Sliding window loop tracking method and device

A loop tracking and sliding window technology, applied in the field of satellite navigation applications, can solve the problems of inability to effectively process satellite signals, inability to locate and navigate, etc.

Inactive Publication Date: 2016-05-11
SPACE STAR TECH CO LTD
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  • Abstract
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  • Claims
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Problems solved by technology

This makes traditional navigation receivers unable to effectively process satellite signals

Method used

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  • Sliding window loop tracking method and device
  • Sliding window loop tracking method and device
  • Sliding window loop tracking method and device

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Embodiment Construction

[0057] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0058] In the traditional loop, in order to enhance the filtering effect, reduce noise and improve tracking accuracy, the coherent integration time should be extended as much as possible, but the length of the coherent integration time is affected by the navigation data bit jump. For example, the D2 navigation message rate broadcast by B3I is 500bps, so the longest coherent integration time of the loop can only be 2ms, so the tracking accuracy cannot be further...

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Abstract

The invention provides a sliding window loop tracking method and a device. According to the technical scheme of the invention, firstly, based on locally generated sine and cosine copied carriers, stripping the carrier of a satellite signal to obtain a first branch signal and a second branch signal; secondly, stripping the pseudo codes of the first and second branch signals according to local pseudo codes and conducting the low-pass filtering and the coherent integration to obtain the coherent integral values of a front branch, an immediate branch and a rear branch; thirdly, accumulating multiple adjacent integral values of the immediate branch in the non-coherent manner and conducting the phase demodulation of a carrier loop to obtain the phase difference between a local carrier and an input carrier; fourthly, adopting the non-coherent lead-lag magnitude method, estimating the integral values of the front and rear branches to obtain the phase difference between a local pseudo code and an input pseudo code; fifthly, filtering the phase difference between the local pseudo code and the input pseudo code, and adjusting the frequency of the local pseudo code according to the filtering result; sixthly, filtering the phase difference between the local carrier and the input carrier within a long non-coherent accumulation period of time in the sliding window manner, and adjusting the frequency of the sine copied carrier and the frequency of the cosine copied carrier according to the filtering result.

Description

technical field [0001] The invention relates to the application field of satellite navigation, in particular to a sliding window loop tracking method and device based on a non-coherent accumulating phase detector, which can be used for satellite signal tracking in high dynamic and weak signal environments, and can improve the receiver's ability to navigate Tracking accuracy of satellite signals. Background technique [0002] With the development needs of national defense and military, the dynamic (speed) of advanced weapons and equipment such as missiles and fighter jets is getting higher and higher. Acceleration or even jerk, which will cause a large Doppler shift and its rate of change. In addition, with the development of the application field of satellite navigation and the improvement of modernization, the requirements for the tracking accuracy of the receiver are also getting higher and higher. This makes the traditional navigation receiver unable to effectively proc...

Claims

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Application Information

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IPC IPC(8): G01S19/30G01S19/29G01S19/37
CPCG01S19/30G01S19/29G01S19/37
Inventor 薛志芹王君帅周同杨燕娇董启甲
Owner SPACE STAR TECH CO LTD
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