Low-orbit satellite anchoring-based autonomous orbit determination method of Beidou navigation constellation

Abstract

The invention relates to a low-orbit satellite anchoring-based autonomous orbit determination method of Beidou navigation constellation. The low-orbit satellite anchoring-based autonomous orbit determination method comprises the steps of performing inter-satellite bidirectional pseudo-range observation by a Beidou inter-satellite link, sending Beidou inter-satellite bidirectional observation quantity information and prior position and speed information of a local satellite under a geocentric inertial coordinate system to an adjacent Beidou navigation satellite by the inter-satellite link; receiving Beidou downlink observation quantity information sent from a low-orbit satellite and autonomous orbit determination data of the low-orbit satellite; performing error correction on pseudo-range between Beidou double satellites and pseudo-range between the Beidou satellite and the low-orbit satellite, and eliminating a transceiving equipment error and a link error; and unifying the corrected pseudo-range between the Beidou satellite and the low-orbit satellite and the pseudo-range between the Beidou satellite and the low-orbit satellite to the same moment, decoupling inter-satellite distance and relative clock error in the bidirectional observation information between Beidou satellites, taking the low-orbit satellite pseudo-range, the distance between the Beidou satellites and the relative clock error as observation quantity, and calculating position, speed and clock error of the Beidou satellite by an extended Kalman filtering method.

Description

technical field [0001] The invention relates to the technical field of autonomous orbit determination of navigation constellations, in particular to a method for autonomous orbit determination of Beidou navigation constellations based on low-orbit satellite-based anchoring. Background technique [0002] At present, the Beidou navigation constellation autonomous orbit determination adopts two methods: 1. The autonomous orbit determination based on the ground anchor station, the ground operation control station or the ground mobile station anchors the Beidou constellation, which is used as a "pseudo-satellite" with known coordinates and the navigation constellation Other satellites complete Ka-band two-way precision measurement and time synchronization, and use their prior coordinates to establish a connection between the Beidou constellation and the earth; 2. The navigation constellation is completely autonomous in orbit determination, relying only on the high-precision mid-hi...

AI Technical Summary

Problems solved by technology

Among them, the methods introduced in Document 1 and Document 3 need the support of artificial satellites at the Earth-Moon Lagrangian point, and the engineering cost is very high; the method introduced in Document 2 has poor autonomous navigation accuracy, and the method introduced in Document 4 belongs to the semi-autonomous positioning of navigation constellations. rail approach, no support off the ground

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