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Real-time overbounding method for civil aviation satellite navigation integrity augmentation system errors

A satellite navigation and augmentation system technology, which is applied in the field of satellite navigation augmentation systems, can solve the problems of error model parameter amplification, no model validity verification, etc., and achieve the effect of improving usability

Pending Publication Date: 2018-12-21
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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Problems solved by technology

[0014] The purpose of the present invention is to provide a real-time envelope method of civil aviation satellite navigation integrity enhancement system error, to solve the non-stationary and time-dependent processing of pseudo-range error in the prior art, resulting in insufficient independent samples for the above-mentioned model The validity of the model is verified; and the shortage of independent samples for the envelope calculation leads to the problem of excessive amplification of the error model parameters

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  • Real-time overbounding method for civil aviation satellite navigation integrity augmentation system errors

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[0036] In order to make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are only exemplary and not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessarily obscuring the concept of the present invention.

[0037] The pseudorange error of the satellite navigation enhancement system has the following three characteristics:

[0038] 1. Non-stationarity: As one of the main error sources of GBAS, the multipath error is related to the satellite elevation angle, so the statistical characteristics of the pseudorange error cannot remain stable during the change of the satellite elevation angle;

[0039] 2. Time correlation: Due ...

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Abstract

The invention discloses a real-time overbounding method for civil aviation satellite navigation integrity augmentation system errors. According to the method, a time sequence model is utilized to analyze the temporal correlation of pseudo-range errors, fat-tail error samples without the temporal correlation are obtained, and overbounding calculation is performed after normalization processing is performed on the fat-tail error samples through a generalized autoregressive conditional heteroscedasticity (GARCH) model, so that a stationarity model of temporal correlation errors is established; and a confidence upper limit of a standard deviation of the pseudo-range errors is determined, optimal pseudo-range error sequence length is determined, and therefore processing of the uncertainty and error non-stationarity of the model is realized. Through the method, an extra integrity risk cannot be introduced; and due to tighter overbounding, the protection level calculated in real time is lowerthan that calculated through a traditional method, and consequently the availability of a satellite navigation augmentation system is improved.

Description

Technical field [0001] The invention relates to the technical field of satellite navigation enhancement systems, in particular to a real-time envelope method for enhancing the integrity of civil aviation satellite navigation systems. Background technique [0002] The GBAS (Ground Based Augmentation System) of satellite navigation includes satellite subsystem, ground subsystem and airborne subsystem. In the airborne subsystem, airborne users (usually referred to as aircraft) approach and take off. The distance between the user and the monitoring station of the ground subsystem is relatively close, and the positioning error in space and time is used (that is, the positioning error of the airborne user and the monitoring station within a certain space and time range is basically the same), and the airborne user The accuracy of navigation and the ability to monitor integrity can be improved based on the pseudorange correction value and integrity information broadcast by the monitorin...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S19/20
CPCG01S19/20
Inventor 方堃蒋欣张展霍航宇
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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