High-precision real-time vibration removal algorithm for instantaneous semi-major axis of satellite orbit

Abstract

The invention provides a satellite orbit semi-major axis vibration removal scheme based on discrete Fourier transform and least square fitting, constructs a vibration removal semi-major axis calculation method suitable for satellite orbit phase control, and establishes a method combining orbit forecasting, numerical value averaging and numerical value fitting, and a high-precision real-time vibration removal algorithm for the satellite orbit semi-major axis is further designed. According to the method, the concepts of numerical value averaging and numerical value fitting are adopted, and a primary vibration-removing semi-major axis is given by utilizing numerical value averaging; and further de-oscillation is carried out by using a discrete Fourier transform and numerical fitting method. According to the specific implementation method, orbit forecasting is carried out through an orbit dynamics model, so that high-precision absolute position and speed information of a satellite in a long enough time period is obtained, finally, the instantaneous semi-major axis of the satellite orbit is obtained through calculation, and the instantaneous semi-major axis in a certain period is utilized to obtain an initial vibration-removed semi-major axis through numerical averaging; inherent frequency of residual short-period oscillation is extracted through discrete Fourier transform; and finally, according to the inherent frequency of the residual short-period oscillation, a numerical fitting method is used to calculate and obtain a satellite orbit de-vibration average semi-major axis. The method has the advantages of high navigation precision and good real-time performance.

Description

technical field [0001] The present invention provides a devibration algorithm for the instantaneous semi-major axis of a high-precision real-time satellite orbit, which relates to the situation that the satellite's high-precision orbit is known within a certain period of time, and the available orbit is lengthened through a short-term orbit forecast, and the instantaneous semi-major axis of the orbit is The segmental numerical average of the major axis is first devibration, the discrete Fourier transform extracts the natural frequency of the short-period oscillation left over from the first devibration semi-major axis, and the numerical fitting of the first devibration semi-major axis removes the residual short-period oscillation term, The long-term term and the long-period term are retained, and finally the average semi-major axis of the satellite orbit after eliminating the short-period oscillation is obtained. It belongs to the field of navigation technology. Background t...

AI Technical Summary

Problems solved by technology

If the short-period oscillation term in the instantaneous semi-major axis is not eliminated, the number of times the orbit phase control system will be controlled is much higher than it should be, which will greatly increase fuel consumption and increase the cost of the satellite

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