Cooperative Guidance Method of Leader and Seeker-less Follower Flight Vehicles

doi:10.12382/bgxb.2023.0678

Abstract

Abstract:

A three-dimensional cooperative guidance method is presented to investigate the problem of leader and seeker-less follower flight vehicles attacking on the targets by sector coverage. An impact time control guidance law with fixed-time convergence is presented for the leader to reach a target at desired impact time. A sector coverage configuration against target with dynamic self-adjusting center and radius is proposed with the leader as baseline. Finally,on the basis of the desired converge sector, the cooperative guidance law is given for the followers to reach the target simultaneously with multi-directional sector blockade. A theoretical analysis is given to prove the stability of the proposed method. The simulated results show that the proposed method can be used to make all the flight vehicles hit the target at appointed impact time, and the leader and the seeker-less followers can form the coverage situation towards the target.

Key words: leader-follower flight vehicles, cooperative guidance, seeker-less, muti-directional coverage, impact time

CLC Number:

TJ765.3

LI Guofei, TANG Qingpu, WU Yunjie. Cooperative Guidance Method of Leader and Seeker-less Follower Flight Vehicles[J]. Acta Armamentarii, 2023, 44(11): 3436-3446.

Figures/Tables 16

Fig.1 Relative motion relationship between the ith flight vehicle and the target

Fig.2 Flight configuration for R0≫ρ

Fig.3 Sphere-shaped coverage configuration for R0≈ρ

Fig.4 LOS parallel coordinate system

Fig.5 Communication topology of leader and follower flight vehicles

Table 1 Initial conditions of flight vehicles

飞行器	(x,y,z)/m	θ/(°)	ψ_V/(°)
主飞行器	(5000, 8500,7600)	-10	10
从飞行器1	(4000,8000,7000)	-10	10
从飞行器2	(4500,8000,7000)	-10	10
从飞行器3	(4000,8500,7600)	-10	10

Fig.6 Trajectory curves of flight vehicles

Fig.7 Trajectory curves of flight vehicles after t=42s

Fig.8 Distances among flight vehicles

Fig.9 Impact time error of leader

Fig.10 Response of cooperative variable ξi

Fig.11 Response of cooperative variable ηi

Fig.12 Distance between flight vehicle and target

Fig.13 Three-axis accelerations of leader in the proposed method

Fig.14 Three-axis accelerations of leader under guidance law (6)

Fig.15 Three-axis acelerations of followers

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