Real-time parallel determination method of high-sampling-rate navigation satellite clock correction

A navigation satellite, high sampling rate technology, applied in the field of precise positioning of global navigation satellite systems, can solve the problems of low efficiency of navigation satellite clock error and large amount of calculation, and achieve the effect of shortening calculation time, improving efficiency and easy operation

Active Publication Date: 2021-03-09
PLA STRATEGIC SUPPORT FORCE INFORMATION ENG UNIV PLA SSF IEU
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Problems solved by technology

[0005] The purpose of the present invention is to provide a real-time parallel determination method of high sampling rate navigation satellite clock differenc

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  • Real-time parallel determination method of high-sampling-rate navigation satellite clock correction

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Embodiment Construction

[0022] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0023] The present invention first screens a certain number of surveying stations evenly distributed in the world from the GNSS network, receives observation data with a high sampling rate of the surveying stations in real time, checks the quality of the data, and performs parallel preprocessing; secondly, each epoch of each surveying station Using the observation data of the ultra-fast predicted orbit, the ultra-fast earth rotation parameter file, the antenna model file, the tide correction file, the hardware delay correction file, etc., establish six responsibility chains to correct the error of the epoch information, and calculate the epoch station in parallel Finally, construct clock error estimation observation equation and normal equation sequentially, fix ambiguity in parallel, and solve algorithm equations in parallel to realize real-...

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Abstract

The invention relates to a real-time parallel determination method of a high-sampling-rate navigation satellite clock error, and belongs to the technical field of global navigation satellite system precision positioning. Observation data parallel preprocessing, epoch station star information parallel generation, ambiguity parallel fixation and normal equation parallel calculation are adopted in the clock error determination process. The method comprises the following steps: calculating a normal equation, carrying out matrix partitioning parallel inversion on a state transition matrix of Kalmanfiltering, carrying out Cholesky decomposition on the normal matrix of the normal equation, dividing the normal matrix into a plurality of blocks, and independently solving each block so that the whole calculation process can be subjected to parallel processing, and the method is simple and easy to operate. According to the method, the calculation time of the high-sampling-rate precision navigation satellite clock error is shortened, and the calculation efficiency of the high-sampling-rate real-time precision navigation satellite clock error is improved.

Description

technical field [0001] The invention relates to a real-time parallel determination method of high-sampling-rate navigation satellite clock error, belonging to the technical field of global navigation satellite system precision positioning. Background technique [0002] In the non-difference calculation mode, GNSS (Global Navigation Satellite System) real-time precise positioning requires high-precision real-time orbit and real-time clock difference. The ultra-fast forecast products released by the International GNSS Service (International GNSS Service, IGS) have no time delay. Taking the GPS system as an example, because the GPS satellite orbit determination model is very accurate, the theory is perfect enough, and its ultra-fast orbit prediction accuracy is better than 5cm, which can meet the requirements of real-time positioning, but the satellite clock error accuracy is poor, and its clock error prediction The accuracy can only reach 3ns, and the equivalent distance is 0....

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Application Information

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IPC IPC(8): G01S19/27G01S19/40
CPCG01S19/27G01S19/40
Inventor 李林阳赵冬青黄娴李健贾真张金辉冯绪王栋民李晋斐赖路广
Owner PLA STRATEGIC SUPPORT FORCE INFORMATION ENG UNIV PLA SSF IEU
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