Three-dimensional Adaptive Fixed-time Multi-missile Cooperative Guidance Law

doi:10.12382/bgxb.2023.0640

Abstract

Abstract:

An adaptive fixed-time cooperative guidance law is proposed for multiple missiles simultaneously attacking a maneuvering target in three-dimensional space. A 3-D missile-target dynamics model is established, and the adaptive guidance law are designed based on the line of sight (LOS) direction and its vertical direction. This ensures that the remaining flight time and normal velocity converge consistently within a fixed time. The adaptive guidance law are employed to track the motion parameters of maneuvering targets, thus enhancing the stability of multiple missile system and its strike accuracy against the maneuvering targets. The convergence conditions of the multiple missile system are improved, and the designed guidance law possess the capability to constrain the attack time. Saturated functions are introduced into the guidance law to avoid system oscillations caused by the sign function. The effectiveness of the proposed fixed-time cooperative guidance law and its robustness against communication topology switches are validated through simulation experiment. The experimental results indicate that, compared to the guidance law designed in the reference literatures, the proposed guidance law exhibit rapid system convergence and high accuracy.

Key words: multi-missile cooperative guidance, fixed-time, adaptive law, maneuvering target

CLC Number:

TJ765.3

YU Hang, LI Qingyu, DAI Keren, LI Haojie, ZOU Yao, ZHANG He. Three-dimensional Adaptive Fixed-time Multi-missile Cooperative Guidance Law[J]. Acta Armamentarii, 2024, 45(8): 2646-2657.

Figures/Tables 8

Fig.1 Schematic diagram of simultaneous attack of multiple missiles

Fig.2 Three-dimensional dynamic diagram of missile

Fig.3 The communication topology G of missiles

Table 1 Initial states of each missile and target

导弹与目标	位置/m	初速/ (m·s^-1)	纵向面垂直于视线方向航向角误差/rad	横向面垂直于视线方向航向角误差/rad
导弹1	(3000,0,3000)	450	-0.09	0.02
导弹2	(7000,-2000,0)	440	0.10	-0.07
导弹3	(0,0,0)	350	0.11	0.05
导弹4	(-7000,0,0)	350	-0.15	0.01
导弹5	(-3000,1000,-1000)	400	0.12	-0.10
目标	(15000,15000,15000)

Fig.4 Simulated results of Eq. (14)-(16) of adaptive distributed guidance law

Fig.5 Simulation results of Eq.(41) of guidance law with attack time constraint

Fig.6 Comparison of adaptive guidance laws Eq.(14)- (16) with those in Ref.[11] under the same initial conditions

Fig.7 Robustness simulation results of guidance laws Eq.(14)-(16) against topology switching

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