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Satellite navigation signal tracking method based on maximum likelihood coherent integration

A satellite navigation signal and coherent integration technology, applied in satellite radio beacon positioning systems, measuring devices, instruments, etc., can solve the problems of long coherent integration time and lack of gain, so as to lengthen coherent integration time, maintain linearity, Performance-enhancing effects

Active Publication Date: 2018-06-15
北方雷科(安徽)科技有限公司
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Problems solved by technology

However, the amount of data calculation of this algorithm will increase exponentially with the extension of the integration time, which makes it impossible to make the coherent integration time very long, and the ideal gain cannot be obtained.

Method used

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  • Satellite navigation signal tracking method based on maximum likelihood coherent integration
  • Satellite navigation signal tracking method based on maximum likelihood coherent integration
  • Satellite navigation signal tracking method based on maximum likelihood coherent integration

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Embodiment Construction

[0032] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0033] The satellite navigation receiver can receive the signals transmitted by n navigation satellites at the same time, and the sum of the n navigation satellite signals is called the navigation satellite radio frequency signal S RF :

[0034]

[0035]

[0036] In the formula, the superscript j represents the satellite number; A represents the signal amplitude; C represents the spreading code, that is, the ranging code or the ranging code after BOC subcarrier modulation, including all codes in various navigation satellite systems, such as The C / A code and P code in the American GPS system, various codes in the Chinese Beidou system and the European Galileo system, etc., the code width of the ranging code is T C ; D represents the data code modulated on the ranging code and possible secondary coding, and the code width of the data code ...

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Abstract

A satellite navigation signal tracking method based on maximum likelihood coherent integration is disclosed. In a carrier tracking loop in a satellite navigation signal tracking stage, polarities of the added values of the coherent integration results in subsequent data code bit times are sequentially subjected to recursion according to a maximum likelihood principle after coherent integration results in the same data code bit time are added; the most reasonable data polarity path is determined; a maximum added value of coherent integration results in different data code bit times is obtained;total coherent integration time is lengthened to N complete data code bit times. The method disclosed in the invention can be used for lengthening the coherent integration time during tracking operation; sensitivity and stability of signal tracking can be improved and accuracy of observation quantities can be increased; a calculation amount remains linearly stable.

Description

technical field [0001] The invention belongs to the technical field of satellite navigation, in particular to a satellite navigation signal tracking method based on maximum likelihood coherent integration. Background technique [0002] Global Navigation Satellite System (GNSS, Global Navigation Satellite System) is a system with positioning, navigation, and timing functions consisting of three parts: the space part, the ground monitoring part, and the user receiver. It is used in navigation, aviation, surveying and mapping, and precise positioning. And other civilian fields, industrial fields and military fields. The space part of the satellite navigation system is composed of multiple satellites distributed on different orbital planes to ensure that the ground receiver can receive signals from enough satellites at any time and anywhere within the coverage area, and obtain accurate positions through calculations , time, speed and other information. [0003] At present, the...

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Application Information

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IPC IPC(8): G01S19/29G01S19/30
CPCG01S19/246
Inventor 不公告发明人
Owner 北方雷科(安徽)科技有限公司
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