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Integrity processing method based on least square residual error edge detection

A technology of least squares and edge detection, applied in the application field of satellite navigation systems, can solve the problems of inability to apply geographical environment, prone to false rejection, poor satellite spatial structure, etc., to improve availability, improve availability, and reduce false rejection. rate effect

Active Publication Date: 2016-05-04
郑州威科姆科技股份有限公司
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is to provide a integrity processing method based on the least squares residual edge test. The present invention solves the problem that the traditional RAIM least squares residual sum method has strict requirements on the geographical environment and the structure of the observation satellite, and cannot It is applied to the situation where the geographical environment is not good and the satellite space structure is poor, and the faulty satellite identification is only based on the satellite pseudo-range residual, which is prone to technical problems of false detection

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  • Integrity processing method based on least square residual error edge detection

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Embodiment Construction

[0032] The present invention focuses on taking the BD+GPS dual-mode as an example to introduce a faulty star elimination method based on the least square residual edge test, and the pseudo-range observations of each satellite are regarded as equal-weight observations.

[0033] Such as figure 1 As shown, an integrity processing method based on the least squares residual edge test includes the following steps:

[0034] Step 1. The receiver antenna captures and tracks the signal from the satellite, and eliminates abnormal satellites according to the navigation message;

[0035] Step 2. According to the number of received satellites, perform carrier-to-noise ratio and elevation angle fusion to select satellites, and eliminate abnormal satellites;

[0036] Step 3. According to the number of different observation satellites, set the maximum number of satellites NT that can be eliminated, the maximum threshold value Td of the residual error, and the error threshold value бT under th...

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Abstract

The invention discloses an integrity processing method based on least square residual error edge detection. The method comprises steps that 1), the least square residual error corresponding to each satellite is calculated; 2), the least square residual errors corresponding to the satellites are ordered, and the front N1 least square residual errors and the back N2 least square residual errors are selected from the ordered ones and are taken as pre-selected fault satellite detection objects; 3), the pre-selected fault satellites determined in the step 2) are sequentially eliminated one by one, user state least square equation solution is carried out, and corresponding post-detection unit weight mean errors are calculated according to the solved residual errors; and 4), the (N1+N2) post-detection unit weight mean errors acquired in the step 3) through calculation are ordered, and a satellite corresponding to the least root mean square of one least square residual error is the fault satellite. According to the method, strict RAIM integrity guarantee is not required, tests prove that the integrity processing method based on least square residual error edge detection can accurately identify the fault satellite, and the integrity processing method based on least square residual error edge detection is a simple, rapid and effective fault satellite identification method for user clients.

Description

technical field [0001] The invention relates to the technical field of satellite navigation system application, in particular to an integrity processing method based on least square residual edge inspection. Background technique [0002] The integrity of satellite navigation originally originated from the requirements of civil aviation users for high reliability of the system. Certain errors in satellites will cause ranging errors, reducing the safety and integrity of users. Especially for some system failures, it takes half an hour or even several hours for ground monitoring stations to find out. As a result, many aviation users will receive and use wrong information from one or several failed satellites, thus making the positioning of these users deviate. At present, its location is tens of kilometers away, which is extremely harmful to navigation safety. It is not allowed for civil aviation applications and must be taken seriously. With the rapid development of the glob...

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Application Information

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IPC IPC(8): G01S19/20
CPCG01S19/20
Inventor 贾小波王倩倩邹世合吴淑琴赵平丽
Owner 郑州威科姆科技股份有限公司
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