beijing Institute of Space Long March Vehicle. His main research interests include flight vehicle design, guidance and control. E-mail: liqiang2568837@126.com

XIA Qunli was born in 1971. He received his B.E. degree in Launching engineering, M.E. degree in flight mechanics and Ph.D. degree in aircraft design from Beijing Institute of Technology in 1993, 1996, and 1999 respectively. He is an associate professor in Beijing Institute of Technology. His research interests are missile guidance and control technology. E-mail: 1010@bit.edu.cn

Abstract

Abstract:

With the increasing precision of guidance, the impact of autopilot dynamic characteristics and target maneuvering abilities on precision guidance is becoming more and more significant. In order to reduce or even eliminate the autopilot dynamic operation and the target maneuvering influence, this paper suggests a guidance system model involving a novel integral sliding mode guidance law (ISMGL). The method utilizes the dynamic characteristics and the impact angle, combined with a sliding mode surface scheme that includes the desired line-of-sight angle, line-of-sight angular rate, and second-order differential of the angular line-of-sight. At the same time, the evaluation scenario considere the target maneuvering in the system as the external disturbance, and the non-homogeneous disturbance observer estimate the target maneuvering as a compensation of the guidance command. The proposed system’s stability is proven based on the Lyapunov stability criterion. The simulations reveale that ISMGL effectively intercepted large maneuvering targets and present a smaller miss-distance compared with traditional linear sliding mode guidance laws and trajectory shaping guidance laws. Furthermore, ISMGL has a more accurate impact angle and fast convergence speed.

Key words: disturbance observer, pilot dynamics, integral sliding mode, impact angle constraint, maneuvering target

Jianping ZHOU, Wenjie ZHANG, Hang ZHOU, Qiang LI, Qunli XIA. Design of integral sliding mode guidance law based on disturbance observer[J]. Journal of Systems Engineering and Electronics, 2024, 35(1): 186-194.

Figures/Tables 11

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References 18

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Variable	Value
${v_{\rm{M}}}$/(${\rm{m} }\cdot{\rm{s} }^{-1}$)	600
${v_{\rm{T}}}$/(${\rm{m} }\cdot{\rm{s} }^{-1}$)	300
${x_{\rm{M}}}$/(${\rm{m} }\cdot{\rm{s} }^{-1}$)	0
${y_{\rm{M}}}$/${\rm{m}}$	0
${\theta _{\rm{M}}}$/(°)	40
${x_{\rm{T}}}$/m	4330
${y_{\rm{T}}}$/m	2500
${\theta _{\rm{T}}}$/(°)	0
$\tau $/s	0.5
${q_d}$/(°)	20

Guidance law	${t_f}$/s	$r( { {t_f} } )$/m	$q( { {t_f} } )$/(°)
ISMGL	13.38	0.38	19.95
LSMGL	13.32	0.45	19.90
TSGL	13.62	7.1	179
ISMGL	16.72	0.42	20.03
LSMGL	16.58	0.58	20.06
TSGL	16.38	16.0	-68

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Design of integral sliding mode guidance law based on disturbance observer

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