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A Clock Maintenance Method for Spaceborne Computer Navigation Filter

A space-borne computer and clock technology, applied in navigation calculation tools, radio wave measurement systems, satellite radio beacon positioning systems, etc., can solve the problems of space-borne computer calculation cycle mismatch, and has not yet been made public

Active Publication Date: 2022-03-04
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Specifically, there are many types of calculation periods for spaceborne computers, and the most common one is 0.5 seconds; the most common update frequency for GNSS receiver measurement data is 1Hz, which does not match the calculation period of spaceborne computers.
At present, there are no published patents or papers and other research results for the clock maintenance method of spaceborne computer navigation filtering

Method used

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  • A Clock Maintenance Method for Spaceborne Computer Navigation Filter
  • A Clock Maintenance Method for Spaceborne Computer Navigation Filter
  • A Clock Maintenance Method for Spaceborne Computer Navigation Filter

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Experimental program
Comparison scheme
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Embodiment Construction

[0037] 1) Judgment on the validity of track measurement data

[0038] There are three logical criteria 1a), 1b) and 1c) in the data validity judgment in step (1), if the three logical criteria are satisfied simultaneously, the GNSS receiver data is valid, and the flag bit Flag=1 is set; Otherwise, Flag=0 is set .

[0039] 1a) Determine the positioning flag of the GNSS receiver test data. When the "location flag" is resolved to be valid, it is determined that the receiver data "meets the available requirements"; when the positioning flag is other values, it is judged that the receiver data is "unavailable".

[0040] 1b) Judging whether the valid flags and track data of the GNSS measurement data conform to the track characteristics; and eliminate wrong measurement data. Orbital data meet the needs of orbital characteristics, and "satisfy the threshold judgment formula" is as follows

[0041] 6.79×10 6 m≤||r||≤7.05×10 6 m

[0042] and

[0043] 7.46×10 3 m / s≤||v||≤7.75×10 ...

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Abstract

The present invention is a clock maintenance method for navigation filtering of a satellite-borne computer. Aiming at the situation that the clocks between different single machines on the 1553B bus in the satellite platform are not synchronized, and the data frequency is inconsistent with the calculation cycle of the satellite-borne computer, the time axis of navigation filtering is maintained. , Construct the protection mechanism of the navigation measurement data access system to ensure the stability and effectiveness of the navigation filtering algorithm. The method can overcome the phenomenon that the GNSS measurement data time stamp jumps or wrong data, and the data is invalid or the data is not updated. Compared with directly using the GNSS measurement data to determine the orbit, the present invention has a more reliable orbit output result of the navigation filtering algorithm.

Description

technical field [0001] The invention relates to a clock maintenance method for satellite-borne computer navigation filtering. More specifically, it is a situation where the clocks of different stand-alone machines on the 1553B bus in the satellite platform are not synchronized, and the data frequency is inconsistent with the calculation period. By maintaining the time axis of navigation filtering and constructing the protection of the navigation measurement data access system mechanism. The method can overcome the jumping or wrong data of the GNSS measurement data time stamp, and the phenomenon that the data is invalid or the data is not updated, and can make the orbit output result of the navigation filtering algorithm more stable. The invention relates to a clock maintenance method for navigation filtering of a spaceborne computer, which belongs to the application field of spacecraft engineering technology. Background technique [0002] For satellites in low-Earth orbit,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S19/23G01C21/20G06F1/12
CPCG01S19/23G01C21/20G06F1/12
Inventor 杨盛庆贾艳胜王文妍杜耀珂陈筠力朱郁斐王禹刘美师
Owner SHANGHAI AEROSPACE CONTROL TECH INST