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Clock maintenance method for satellite-borne computer navigation filtering

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

Active Publication Date: 2020-07-17
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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  • Clock maintenance method for satellite-borne computer navigation filtering
  • Clock maintenance method for satellite-borne computer navigation filtering
  • Clock maintenance method for satellite-borne computer navigation filtering

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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 invention discloses a clock maintenance method for satellite-borne computer navigation filtering. Aiming at the conditions that clocks of different single machines on a 1553B bus entering a satellite platform are not synchronous and the data frequency is inconsistent with the calculation period of a satellite-borne computer, a protection mechanism of a navigation measurement data access systemis constructed by maintaining a time axis of navigation filtering, so that the stability and effectiveness of a navigation filtering algorithm are ensured. The method can overcome the bounce or errordata of GNSS measurement data timestamps and the data invalidation or data non-update phenomenon. Compared with the method of directly using GNSS measurement data to determine the orbit, the method of the invention has the advantage that the orbit output result of the navigation filtering algorithm is more reliable.

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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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