Satellite fault identification method and device and software receiver

A satellite fault and identification method technology, applied in the field of satellite navigation and positioning, can solve the problems of low space complexity, high time complexity, high space complexity, low time complexity, etc., and achieves low space complexity and low time complexity. , the effect of increasing the minimum pseudo-range jump recognition

Active Publication Date: 2020-03-24
HUBEI SANJIANG SPACE XIANFENG ELECTRONICS&INFORMATION CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] Aiming at at least one defect or improvement requirement of the prior art, the present invention provides a satellite fault identification method, device and software receiver, combining the respective advantages of the least squares residual algorithm and the parity space check algorithm, with time complexity The characte

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  • Satellite fault identification method and device and software receiver
  • Satellite fault identification method and device and software receiver
  • Satellite fault identification method and device and software receiver

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Embodiment 1

[0085] figure 2 The specific algorithm flow of the satellite fault identification method proposed by the present invention is described in more detail, as shown in Figure 2, the specific flow is as follows:

[0086] (1) After the software receiver receives the satellite signal through the antenna, firstly start the storage program in the FLASH in the receiver, realize the bit synchronization and frame synchronization of the satellite signal, analyze the effective satellite ephemeris information, and decode the satellite navigation message, Finally, the satellite number, satellite pseudo-range and other information are obtained. Calculate the pitch angle and azimuth angle of the satellite through the above information, and delete the satellites whose pitch angle is less than 10 degrees.

[0087] (2) After the effective satellites are selected, the least squares algorithm is used for rough positioning, and the converged receiver position x, y, z and receiver clock error d are ...

Embodiment 2

[0104] This embodiment provides a satellite fault identification device, which includes:

[0105] The creation unit is used to collect the converged receiver position data and receiver clock error when performing satellite positioning based on the least squares algorithm, construct an observation matrix H according to the above receiver position data and receiver clock error, and perform normalization on the observation matrix H Intersecting triangular decomposition to obtain the standard orthogonal matrix Q; use the odd-even space algorithm to decompose the above-mentioned standard orthogonal matrix Q to generate the even-even space matrix Q p ;

[0106] The first calculation unit is used for the above parity space matrix Q p Perform matrix operations to obtain the slope of each satellite involved in positioning and extract the maximum slope value Slope max ;

[0107] The first calculation unit is used to calculate according to the above-mentioned maximum slope value Slope...

Embodiment 3

[0111] This embodiment provides a software receiver, which includes at least one processor and at least one memory, wherein a computer program is stored in the memory, and when the computer program is executed by the processor, the processor executes the satellite fault identification method described above A step of. The types of the processor and the memory are not specifically limited, for example: the processor can be a microprocessor, a digital information processor, an on-chip programmable logic system, etc.; the memory can be a volatile memory, a non-volatile memory, or a combination thereof, etc. .

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Abstract

The invention discloses a satellite fault identification method, a satellite fault identification device and a software receiver, and relates to the technical field of satellite navigation and positioning. The method comprises the following steps: acquiring receiver position data and clock correction, constructing an observation matrix according to the receiver position data and the clock correction, and decomposing the observation matrix by adopting an odd-even space algorithm to generate an odd-even space matrix; performing matrix operation on the odd-even space matrix to obtain the slope ofeach satellite participating in positioning, and extracting the maximum slope value; calculating a similar radial error protection value of the positioning satellite based on the maximum slope valueand the false alarm detection value, and when the similar radial error protection value is not less than a preset value, calculating a check statistic according to satellite deviation data corresponding to the odd-even space matrix; detecting whether a satellite participating in positioning has a fault or not according to the verification statistics, the false alarm detection value and a preset threshold factor. The method has the characteristics of low time complexity and low space complexity, and can adapt to satellite fault detection and identification of normal flight and high dynamic flight.

Description

technical field [0001] The invention belongs to the technical field of satellite navigation and positioning, and more specifically relates to a satellite fault identification method, device and software receiver. Background technique [0002] In the calculation of user position, velocity and time information (Position Velocity Time, PVT) of the software receiver, it is necessary to output measurement information such as user longitude, latitude, altitude and velocity in real time. In order to improve the navigation accuracy of the receiver, the satellite must be monitored in real time. However, changes in multi-constellation visible satellites in a complex environment are likely to cause system failures, resulting in unstable detection performance. Therefore, it is necessary to design an algorithm for receiver monitoring and identifying faulty satellites (RAIM, Receiver Autonomous Integrity Monitoring). When the error of observation information exceeds the threshold, the al...

Claims

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Application Information

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IPC IPC(8): G01S19/20
CPCG01S19/20
Inventor 宋波周昭辉刘晓飞
Owner HUBEI SANJIANG SPACE XIANFENG ELECTRONICS&INFORMATION CO LTD
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