A satellite fault identification method, device and software receiver
A satellite failure and identification method technology, applied in the field of satellite navigation and positioning, can solve the problems of low time complexity, low space complexity, high time complexity and high space complexity, and achieve low time complexity, low space complexity, The effect of increasing the recognition degree of the minimum pseudo-range jump
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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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