Three-dimensional Adaptive Sliding Mode Cooperative Guidance Law with Impact Time and Angle Constraints

doi:10.12382/bgxb.2022.1086

Abstract

Abstract:

Aiming at the problem of three-dimensional multiple missiles intercepting a maneuvering target simultaneously, a three-dimensional distributed cooperative guidance law considering time and space constraints. The proposed guidance law is based on fixed-time stable theory and adaptive sliding mode theory. Along the light-of-sight (LOS) direction, an improved robust adaptive cooperative guidance law is presented based on fixed-time consensus, which can drive a group of missiles to attack maneuvering target at a desired impact time without inherent chattering of sliding mode control. Along the direction vertical to the line-of-sight, a robust adaptive guidance law is proposed based on nonsingular fixed-time terminal sliding mode technique, which can drive missiles attack target with desired impact angle and avoid collision between missiles. Through the Lyapunov stability theory, the fixed-time stability of closed-loop system is demonstrated. The simulation results show that the proposed approach can be implemented to intercept maneuvering targets with desired impact time and impact angle.

Key words: distributed cooperative guidance law, fixed-time control theory, impact time and impact angle constraint, adaptive sliding mode, maneuvering target

CLC Number:

V249.1

WANG Yuchen, WANG Wei, LIN Shiyao, YANG Jing, WANG Shaolong, YIN Zhao. Three-dimensional Adaptive Sliding Mode Cooperative Guidance Law with Impact Time and Angle Constraints[J]. Acta Armamentarii, 2023, 44(9): 2778-2790.

Figures/Tables 11

References 26

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导弹	相对距离/ m	速度/ (m·s^-1)	视线倾角/ (°)	视线偏角/ (°)	期望终端视线倾角/ (°)	期望终端视线偏角/ (°)
M₁	9200	300	20	60	12	55
M₂	9800	350	-10	20	-5	25
M₃	10400	330	10	30	10	26
M₄	11000	420	-20	10	-25	15

导弹	相对距离/ m	速度/ (m·s^-1)	视线倾角/ (°)	视线偏角/ (°)	期望终端视线倾角/ (°)	期望终端视线偏角/ (°)
M₁	9200	300	20	60	12	55
M₂	9800	350	-10	20	-5	25
M₃	10400	330	10	30	10	26
M₄	11000	420	-20	10	-25	15

制导律	导弹	拦截时间/s	脱靶量/m	误差/ (°)	误差/ (°)
	M₁	40.006	0.0988	0.0643	0.0622
本文AITACGL	M₂	40.006	0.1275	0.0603	0.0624
	M₃	40.006	0.1518	0.0625	0.0607
	M₄	40.006	0.1243	0.0631	0.0629
	M₁	27.713	0.5914	0.4372	0.9221
FTCGL	M₂	27.713	0.3206	0.5837	0.5718
	M₃	27.713	0.0484	0.2943	0.5556
	M₄	27.713	0.2312	0.2658	0.3627

制导律	导弹	拦截时间/s	脱靶量/m	误差/ (°)	误差/ (°)
	M₁	40.006	0.0988	0.0643	0.0622
本文AITACGL	M₂	40.006	0.1275	0.0603	0.0624
	M₃	40.006	0.1518	0.0625	0.0607
	M₄	40.006	0.1243	0.0631	0.0629
	M₁	27.713	0.5914	0.4372	0.9221
FTCGL	M₂	27.713	0.3206	0.5837	0.5718
	M₃	27.713	0.0484	0.2943	0.5556
	M₄	27.713	0.2312	0.2658	0.3627