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Satellite orbit perturbation compensation method for two-way satellite time transfer

A two-way time and satellite orbit technology, applied to clocks driven by synchronous motors, electronic timers, electric mechanical clocks, etc., can solve problems such as satellite two-way time transmission errors

Inactive Publication Date: 2013-10-09
中国航天科工集团第二研究院二〇三所
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a satellite orbit perturbation compensation method for satellite two-way time transfer to solve the problem of satellite two-way time transfer error caused by satellite orbit perturbation

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  • Satellite orbit perturbation compensation method for two-way satellite time transfer
  • Satellite orbit perturbation compensation method for two-way satellite time transfer
  • Satellite orbit perturbation compensation method for two-way satellite time transfer

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Embodiment Construction

[0042] The specific steps of a satellite orbit perturbation compensation method for satellite two-way time transfer are:

[0043] first step Building a two-way time transfer system for orbital perturbation compensation satellites

[0044]The orbital perturbation compensation satellite two-way time transfer system includes: the satellite two-way time transfer system and the orbital perturbation compensation device 6 . Among them, the satellite two-way time transfer system includes: master atomic clock, master earth station 2, slave atomic clock and slave earth station 3; orbit equipment compensation device includes: distance calculation module 7, control amount calculation module 8, pulse adjustment module 9 and data Compensation module 10.

[0045] The orbital perturbation compensation satellite two-way time transfer system is realized by connecting the orbital perturbation compensation device 6 in series between the atomic clock and the earth station 3 in the traditional...

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Abstract

The invention discloses a satellite orbit perturbation compensation method for two-way satellite time transfer. The distance between an earth station and a satellite is confirmed by setting up an orbit perturbation compensation satellite two-way time transfer system and a distance calculating module (7), 1PPS phase control words are confirmed through a control quantity calculating module (8), pulses per second are adjusted through a pulse adjusting module (9), measured deviation generated by a 1PPS adjusting operation is compensated through a data compensation module (10), and therefore the compensation of satellite orbit perturbation in the two-way satellite time transfer system is completed. According to the method, the changes of time signal transmission delay caused by the satellite orbit perturbation in a forward direction and a reverse direction are counteracted, the influence of the satellite orbit perturbation is greatly lowered, and the precision of two-way satellite real-time time transfer is improved.

Description

technical field [0001] The invention relates to a satellite orbit perturbation compensation method, in particular to a satellite orbit perturbation compensation method for satellite two-way time transfer. Background technique [0002] The satellite two-way time transfer method is a high-precision time transfer technology. It uses geosynchronous communication satellites to transfer time to transfer timing modulation information between earth stations, and realizes time information interaction between stations and high-precision time difference measurement. This method has been developed since the last century Since it was put forward in the 1960s, it has been widely valued. Especially in recent years, the progress of satellite communication and pseudo-code spread spectrum technology has further improved the accuracy of the satellite two-way time transfer system, and the cost and volume have been continuously reduced. At present, the satellite two-way time transfer has become a...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G04G7/00
Inventor 张升康王宏博王学运杨军冯克明
Owner 中国航天科工集团第二研究院二〇三所