A GNSS Mobile Satellite Orbit Determination Method Constrained by Additional Clock Difference Model

Abstract

The invention discloses a GNSS (Global Navigation Satellite System) maneuvering satellite orbit determination method with additional clock error model constraint, comprising the steps of: acquiring observation data of an observation station; 2) eliminating observation data after maneuvering, and performing dynamic precision orbit determination calculation on arc sections before and during maneuvering; 3) extracting estimation values of a satellite clock error before maneuvering, an ambiguity, a receiver clock error during maneuvering, a ZTD (Zenith Tropospheric Delay) and an ISB (Inter-SystemBias) parameter; 4) establishing a clock error forecasting model based on the estimation value of the satellite clock error before maneuvering; 5) fixing the receiver clock error, the ambiguity without cycle slip, the ZTD and the ISB parameter, adding constraint of the clock error forecasting model, and performing orbit determination calculation on a satellite orbit during maneuvering by adoptinga reverse dynamic precision single-point positioning method; and 6) iteratively solving position parameters of the maneuvering satellite at the current epoch until the position parameters are converged, and performing solving at the next epoch. According to the GNSS maneuvering satellite orbit determination method of the invention, through introduction of the satellite clock error forecasting model constraint, the correlation between satellite orbit radial direction and the satellite clock error can be greatly weakened, and the orbit radial direction orbit determination precision of the maneuvering satellite is effectively improved.

Description

technical field [0001] The invention belongs to the field of global navigation satellite systems (GNSS), and in particular relates to a technology for improving orbit determination accuracy during satellite maneuvering. Background technique [0002] The precise orbit of GNSS satellites is a prerequisite for using satellites for navigation and positioning applications. Due to the influence of perturbation force, the satellite will gradually deviate from its predetermined orbit during its in-orbit operation. When the deviation exceeds the preset range, it is necessary to apply a maneuvering thrust to the satellite to make the satellite return to the preset orbit. my country's Beidou-2 satellite navigation system adopts the GEO / IGSO / MEO mixed constellation layout mode. Due to its static characteristics, GEO satellites need to perform frequent orbital maneuvers to maintain a fixed position in space. The maneuvering frequency is usually every three to five Once a week, the Beidou...

AI Technical Summary

Problems solved by technology

For the precise orbit determination of GNSS satellites during maneuvering, there are mainly two methods: one is the dynamic model error compensation method that models the maneuvering force in dynamic orbit determination. The advantage of this method is that it can obtain continuous The disadvantage of satellite orbits is that the maneuvering force is usually difficult to accurately model, and the satellite orbit accuracy obtained during the maneuvering period is generally on the order of tens of meters, and before and after maneuvering as a continuous processing arc, the orbit accuracy of the normal arc will be affected by the maneuvering force model. Another method is to use the kinematics orbit determination method during the maneuver. The advantage of this method is that the satellite orbit is only determined by the observation information during the maneuver and is not affected by the maneuver force error. However, the accuracy of this method is limited to Geometric observation conditions of satellites. Since GNSS satellites are medium and high-orbit satellites, the geometric configuration of satellite observations by ground stations is poor. In particular, there is a strong correlation between satellite radial and clock error, and the orbit determination accuracy is difficult to meet the requirements of navigation and positioning. need

[0003] Based on the above analysis, the currently commonly used GNSS satellite orbit determination method during maneuvering is difficult to obtain satellite orbits with high precision, making the maneuvering satellite data unable to be used for positioning services, especially for my country's Beidou satellite navigation system, the frequent orbital maneuvering of GEO satellites will seriously Affects the availability of system services

Images