An Antenna Tracking Method for Medium and Low Orbit Constellation Satellites

Abstract

The invention belongs to the field of tracking algorithms, and relates to an antenna tracking method based on medium and low orbit constellation satellites. The steps are as follows: Step 1: Calculate the position P of each constellation satellite within a certain period T on the basis of the root number of SATi orbits of each constellation satellite of the medium and low orbit constellation satellites. Step 2: Obtain the antenna carrier S 0 Current location PS 0 , combined with the orbital position set (T, P) of the constellation satellite SATi in step 1, the transit sequence of each SATi is formed. Step 3: Transit sequence through constellation satellite SATi (T u , I u , P u ) to calculate the antenna carrier S 0 Command angle A for constellation satellite SATi u . Step 4: According to the (T u , I u , P u , A u ) sequence, formulate the tracking strategy of the constellation satellites, and ensure the smooth operation of the antenna. The invention establishes a model according to the dynamics of constellation satellite operation to predict the orbit information of the satellite within a certain period of time, performs automatic and efficient antenna tracking functions, and involves the optimal tracking function 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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