Method and system for realizing real-time orbit determination for single satellite navigation positioning system

Abstract

The invention provides a method and a system for realizing real-time orbit determination for a single satellite navigation positioning system. The method comprises steps that a should-be-switched-to orbit determination work mode is determined according to a present orbit determination work mode and the available star number of the satellite navigation positioning system, and switching operation is carried out; the observation data of the satellite navigation positioning system is transferred from an earth-fixed coordinate system to an orbit coordinate system through coordinate transformation; the observation data after coordinate transformation is inputted to a Kalman filter, time update for the state quantity of the Kalman filter is carried out, and orbital element one-step forecast is acquired; measurement update for the state quantity of the Kalman filter is carried out by utilizing the observation data of the satellite navigation positioning system. The Kalman filtering method on the basis of a dynamic orbit model and the system are employed, being closer to practical modeling, switching among different orbit determination modes can be realized, demands of high precision real-time orbit determination and autonomous satellite navigation can be satisfied, and the method and the system can be applied to multiple types of satellite navigation positioning systems such as GPS, GLONASS, second-generation Beidou and GALILEO.

Description

technical field [0001] The invention belongs to the field of satellite navigation and positioning, and in particular relates to a single-system real-time orbit determination realization method and system based on satellite navigation and positioning system measurement. Background technique [0002] GPS / GLONASS is a satellite navigation system capable of timing and ranging space rendezvous positioning, which can provide all-weather, continuous, real-time, high-precision three-dimensional position, three-dimensional velocity and time information to global users. The observation modes of satellite autonomous navigation are mainly divided into two modes: celestial navigation and radio ranging navigation. Celestial navigation uses the measurement of the optical and magnetic characteristics of natural celestial bodies to realize satellite autonomous navigation. Radio ranging navigation uses space-borne radio measuring instruments to obtain the measured value of the distance of the...

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to: overcome the simple modeling of the comprehensive dynamic orbit determination method in the prior art, the inability to be sufficiently close to the actual model, and the relatively low real-time accuracy of the existing space-borne satellite navigation and positioning system that uses a simple geometric method for single-point positioning to provide a real-time and high-precision satellite navigation orbit determination method

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