ARAIM (Advanced Receiver Autonomous Integrity Monitoring) fault detection method based on pseudo-range measurement characteristic value extraction

A pseudo-range measurement and fault detection technology, which is applied in the field of satellite navigation, can solve the problems of lack of comparison of redundant observations and the inability of the separation algorithm to perform consistency detection, so as to reduce the positioning calculation process, ensure availability, and reduce data The effect of throughput

Active Publication Date: 2019-07-30
BEIHANG UNIV
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Problems solved by technology

Constellation faults are related faults caused by the space segment or the ground segment. This type of fault will affect the navigation signals or messages of multiple satellites, which leads to the consistency of the satellite pseudo-range measurements in the navigation constellation. There is no Redundant observations, so consistency detection cannot be performed using the solution separation algorithm
Constellation faults will cause the receiver to obtain consistent pseudorange measurements, lack of comparison of redundant observations, and fail to use receiver autonomous detection for fault detection
[0008] Therefore, in order to solve the real-time problem of the solution separation algorithm in the prior art, and the unavailability problem under the constellation fault condition, the present invention proposes an ARAIM fault detection method based on pseudorange measurement eigenvalue extraction

Method used

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  • ARAIM (Advanced Receiver Autonomous Integrity Monitoring) fault detection method based on pseudo-range measurement characteristic value extraction
  • ARAIM (Advanced Receiver Autonomous Integrity Monitoring) fault detection method based on pseudo-range measurement characteristic value extraction
  • ARAIM (Advanced Receiver Autonomous Integrity Monitoring) fault detection method based on pseudo-range measurement characteristic value extraction

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Embodiment 1

[0053] According to the present invention, in this embodiment, the receiver receives a large number of pseudo-range measurement values ​​within a certain period of time, and performs positioning calculation on all pseudo-range values. To solve the problem of real-time performance, an ARAIM fault detection method based on the extraction of pseudorange measurement feature values ​​is proposed.

[0054] Such as figure 2 The flow chart of the ARAIM fault detection method based on pseudorange measurement feature value extraction in the first embodiment of the present invention is shown. According to an embodiment of the present invention, an ARAIM fault detection method method based on pseudorange measurement feature value extraction includes the following methods step.

[0055] Step S101 , calculating the sum of the integrity risks under each failure mode, and the maximum value of the integrity risk value, that is, the integrity risk value corresponding to the worst failure mode...

Embodiment 2

[0078] This embodiment aims at the consistency of pseudorange measurement values ​​in constellation faults, and there is no problem of unavailability of ARAIM fault detection due to redundant observations. Such as Figure 4 The flow chart of the ARAIM fault detection method based on pseudorange measurement feature value extraction in the second embodiment of the present invention is shown. According to an embodiment of the present invention, an ARAIM fault detection method based on pseudorange measurement feature value extraction includes the following method steps .

[0079] Step S201, obtaining a covariance matrix of pseudorange measurement values.

[0080] Obtain N pseudorange measurement values, calculate the covariance of any two pseudorange measurement values, and obtain the covariance matrix of pseudorange measurement values.

[0081] The airborne receiver collects N pseudorange measurements {x 1 ,x 2 ,...x N}, calculate the covariance of pseudorange measurements b...

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Abstract

The invention provides an ARAIM (Advanced Receiver Autonomous Integrity Monitoring) fault detection method based on pseudo-range measurement characteristic value extraction. The method comprises the steps of computing integrity risk sum in each fault mode and the maximum value of integrity risk values in each fault mode; computing the number of fault modes through utilization of specific values between the integrity risk sum in each fault mode and an integrity risk of the maximum fault and taking the sample number of corresponding pseudo-range measurement values as the effective sample number;taking the specific value between certain time period T and the effective sample number as effective sample time; sampling pseudo-range measurement value samples collected by a receiver according tothe effective sampling time, thereby obtaining an effective pseudo-range measurement set; computing detection statistics through utilization of the effective pseudo-range measurement set, and carryingout integrity fault detection. According to the method, data processing quantity of an airborne receiver is reduced, load of the airborne receiver is reduced, and algorithm timeliness is improved.

Description

technical field [0001] The invention relates to the technical field of satellite navigation, in particular to an ARAIM fault detection method based on pseudorange measurement feature value extraction. Background technique [0002] Advanced Receiver Autonomous Integrity Monitoring (Advanced Receiver Autonomous Integrity Monitoring, ARAIM), as a new generation of satellite navigation airborne receiver integrity monitoring technology, has the ability to use multiple GNSS (Global Navigation Satellite System, global satellite navigation system) constellations, dual frequencies, As well as the capability of multi-fault monitoring, it can support vertical navigation below 200 feet (LPV-200), and the upgrade cost is low, and the performance is significantly improved. It is currently a hot research direction in the field of GNSS civil aviation applications. The ARAIM benchmark algorithm uses the data transmitted by the satellite navigation system as input, and performs navigation pos...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S19/23
CPCG01S19/23G01S19/20G01S19/24G06F17/16G06F17/18
Inventor 王志鹏朱衍波高臻方继嗣杜镜天
Owner BEIHANG UNIV
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