Cooperative guidance method for seeker-less missile and beacon aircraft

doi:10.23919/JSEE.2026.000094

Abstract

Abstract:

To solve the problem of the precise strike for seeker-less missile, a cooperative guidance method of seeker-less missile and the beacon aircraft is proposed. Firstly, the guidance law considering the miss distance and line-of-sight (LOS) angle constraint is designed to achieve the precise strike on the target and satisfy the LOS angle constraint. On this basis, the tangential load of the beacon aircraft is designed to ensure that the remaining flight time (time-to-go) for the missile and the beacon aircraft converge to the same value within a finite time, thus the seeker-less missile can indirectly strike the target precisely. Simulation results validate the effectiveness of the proposed method in addressing the problem of cooperative strike on target, and compared with the cooperative guidance method in reference, the proposed cooperative guidance method is better in strike accuracy and demand overload.

Key words: seeker-less missile, beacon aircraft, cooperative guidance law, time-to-go

Zhengxin TAO, Shifeng ZHANG. Cooperative guidance method for seeker-less missile and beacon aircraft[J]. Journal of Systems Engineering and Electronics, 2026, 37(2): 687-696.

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Aircraft	Parameter	Value
Missile	$[{X_\text{m}},{Y_\text{m}}]$/km	$[0.0,0.0]$
	$ V_\text{m}^0/({\text{m}}/{\text{s}}) $	$250$
	$ {\phi _\text{m}} /(^\circ)$	$50 $
	$\phi _{{r_1}}^\text{d}/(^\circ)$	$15 $
Beacon	$[{X_\text{b}},{Y_\text{b}}]/{\text{km}}$	$[6.0,5.5]$
	$ V_\text{b}^0 /({\text{m}}/{\text{s}})$	$70$
	$ {\phi _\text{b}}/(^\circ) $	$60 $
	$\phi _{{r_2}}^\text{d}/(^\circ)$	$20 $
Target	$[{X_\text{T}},{Y_\text{T}}]/{\text{km}}$	$[8.0,7.1]$

Aircraft	Parameter	Value
Missile ${M_1}$	Initial position/km	$[0.0,0.0] $
	Velocity/(m/s)	$250$
	Flight path angle/(°)	$50$
	Desired LOS angle/(°)	$15 $
Missile ${M_2}$	Initial position/km	$[1.0,16.0 ]$
	Velocity/(m/s)	$250$
	Flight path angle/(°)	$ - 70 $
	Desired LOS angle/(°)	$ - 30 $
Target	$[{X_\text{T}},{Y_\text{T}}]/{\text{km}}$	$[8.0 ,7.1 ]$

Aircraft	Type of noise	Deflection range ($3\sigma $)
Missile	Velocity of missile ${V_\text{m}}$	$[ - 3,3]{\text{ m/s}}$
	LOS angle between beacon and target $ {\phi _{{r_1}}} $	$ [ - 5{\text{% }},5{\text{% }}] $
	Position of missile $[{X_\text{m}},{Y_\text{m}}]$	$ [ - 5,5]{\text{ m}} $
Beacon aircraft	Velocity of beacon ${V_\text{b}}$	$[ - 1,1]{\text{ m/s}}$
	LOS angle between beacon and target $ {\phi _{{r_2}}} $	$ [ - 5{\text{% }},5{\text{% }}] $
	Position of beacon $[{X_\text{b}},{Y_\text{b}}]$	$ [ - 1,1]{\text{ m}} $

Type of miss distance	Average/m	Standard deviation/m
Missile-Target	$1.62$	$0.74$
Missile-Beacon	$1.65$	$0.79$
Beacon-Target	$0.79$	$0.41$

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