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Position keeping method of electric propulsion stationary orbit satellite

A technology of geostationary orbit and electric propulsion, applied in the field of geostationary orbit satellite position maintenance, electric propulsion geostationary orbit satellite position maintenance field

Inactive Publication Date: 2014-09-03
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a method for maintaining the position of an electric propulsion geostationary orbit satellite, which can more accurately solve the problem of position drift of the electric propulsion geostationary orbit satellite in the east-west and north-south directions

Method used

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  • Position keeping method of electric propulsion stationary orbit satellite
  • Position keeping method of electric propulsion stationary orbit satellite
  • Position keeping method of electric propulsion stationary orbit satellite

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Embodiment

[0092] The present invention provides a method for maintaining the position of an electric propulsion geostationary orbit satellite. The satellite has entered the synchronous orbit, and the initial longitude and orbit inclination are within the position maintaining interval. The position keeping method described will overcome the influence of space perturbation force on longitude and latitude, and keep the geostationary orbit satellite near the nominal position.

[0093] The four electric thrusters of the electric propulsion system are installed on the back floor of the satellite, such as figure 1 are shown as northwest thruster 1, northeast thruster 2, southwest thruster 3 and southeast thruster 4, respectively, the tangential, normal and radial components of the four thrusters relative to the center of mass in the orbital coordinate system are l, respectively T =0.4m, l N =1.5m, l R =1.6m. In this embodiment, n=3 is taken as an example. Correspondingly, the change history...

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Abstract

The invention relates to a position keeping method of a stationary orbit satellite, particularly to a position keeping method of an electric propulsion stationary orbit satellite, and belongs to the technical field of the orbit control of a satellite. Four thrusters of an electric propulsion system are mounted at the northwest, the northeast, the southwest and the southeast of the satellite back floor. For the four thrusters, the tangential distances and the normal distances relative to a satellite centroid are the same, and the thrust directions pass through the satellite centroid. A position keeping period comprises a one-day orbit determining period and n two-day small control periods, wherein the four thrusters in one small control period are respectively started, and at the same time, the orbit inclination, the flat longitude drifting ratio and the eccentricity ratio are controlled. The position keeping method disclosed by the invention solves the problem of the position keeping of the stationary orbit satellite of the electric propulsion system.

Description

technical field [0001] The invention relates to a method for maintaining the position of a stationary orbit satellite, in particular to a method for maintaining the position of an electric propulsion stationary orbit satellite, and belongs to the technical field of satellite orbit control. Background technique [0002] Geostationary orbit refers to the orbit of spacecraft that is synchronized with the earth's rotation over the equator. Geostationary orbit satellites play an important role in communications, remote sensing, navigation, data relay and other fields (Zhai Guang, Zhang Jingrui, Zhou Zhicheng. Geostationary orbit satellites in orbit Research progress of life extension technology[J].Acta Astronautica. 2012,33(7):849-859.). [0003] The ideal geostationary orbit plane coincides with the earth’s equatorial plane, and the longitude of the satellite is fixed. However, considering that the space perturbation force causes the satellite to move freely, causing the longitu...

Claims

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Application Information

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IPC IPC(8): B64G1/24
Inventor 赵书阁张尧张景瑞袁俊刚胡照陈宇军
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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