Synchronous orbit electric propulsion position maintenance and angular momentum unloading joint control method

Abstract

The invention relates to a synchronous orbit electric propulsion position maintenance and angular momentum unloading joint control method comprising the steps that a position maintenance cycle Ts, a control cycle Tc and orbit measurement time Tm are determined; the control cycle Tc is total time including completion of one time of the ignition process of all thrusters respectively; the orbit measurement time Tm is obtained in a way that time required by orbit measurement is rounded up to an integer of integer orbit cycles; one position maintenance cycle Ts includes one orbit measurement process Tm and multiple control cycles Tc: orbit element control variables, including inclination angle control variable vectors (deltaix, deltaiy), eccentricity control variable vectors (deltaex, deltaey) and a flat longitude drift rate control variable deltaD, of each control cycle are calculated before starting of each position maintenance cycle Ts; the electric thruster ignition parameters of each control cycle are determined, and the ignition parameters include ignition duration and an ignition position; and an electric thruster rotating angle is determined according to the electric thruster ignition parameters and angular momentum unloading quantity before starting of each control cycle Tc.

Description

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

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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