Antenna tracking method based on low and medium orbit constellation satellites

Abstract

The invention belongs to the field of a tracking algorithm, and relates to an antenna tracking method based on low and medium orbit constellation satellites. The antenna tracking method comprises thesteps of first, calculating the position of each constellation satellite within a certain period based on the number of orbits of each constellation satellite SATi of the low and medium orbit constellation satellites; second, obtaining the current position PS0 of an antenna carrier S0, and forming a transit sequence of each constellation satellite SATi by combining an orbit position set (T, P) ofthe constellation satellite SATi in the step one; third, calculating an instruction angle Au of the antenna carrier S0 for the constellation satellite SATi according to the transit sequence (Tu, Iu, Pu) of the constellation satellite SATi; and fourth, formulating a tracking strategy of the constellation satellites according to a sequence (Tu, Iu, Pu, Au) of each constellation satellite SATi, and ensuring the smooth operation of the antenna. The antenna tracking method builds a model according to the constellation satellite operation dynamics to predict orbit information of each satellite within a period of time, carries out an automatic and efficient antenna tracking function and involves a function of tracking optimization of multiple constellation satellites.

Description

technical field [0001] The invention belongs to the field of tracking algorithms, and in particular relates to an antenna tracking method based on medium and low orbit constellation satellites. Background technique [0002] For high-orbit satellites, the running speed is slow and the orbit drift is also slow. Therefore, the satellite orbit can be predicted by using the orbital elements to complete high-precision guidance measurement. Orbit drift is also fast, and the method of prior orbit prediction cannot guarantee the guidance accuracy. The real-time solution method cannot be solved analytically due to the high nonlinearity of the mechanical equations of each model, and the iterative method requires a large amount of calculation. Therefore, the present invention predicts the orbit information within a certain period of time based on the number of constellation satellites, and then calculates the antenna carrier command angle under the premise of ensuring real-time performa...

AI Technical Summary

Problems solved by technology

[0002] For high-orbit satellites, the running speed is slow and the orbit drift is also slow. Therefore, the satellite orbit can be predicted by using the orbital elements to complete high-precision guidance measurement. Orbit drift is also fast, and the method of orbit prediction in advance cannot guarantee the guidance accuracy. The real-time solution method cannot be solved analytically due to the high nonlinearity of the mechanical equations of each model, and the iterative method requires a large amount of calculation.

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