Rough synchronization method for satellite bidirectional time comparison

A two-way time comparison and time comparison technology, applied in the field of coarse synchronization, can solve problems such as poor independence and susceptibility to interference, and achieve the effect of improving autonomy and independence

Inactive Publication Date: 2013-12-18
中国航天科工集团第二研究院二〇三所
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Problems solved by technology

[0004] The purpose of the present invention is to provide a coarse synchronization method for two-way time comparison of satellites...

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  • Rough synchronization method for satellite bidirectional time comparison
  • Rough synchronization method for satellite bidirectional time comparison

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Embodiment Construction

[0027] The specific steps of a coarse synchronization method for satellite two-way time comparison are:

[0028] The first step is to build a satellite two-way time comparison system

[0029] Satellite two-way time comparison system, including: satellite two-way time comparison master station and satellite two-way time comparison slave station. Among them, the satellite two-way time comparison master station includes: master atomic clock, master time comparison modem and master satellite receiving and receiving earth station; satellite two-way time comparison slave station includes: slave atomic clock, slave time comparison modem, and satellite sending and receiving earth station station and coarse synchronizer. Coarse synchronization device, including: 1PPS splitter, phase micro-step module, two-to-one switch and control module.

[0030] At the satellite two-way time comparison main station, the 10MHz and 1PPS signals output by the main atomic clock are input to the referen...

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Abstract

The invention discloses a rough synchronization method for satellite bidirectional time comparison. A satellite bidirectional time comparison system is established, rough clock correction is measured, a phase micro-leap module (11) is used for adjusting a 1PPS phase and realizing rough synchronization, and lastly rough synchronization of 1PPS between two stations is realized. According to the rough synchronization method for satellite bidirectional time comparison, a rough synchronizer (9) is in series connection with a satellite bidirectional time comparison slave station (2) to directly measure the initial clock correction of the 1PPS of a master atomic clock (3) and the 1PPS of a slave atomic clock (6), the phase micro-leap module (11) is used for adjusting the 1PPS of the slave station, and therefore rough alignment of master time and slave time of satellite bidirectional time comparison is realized; a control module (13) is used for measuring and processing the clock correction and controlling the operation time sequence of devices; rough synchronization of the time of the master station and the time of the slave station is realized under the condition that other means are not needed, and therefore the autonomy and independence of the satellite bidirectional time comparison system are improved.

Description

technical field [0001] The invention relates to a rough synchronization method, in particular to a rough synchronization method for satellite two-way time comparison. Background technique [0002] Satellite two-way time comparison is one of the most accurate time transfer technologies at present. It uses geosynchronous communication satellites to transfer time to transmit timing modulation information between earth stations, and realizes high-precision time information interactive comparison between stations. It is widely used in international standards Time (TAI / UTC) comparison, standard time traceability, and high-precision remote time synchronization. When performing two-way time comparison of satellites, it is necessary to roughly synchronize the time pulse (1PPS) of the atomic clocks of the ground stations participating in the comparison, so as to reduce the asymmetry of the two-way comparison link and further improve the accuracy of the two-way comparison. [0003] At...

Claims

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Application Information

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IPC IPC(8): G04R40/06G04R20/04H04B7/185
Inventor 张升康王宏博杨军冯克明
Owner 中国航天科工集团第二研究院二〇三所
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