Missile guidance law design based on free-time convergent error dynamics

doi:10.23919/JSEE.2024.000103

Journal of Systems Engineering and Electronics ›› 2024, Vol. 35 ›› Issue (5): 1315-1325.doi: 10.23919/JSEE.2024.000103

收稿日期:2022-10-26 出版日期:2024-10-18 发布日期:2024-11-06

Missile guidance law design based on free-time convergent error dynamics

Yuanhe LIU¹^,²(), Nianhao XIE²^,³(), Kebo LI²(), Yan’gang LIANG²^,*()

¹ Aviation Combat and Service Institute, Aviation University of Air Force, Changchun 130022, China
² College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410072, China
³ Naval Aeronautical University, Yantai 264000, China

Received:2022-10-26 Online:2024-10-18 Published:2024-11-06
Contact: Yan’gang LIANG E-mail:liuyuanhe12@nudt.edu.cn;xienianhao@nudt.edu.cn;likeboreal@nudt.edu.cn;liangyg@nudt.edu.cn
About author:
LIU Yuanhe was born in 1993. He received his Ph.D. degree from the National University of Defense Technology, Changsha, China, in 2023. He is a lecturer with Aviation University of Air Force. His current research interests include flight vehicle dynamics, guidance, and control. E-mail: liuyuanhe12@nudt.edu.cn

XIE Nianhao was born in 1994. She received her Ph.D. degree from the National University of Defense Technology, Changsha, China, in 2023. She is a lecturer with Naval Aeronautical University. Her current research interests are multi-target tracking method, and formation control of multi-agent system. E-mail: xienianhao@nudt.edu.cn

LI Kebo was born in 1986. He received his B.S. degree in aerospace engineering from National University of Defense Technology (NUDT), Changsha, China, in 2008, and M.S. and Ph.D. degrees in flight vehicle design in aeronautical and astronautical science and technology from NUDT, Changsha, China, in 2010 and 2016, respectively. He is currently an associate professor with the Department of Applied Mechanics, College of Aerospace Science and Engineering, NUDT. His main research interests include missile guidance laws and spacecraft guidance and control. E-mail: likeboreal@nudt.edu.cn

LIANG Yan’gang was born in 1979. He received his Ph.D. degree in aerospace science and technology from National University of Defense Technology (NUDT), China, in 2009. He is currently a professor with the Department of Applied Mechanics, College of Aerospace Science and Engineering, NUDT. His research interests include aerospace system analysis and simulation, and effectiveness assessment. E-mail: liangyg@nudt.edu.cn
Supported by:
This work was supported by the National Natural Science Foundation of China (12002370).

摘要/Abstract

Abstract:

To solve the finite-time error-tracking problem in missile guidance, this paper presents a unified design approach through error dynamics and free-time convergence theory. The proposed approach is initiated by establishing a desired model for free-time convergent error dynamics, characterized by its independence from initial conditions and guidance parameters, and adjustable convergence time. This foundation facilitates the derivation of specific guidance laws that integrate constraints such as leading angle, impact angle, and impact time. The theoretical framework of this study elucidates the nuances and synergies between the proposed guidance laws and existing methodologies. Empirical evaluations through simulation comparisons underscore the enhanced accuracy and adaptability of the proposed laws.

Key words: guidance design, free-time convergence, error dynamics approach, impact angle constraint, impact time constraint

. [J]. Journal of Systems Engineering and Electronics, 2024, 35(5): 1315-1325.

Yuanhe LIU, Nianhao XIE, Kebo LI, Yan’gang LIANG. Missile guidance law design based on free-time convergent error dynamics[J]. Journal of Systems Engineering and Electronics, 2024, 35(5): 1315-1325.

图/表 9

参考文献 15

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Number	Guidance law	K or N	T_s/s
Missile 1	FeTCED-LACG	3	20
Missile 2	FeTCED-LACG	3	30
Missile 3	FeTCED-LACG	3	40
Missile 4	PNG	4	−

Number	Guidance law	(N, K)	T_s/s
Missile 1	FeTCED-IACG	(4, 3)	20
Missile 2	FeTCED-IACG	(4, 3)	30
Missile 3	FeTCED-IACG	(4, 3)	40
Missile 4	OED-IACG	(4, 3)	−

Number	Guidance law	(N, K)	T_s/s
Missile 1	FeTCED-ITCG	(4, 5)	20
Missile 2	FeTCED-ITCG	(4, 5)	30
Missile 3	FeTCED-ITCG	(4, 5)	40
Missile 4	OED-ITCG	(4, 5)	−

Missile guidance law design based on free-time convergent error dynamics

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