Accurately tracking hypersonic gliding vehicles via an LEO mega-constellation in relay tracking mode

doi:10.23919/JSEE.2023.000078

Abstract

Abstract:

In order to effectively defend against the threats of the hypersonic gliding vehicles (HGVs), HGVs should be tracked as early as possible, which is beyond the capability of the ground-based radars. Being benefited by the developing mega-constellations in low-Earth orbit, this paper proposes a relay tracking mode to track HGVs to overcome the above problem. The whole tracking mission is composed of several tracking intervals with the same duration. Within each tracking interval, several appropriate satellites are dispatched to track the HGV. Satellites that are planned to take part in the tracking mission are selected by a new derived observability criterion. The tracking performances of the proposed tracking mode and the other two traditional tracking modes, including the stare and track-rate modes, are compared by simulation. The results show that the relay tracking mode can track the whole trajectory of a HGV, while the stare mode can only provide a very short tracking arc. Moreover, the relay tracking mode achieve higher tracking accuracy with fewer attitude controls than the track-rate mode.

Key words: target tracking, mega-constellation, hypersonic gliding vehicle (HGV), sensor selection, observability analysis

Zhao LI, Yidi WANG, Wei ZHENG. Accurately tracking hypersonic gliding vehicles via an LEO mega-constellation in relay tracking mode[J]. Journal of Systems Engineering and Electronics, 2024, 35(1): 211-221.

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Modes	Tracking arc length/s	Attitude control required by the satellite	Measurement accuracy/ arcsec	Required priori information about the target
Relay tracking mode	>500	Once in each tracking interval	5−10	Rough initial motion state
Stare mode	<30	−	5−10	−
Track-rate mode	>500	Real-time	30−60	Accurate trajectory

Parameter	Value
h/km	821.820
i/(°)	98.7
T	200
P	10
F	1

Parameter type	Item	Value
Initial condition of the target tracking	Initial state error	$\Delta { {{{\boldsymbol{x}}} }_0}$= [10 km; 10 km; 10 km; 10 m/s; 10 m/s; 10 m/s]
	Process noise matrix	$\begin{gathered} { { {\boldsymbol{Q} } } } = {\rm{diag} }\left( {\left[ {q_1^2,q_1^2,q_1^2,q_2^2,q_2^2,q_2^2} \right]} \right) \\ {\text{where } }{q_1}{\text{ is } }{10^{ { { - 2} } } }{\text{, } }{q_2}{\text{ is } }1{ {\text{0} }^{ { { - 5} } } } \\ \end{gathered}$
	Simulation duration/s	500
Initial condition of the infrared sensor	Measurement period/s	1
	Measurement error/arcsec	5
	FWHM/(°)	5
	Maximal detectable distance/km	5000
Initial condition of the satellite selection	Virtual FWHM/(°)	50
Initial condition of the satellite selection	Tracking interval/s	30

Satellite selection criterion	Average computing time of a single satellite selection/s
Length of PTA	0.0286
CN	0.2293
Det(Y) based on RIM	0.1072
Det(Y) based on the proposed method	0.0347

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