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Completeness or adequateness monitoring method and device based on local area augmentation system (LAAS)

An integrity monitoring and enhancement system technology, applied in the field of satellite navigation, can solve problems such as failure detection, lack, and integrity risks, and achieve the effect of eliminating the influence of errors, improving accuracy, and ensuring accuracy

Inactive Publication Date: 2013-06-12
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, in the above-mentioned fault monitoring methods, the monitoring of faults is carried out through the model. However, due to the lack of fault independent sample values ​​(there are only 25,000 independent samples in the year at most), the fault model and its detection threshold Difficult to pinpoint accurately, resulting in some extremely rare failures that may go undetected, causing integrity risks

Method used

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  • Completeness or adequateness monitoring method and device based on local area augmentation system (LAAS)
  • Completeness or adequateness monitoring method and device based on local area augmentation system (LAAS)
  • Completeness or adequateness monitoring method and device based on local area augmentation system (LAAS)

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Embodiment 1

[0025] figure 1 It is a flow chart of the integrity monitoring method based on the local area augmentation system provided by Embodiment 1 of the present invention. The execution subject of this embodiment is the ground monitoring station in the local area augmentation system, such as figure 1 As shown, the integrity monitoring method of this embodiment includes:

[0026] Step 101, obtain the code pseudo-range observation value of the positioning satellite in the global navigation satellite system, and generate the code pseudo-range observation value residual according to the code pseudo-range observation value;

[0027] Among them, the ground monitoring station can select observable satellites from the global navigation satellite system as positioning satellites. This embodiment does not limit the number of positioning satellites. There can be one positioning satellite or multiple positioning satellites. Each embodiment of the present invention Both take n positioning satell...

specific Embodiment approach

[0039] This embodiment provides a specific implementation manner of step 101, specifically as follows:

[0040] First of all, this embodiment provides a theoretical expression of code pseudorange observation value, namely formula (1):

[0041] E=A'X'+V' (1)

[0042] Among them, E=[e 1 ... e i ... e n ] T , is an n×1-dimensional code pseudorange observation vector, e i is the code pseudo-range observation value corresponding to the i-th positioning satellite; is the error truth vector of n×1-dimensional code pseudorange observations, is the error true value of the code pseudo-range observation value corresponding to the i-th positioning satellite, which specifically includes systematic errors, such as: ionospheric delay, tropospheric delay, and ephemeris and star clock errors; accidental errors, such as: Errors caused by thermal noise and multipath; and gross errors, which mainly refer to errors caused by faults (for example: abnormally large ephemeris, star clock fail...

Embodiment 2

[0158] Figure 4 A schematic structural diagram of an integrity monitoring device based on a local area augmentation system provided in Embodiment 2 of the present invention, as shown in Figure 4 As shown, the integrity monitoring device of this embodiment includes: an acquisition generation module 21 , a statistics generation module 22 , a judgment module 23 and a processing and sending module 24 .

[0159] Wherein, the integrity monitoring device also includes a receiving module 20, which is used to receive signals from positioning satellites in the global navigation satellite system, wherein the positioning satellites can be controlled by the integrity monitoring device according to the terrain conditions where the system to which it belongs and the accuracy and integrity of the system. It is required to select a suitable satellite shading angle, and then select it from the visible satellites. The receiving module 20 is used to provide the received signal to the acquiring...

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Abstract

The invention provides a completeness or adequateness monitoring method and a device based on a local area augmentation system (LAAS). The method comprises the following steps: acquiring code pseudo range observed values of a positioning satellite in a global navigation satellite system to generate a code pseudo range observed value residual; generating fault monitoring statistic distributed in adecentralization manner according to the code pseudo range observed value and the code pseudo range observed value residual; judging whether the code pseudo range observed value has an error according to the fault monitoring statistic; and if so, calculating corresponding a code pseudo range gross error according to parameters distributed in a decentralization manner, correcting positioning parameters on the basis of the code pseudo range gross error, and sending the corrected positioning parameters to a vehicle-mounted user to monitor the completeness or adequateness of the global navigationsatellite system(LAAS) according to the corrected positioning parameters. The completeness or adequateness monitoring method and the device provided by the invention can monitor more faults in a moredetailed manner, correct the positioning parameters to eliminate fault influence, and improve the completeness or adequateness monitoring accuracy of the vehicle-mounted users.

Description

technical field [0001] The invention relates to the technical field of satellite navigation, in particular to a integrity monitoring method and device based on a local area augmentation system. Background technique [0002] The precision approach stage of civil aviation has extremely high requirements on the integrity performance of the satellite navigation system. Among them, the integrity risk value of category I precision approach is 2×10 -7 , the integrity risk value for Category II and Category III precision approaches is 2×10 -9 . In order to make the satellite navigation system meet the needs of civil aviation, the Federal Aviation Administration (Federal Aviation Administration; referred to as: FAA) and Stanford (Stanford) University and other research institutions have proposed the Local Area Augmentation System (Local Area Augmentation System; referred to as: LAAS). ). [0003] The Local Area Augmentation System (LAAS) is mainly composed of a ground monitoring s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S19/20
Inventor 张军朱衍波王志鹏薛瑞郑磊孙倩
Owner BEIHANG UNIV