A method for detecting GNSS satellite orbital maneuver

A satellite orbit and maneuvering technology, which is applied in satellite radio beacon positioning systems, measuring devices, radio wave measuring systems, etc., can solve the problem of regional observation network misjudging satellite maneuvering, ionospheric delay, satellite maneuvering and abnormal values, etc. question

Active Publication Date: 2018-09-14
INST OF GEODESY & GEOPHYSICS CHINESE ACADEMY OF SCI
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Problems solved by technology

[0007] The purpose of the present invention is to overcome the problems in the prior art that are only applicable to regional observation networks, misjudgment of satellite maneuvers, and when the clock error of the receiver is eliminated, it is easily affected by ionospheric delay, satellite maneuvers and abnormal values, or only It is suitable for the defects and problems of the post-processing mode, and provides a method for detecting GNSS satellite orbit maneuvers based on broadcast ephemeris and global reference network to realize all-weather satellite maneuvers and provide a feasible idea for future real-time satellite maneuvers

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  • A method for detecting GNSS satellite orbital maneuver
  • A method for detecting GNSS satellite orbital maneuver
  • A method for detecting GNSS satellite orbital maneuver

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Embodiment

[0170] see figure 1 , a method for detecting GNSS satellite orbital maneuvering, the method comprises the following steps:

[0171] Step 1: Obtain GNSS observations and broadcast ephemeris of global stations through files or the Internet;

[0172] Step 2: Divide the global GNSS observation network into six subnets (which can be adjusted according to actual needs). Since time is relative, select a station equipped with an atomic clock for each subnet as a reference station, and other stations as a reference station, and then divide each subnet into threads to perform the third and fourth steps;

[0173] Step 3: Construct the linearized ionosphere-depleted combined smooth pseudorange observation equation for each station in the subnetwork:

[0174]

[0175] In formula (1), represents the pseudorange residual, Indicates the unit vector of the line of sight direction, Δs indicates the error of the broadcast ephemeris in the three directions of radial dr, tangential da, an...

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Abstract

The invention provides a method for detecting GNSS satellite orbital maneuver. The method comprises the steps of: acquiring global observation station GNSS observation values and broadcast ephemeris through files or networks; dividing a global GNSS observation network into a plurality of sub-networks and selecting an observation station with an atomic clock for each sub-network as a base station,the other observation stations being reference stations; building a linearized ionosphere-free combination smooth pseudo-range observation equation for each observation station in the sub-networks, and then performing satellite maneuver judgment through two threads. The method can perform reliable all-weather single-epoch maneuver detection on all satellites and can provide a feasible thought forfuture real-time satellite maneuver.

Description

technical field [0001] The invention belongs to the technical field of "geodesy" in the discipline of "surveying and mapping science and technology", and in particular relates to a method for detecting GNSS satellite orbital maneuvers, which is mainly applicable to improving the orbit determination accuracy of mobile satellites and the effective utilization of mobile satellites. Background technique [0002] As a key technology of Global Navigation Satellite System (GNSS), satellite orbit determination has been widely studied to eliminate or weaken the factors that affect its accuracy and stability. Additionally, GNSS users expect highly accurate and reliable orbit products. However, determining satellite maneuvers is important, whether for precise orbit determination with postprocessing, or using predicted orbits. In the case of maneuvering, separate sub-arcs need to be set up for maneuvering satellites in the precise orbit determination of the multi-day solution. In real...

Claims

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Application Information

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IPC IPC(8): G01S19/25G01S19/37
CPCG01S19/258G01S19/37
Inventor 袁运斌叶飞张宝成潭冰峰欧吉坤
Owner INST OF GEODESY & GEOPHYSICS CHINESE ACADEMY OF SCI
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