Receiver autonomous integrity monitoring (RAIM) method used for satellite navigation system

A satellite navigation system and integrity monitoring technology, applied in the field of satellite navigation, can solve problems such as the inability to meet the needs of multi-satellite fault detection and elimination, the increase of multiple satellites, etc., so as to solve the problem that multi-satellite faults are difficult to identify and have a high troubleshooting rate. , the effect of good robustness

Active Publication Date: 2010-08-18
BEIHANG UNIV
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Problems solved by technology

[0033] When using the least squares residual method or the parity space method for troubleshooting, they are mainly for single-satellite faults, which cannot meet the needs of multi-satellite fault detection and elimination
In the multi-constellation integrated satellite navigation system, the probability of simultaneous failure of multiple satellites is greatly increased, and this phenomenon cannot be ignored in navigation and positioning

Method used

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  • Receiver autonomous integrity monitoring (RAIM) method used for satellite navigation system
  • Receiver autonomous integrity monitoring (RAIM) method used for satellite navigation system
  • Receiver autonomous integrity monitoring (RAIM) method used for satellite navigation system

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Embodiment Construction

[0064] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0065] The present invention provides a receiver autonomous integrity monitoring method for a satellite navigation system, the flow chart of the method is as follows figure 1 shown.

[0066] In a certain observation epoch, the receiver observes multiple satellites in multiple combined constellations at the same time. Now it is necessary to monitor the integrity of the receiver autonomously. It is necessary to judge whether there is a fault in the satellite combination according to the positioning results. If there is a fault, The faulty satellites are then eliminated to obtain a constellation of fault-free satellites.

[0067] Step 1: Parameter configuration.

[0068] Configure the estimated maximum number of faulty satellites, fault_num, according to the number of combined constellation satellite systems, and configure the maximum number of repeat ...

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Abstract

The invention discloses a receiver autonomous integrity monitoring method used for a satellite navigation system, which is an RAIM method based on multi-satellite fault detection and removal and achieve the fault removal goal by a mode of acquiring constellations comprising the most fault-free satellites. In the method, fault-free individuals are formed by adopting coding, initialization and individual detection; then an individual comprising the most fault-free satellites is obtained by optimal search, and the individual is used as an initial result; when terminal condition is satisfied, the individual is the final result of RAIM. The method has simple realization, high fault removal efficiency and good robustness, not only can carry out single-fault detection and removal but also can carry out multi-fault detection and removal, is not only suitable for single system but also is suitable for multisystem and effectively achieve the goal of carrying out multi-satellite fault detection and removal in the RAIM method.

Description

technical field [0001] The invention belongs to the field of satellite navigation, and in particular relates to a receiver autonomous integrity monitoring method for a satellite navigation system based on multi-satellite fault detection and elimination. Background technique [0002] Integrity refers to the ability to provide timely warnings to users when the system cannot be used for normal navigation and positioning, or the system error exceeds the limit. Integrity is important for many applications when using satellite navigation and positioning systems, but it is critical for aerospace because users are traveling at high speeds and can quickly veer off course. Since the satellite fault monitoring is carried out through the operation control part of the satellite navigation system itself, the alarm time is relatively long, usually within 15 minutes to a few hours, which cannot meet the needs of aviation navigation, so it is necessary to quickly monitor satellite faults at ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S19/23
Inventor 张晓林陈灿辉霍航宇
Owner BEIHANG UNIV
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