Self-integrity monitoring method suitable for satellite-borne navigation receiver

A navigation receiver and integrity monitoring technology, applied in the field of satellite applications, can solve problems such as large resource occupation, achieve the effects of small calculation amount, avoid complex calculation, and simplify calculation amount

Active Publication Date: 2014-02-19
SPACE STAR TECH CO LTD
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0004] The technical solution problem of the present invention is: overcome the deficiencies in the prior art, provide a kind of RAIM improvement method that is suitable for space-borne navigation receiver, this method can overcome the problem that traditional odd-even space method occupies larger resources, improves navigation receiver Integrity Monitoring Efficiency

Method used

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  • Self-integrity monitoring method suitable for satellite-borne navigation receiver
  • Self-integrity monitoring method suitable for satellite-borne navigation receiver
  • Self-integrity monitoring method suitable for satellite-borne navigation receiver

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Experimental program
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Embodiment

[0069] In order to verify the on-orbit performance of the present invention, the ground and the simulation signal source are jointly tested, and the schematic diagram of the verification system built is as follows figure 2 :

[0070] RAIM is an algorithm embedded inside the receiver. The simulation signal source uses SimGEN simulation control software from Sprint Company to simulate and generate satellite-borne radio frequency signals. The simulation scene lasts for 8 hours. The original orbit data is set in the following table:

[0071] Table 1 Number of six tracks set

[0072] orbital major axis

[0073] Considering the actual on-orbit performance requirements and the characteristics of the orbit of the spacecraft, the selection of prior parameters in this experiment is designed according to the parameters in the table below.

[0074] Table 2 RAIM scenario design

[0075] scene / parameter

[0076] Within 8 hours, the running time used by the parity spa...

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Abstract

A self-integrity monitoring method suitable for a satellite-borne navigation receiver can reflect statistics detection amount of monitoring data quality by utilizing a pseudo-range information structure of the satellite-borne navigation receiver and detect faulted satellites according to the index requirements of a system and a distribution structure detection threshold obeyed by statistics amount. The self-integrity monitoring method suitable constructs the statistics detection amount of an odd-even space through QR decomposition of a primary observation array and based on the least square method, and carries out usability judgment, fault detection and fault identification in the odd-even space. The self-integrity monitoring method has higher response speed, saves more resources and is more suitable for satellite-borne application.

Description

technical field [0001] The invention belongs to the satellite application field and relates to a method for integrity monitoring of a navigation receiver carried by a satellite. Background technique [0002] The satellite-borne navigation receiver is an important part of the satellite measurement and control subsystem, mainly used for real-time positioning, timing, orbit determination, and relative positioning. Requirements such as high reliability have a crucial impact. However, due to the influence of factors such as ionospheric scintillation and navigation star anomalies, spaceborne navigation receivers may have pseudorange anomalies, which will cause integrity problems of navigation receivers. When the satellite introduces the navigation receiver data into the control loop for use, it is very likely that there will be deviations when the satellite applies the navigation data due to autonomous integrity problems. Especially when the satellite performs attitude orbit con...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S19/20G01S19/23
CPCG01S19/20G01S19/23
Inventor 隋叶叶柳涛王烁陆华岳富占
Owner SPACE STAR TECH CO LTD
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