A joint control method of electric propulsion position keeping and angular momentum unloading in synchronous orbit

Abstract

The invention relates to a joint control method of position maintenance and angular momentum unloading of synchronous orbit electric propulsion, comprising: determining the position maintenance period Ts, the control period Tc and the orbit measurement time Tm; The total time; the orbit measurement time Tm is obtained by rounding up the time required for orbit measurement to an integer number of orbit periods; a position keeping period Ts should include an orbit measurement process Tm and several control periods Tc: before the start of each position keeping period Ts , to calculate the control quantities of orbital elements in each control period: inclination control quantity vector (Δix, Δiy), eccentricity control quantity vector (Δex, Δey) and longitude drift rate control quantity ΔD; determine the electric thruster ignition parameters for each control period , the ignition parameters include ignition duration and ignition position; before the start of each control cycle Tc, the rotation angle of the electric thruster is determined according to the ignition parameters of the electric thruster and the angular momentum unloading amount.

Description

technical field [0001] The invention relates to a joint control method for electric propulsion position maintenance and momentum wheel unloading of a synchronous orbit satellite, and belongs to the technical field of satellite orbit attitude dynamics and control. Background technique [0002] Geosynchronous Orbit (GEO, Geosynchronous Orbit) refers to the satellite orbit in which the position relative to the earth is basically unchanged when the satellite is running, and is synchronous with the rotation of the earth. In fact, due to the effects of various perturbation factors, geosynchronous orbit satellites cannot always guarantee a constant position relative to the earth, and it is necessary to continuously exert control force to keep the relative position of the satellite within the required range. The position keeping operation of geostationary orbit satellite is actually the control of satellite inclination, eccentricity and longitude. [0003] At present, the position ...

AI Technical Summary

Problems solved by technology

[0006] (1) The relationship between position keeping control parameters (position keeping period, control period, etc.) and position keeping accuracy is not considered, and there is blindness in the selection of control parameters

[0007] (2) In each position holding period, the ignition parameters of the electric thruster in different control periods need to be calculated recursively, so that the ignition parameters of each control period are not the same, and the solution is complicated

[0008] (3) The demand for angular momentum unloading is not considered, and the influence of the angular momentum unloading performed by the electric thruster on position maintenance is not considered

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