基于载机视觉信息的改进视线制导律设计

doi:10.12305/j.issn.1001-506X.2024.08.25

Abstract

Abstract:

For the demand of low-cost precision strike of unmanned airborne weapons, the proposal of using airborne optoelectronic pods to obtain guidance information and using line-of-sight (LOS) guidance method for guidance law design is proposed. By analyzing the motion relationship of the carrier aircraft, missile, and target, a system state space model is established, and an improved LOS guidance law is designed based on the backstepping method and sliding mode control. The parameters in the guidance law that cannot be obtained by the aircraft are discussed. The tracking differentiator is used to extract the LOS angle and estimate the LOS velocity information. Numerical simulation results show that the improved LOS guidance law can still ensure the accurate strike on the ground target in the presence of LOS angle noise and missile vector pull-off. Compared with the traditional LOS guidance law, the movement direction of the aircraft is not limited, so it can stay away from the target after missile launching to avoid being threatened, which meets the practical demand.

Key words: line-of-sight (LOS) guidance, backstepping method, sliding mode control, airborne air-to-ground missile, tracking differentiator

CLC Number:

TJ765.3

Wenwen ZHANG, Cheng ZHANG, Chenming ZHENG, Runbei CHENG, Tianle CHEN. Design of improved line-of-sight guidance law based on aircraft visual information[J]. Systems Engineering and Electronics, 2024, 46(8): 2779-2788.

Figures/Tables 17

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References 30

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初始状态	数值
载机位置P_a₀/m	(0, 500, 0)
导弹位置P_m₀/m	(0, 500, 0)
目标位置P_t₀/m	(1 700, 0, 0)
载机速度V_a/(m·s^－1)	25
导弹速度V_m₀/(m·s^－1)	25
导弹弹道倾角θ₀/(°)	-16.39
导弹弹道偏角$ \boldsymbol{\psi}_{V_0}$/(°)	0

目标状态	导弹矢径拉偏量/%	脱靶量/m
静止	+10	0.43
静止	-10	0.25
匀速直线	+10	0.20
匀速直线	-10	0.07
圆弧机动	+10	0.69
圆弧机动	-10	0.43

制导律	载机方位/(°)
制导律	0	45	－45	90	－90	135	－135	180
BS-LOSG	0.22	0.31	0.32	0.13	0.13	0.13	0.13	0.18
传统视线制导律	0.19	0.84	0.84	2.91	3.12	65.39	65.43	42.60

制导律	载机方位/(°)
制导律	0	45	－45	90	－90	135	－135	180
BS-LOSG	0.31	0.19	0.71	0.14	0.77	0.16	0.45	0.08
传统视线制导律	0.06	0.15	17.38	15.19	48.90	59.76	21.28	43.01

制导律	载机方位/(°)
制导律	0	45	－45	90	－90	135	－135	180
BS-LOSG	0.79	0.43	0.77	0.58	0.60	0.56	0.44	0.58
传统视线制导律	0.89	0.62	14.14	3.79	44.69	68.02	70.98	95.28

Design of improved line-of-sight guidance law based on aircraft visual information

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