Accuracy analysis of LEO satellites orbit prediction for precise position service

doi:10.11947/j.AGCS.2022.20210473

Abstract

Abstract: Precise orbit prediction of low earth orbit (LEO) satellites is one of the important technologies for LEO navigation enhancement system. In this paper, we use a variety of algorithms to realize orbit prediction under different mission requirements. For LEO orbit prediction on ground, algorithm 1 processes orbit determination and prediction simultaneously. In algorithm 2, the discrete orbit points are fitted dynamically and then orbit integral is extrapolated. The average predicted user range error (URE) accuracy of GRACE-C satellite in 5, 10 and 15 minutes is 5.25, 5.67, 6.25 cm, that of HY2A satellite is 7.83, 8.69, 9.66 cm, that of SWARM-A satellite is 8.88, 9.22, 9.63 cm, and that of SWARM-B satellite is 8.49, 8.98, 9.63 cm. For LEO orbit prediction on board with limited calculation conditions, an orbit integral extrapolation algorithm with a single orbit point and simple dynamic models is used. Because this method mainly considers the perturbation of the Earth's central gravity and non-spherical gravity, the order of the Earth's gravity field has a significant impact on the accuracy of orbit prediction. 60 order gravity field is selected for LEO satellite with an average height of 500 km and 30 order gravity field is selected for LEO satellite with an average height of 1000 km, which can realize the prediction accuracy of about 10 cm for 10 min arc length.

Key words: LEO navigation enhancement system, orbit prediction, dynamic fitting, orbital integral

CLC Number:

P228

YUAN Junjun, LI Kai, TANG Chengpan, ZHOU Shanshi, HU Xiaogong, CAO Jianfeng. Accuracy analysis of LEO satellites orbit prediction for precise position service[J]. Acta Geodaetica et Cartographica Sinica, 2022, 51(5): 640-647.

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