Method for determining track and clock error of navigation satellite

Abstract

The invention belongs to the field of satellite navigation, and particularly relates to a method for determining track and a clock error of a navigation satellite. According to the method, the clock error of the satellite is expressed by a multi-item model, data observed at different times within the same time window is corresponding to a joint clock error parameter, so that inter-satellite one-way pseudo-range observation data and observation data of a ground monitoring state can be adjusted to determine the track and the clock error of the navigation satellite by employing a known method. Compared with a known method only employing ground monitoring station data to determine the track and clock error of the navigation satellite, the track and clock error determination accuracy of the navigation satellite can be remarkably improved under the condition of a regional monitoring state; and compared with a known method employing inter-satellite pseudo-range and observation quantity to determine an orbit and a method employing pseudo-range difference observation quantity to perform time synchronization, original one-way pseudo-range observation data is directly employed, epoch naturalization is not needed to be performed on inter-satellite pseudo-range observation data and so-called pseudo-range and / or pseudo-range difference observation quantity is not needed to be calculated, higher data utilization rate is achieved, and self-consistent track and clock error result can be obtained. By the method, the time delay deviation of inter-satellite link transceiving equipment relativeto hardware of navigation signal equipment also can be estimated.

Description

technical field [0001] The invention belongs to the field of satellite navigation, and in particular relates to a method for determining the orbit and clock error of a navigation satellite. Background technique [0002] As we all know, global or regional navigation satellite systems (such as GPS, Galileo, GLONASS, BDS-2 / 3, QZSS, etc.) consist of an operation control center deployed on the ground, monitoring stations and several satellites operating in earth orbit. Common navigation satellite orbits include MEO (altitude about 20,000km), GEO and IGSO (altitude about 36,000km) orbits, and orbits at other altitudes are also possible. Each of the satellites is equipped with a high-stability atomic clock and a navigation signal device that sends a positioning signal to the user. The positioning signal includes a carrier wave that the user can measure and a ranging code (usually a pseudo-code) modulated on it. random code) and navigation message. The user receiver can receive th...

AI Technical Summary

Problems solved by technology

If the data received by one of the satellites in a certain time frame is lost or abnormal, then the two satellites cannot construct the pseudorange and or pseudorange difference observations corresponding to the time frame, so the data utilization rate is low

The existing methods of using pseudorange and observations to determine the orbit of navigation satellites or using pseudorange difference observations to synchronize satellite time cannot solve the hardware delay deviation of inter-satellite link equipment relative to navigation signal equipment

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