A Calculation Method Applicable to Pseudo-Lite Position

Abstract

The present invention proposes a calculation method suitable for pseudolite positions, including: judging whether it is a pseudolite system; if so, reading the coordinate constant of the pseudolite system; calculating normalized time; calculating the average angular velocity of the satellite; calculating respectively Mean anomaly angle, deviating anomaly angle, true anomaly angle, ascending node angular distance, perturbation correction item at the time of signal transmission; calculate ascending node angular distance after perturbation correction, satellite vector length and orbit inclination angle; calculate pseudolites Position on the orbital plane; calculate the right ascension of the ascending node at the time of signal launch; calculate the position of the pseudolite in the ground-fixed coordinate system. The invention only modifies the basic earth parameters in the satellite position algorithm, so that the space position of the pseudolite can be calculated by using four ephemeris parameters, and solves the problem that the original broadcast ephemeris cannot represent the coordinates of ground stationary objects.

Description

technical field [0001] The invention relates to the technical field of pseudolite positioning, in particular to a calculation method suitable for pseudolite positions. Background technique [0002] The navigation message contains the time and position information of the satellite, which is an indispensable starting data for navigation and positioning. However, since the pseudolite is generally fixed at a known position on the ground or near the ground as a "ground satellite", unlike GPS satellites that operate according to the designed orbit, the original ephemeris model cannot express the position of the pseudolite. [0003] At present, the pseudolite coordinates are not calculated through the ephemeris parameters of the navigation message, but are directly written into the navigation message after a simple transformation. This custom navigation message format is not compatible with the navigation parameter extraction algorithm of the original GPS navigation message format...

AI Technical Summary

Problems solved by technology

[0004] In view of the shortcomings of the prior art described above, the purpose of the present invention is to provide a calculation method suitable for pseudolite positions, so as to solve the problem that the GPS broadcast ephemeris cannot describe the position of stationary objects relative to the ground in the prior art

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