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 ...

Examples

Embodiment Construction

[0092]The principle of the present invention: Step 1 can directly determine parameters such as the position holding period according to external input conditions such as the time required for measuring the orbit and the requirement for position holding accuracy, avoiding the blindness of parameter selection; , the calculation process requires parameters such as the sun’s celestial longitude, the relative Julian day, and the moment of the vernal equinox, which need to be provided on the ground or on the satellite. The calculation process of the meridian longitude control quantity uses a coordinate rotation search algorithm, and the solution process needs iterations; Step 3 is Calculate the ignition parameters of each electric thruster: ignition start time and ignition duration. The calculation process needs the orbit element control quantity obtained in step 2 as input, as well as parameters such as electric thruster thrust, thrust projection coefficient, and spacecraft weight; s...

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 ...

Examples

Embodiment Construction

[0092]The principle of the present invention: Step 1 can directly determine parameters such as the position holding period according to external input conditions such as the time required for measuring the orbit and the requirement for position holding accuracy, avoiding the blindness of parameter selection; , the calculation process requires parameters such as the sun’s celestial longitude, the relative Julian day, and the moment of the vernal equinox, which need to be provided on the ground or on the satellite. The calculation process of the meridian longitude control quantity uses a coordinate rotation search algorithm, and the solution process needs iterations; Step 3 is Calculate the ignition parameters of each electric thruster: ignition start time and ignition duration. The calculation process needs the orbit element control quantity obtained in step 2 as input, as well as parameters such as electric thruster thrust, thrust projection coefficient, and spacecraft weight; s...

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