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Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite

A technology of earth orbit and satellite, which is applied in the field of satellite orbit and attitude control, and can solve problems such as increased thruster consumption, increased satellite complexity and manufacturing costs, and reduced satellite service life

Active Publication Date: 2017-05-10
AIRBUS DEFENCE & SPACE SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Increased satellite complexity and manufacturing costs as it includes many different thrusters
Since many different maneuvers have to be performed, the consumption of the thrusters increases, which reduces the service life of the satellite, especially in the case of chemical thrusters
Also, increasing the number of on / off sequences for the thrusters has a negative effect on the lifespan of the thrusters

Method used

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  • Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite
  • Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite
  • Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite

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Embodiment Construction

[0088] figure 1 The system for controlling the orbit of the satellite 10 is schematically shown. In the following description, the case of the satellite 10 in GEO orbit is considered without limitation. However, it is not excluded to consider other types of spacecraft (space shuttles, space stations, etc.) and / or other earth orbits, such as geosynchronous orbit, medium earth orbit (MEO), low earth orbit (LEO), etc., in other examples.

[0089] For the purpose of description, the satellite 10 is associated with a satellite reference frame centered on the centroid O of the satellite 10 and including three axes X, Y, and Z. Specifically, the X axis is parallel to the velocity vector of the satellite 10 in the inertial reference frame, the Z axis points to the center of the earth T, and the Y axis is orthogonal to the X axis and the Z axis. Each of the X, Y, and Z axes of the satellite reference frame is associated with the corresponding unit vector ux, uy, and uz. The unit vector ...

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Abstract

The present invention relates to a method (50) for controlling the orbit of a satellite (10) in earth orbit, the orbit of the satellite (10) being controlled by commanding, according to a plane of operation, the propulsion means (30, 31), including at least one thruster, and means for moving (20, 21) said propulsion means. According to the invention, said plane of operation includes at least two orbit-control operations, thrust powers of the propulsion means (30, 31) during said two orbit-control operations having respective thrust directions that are not parallel in an inertial frame of reference, each one of said thrust powers being determined so as to simultaneously control the inclination and the position of the orbit of the satellite as well as to form a momentum that is suitable for unloading a device for storing angular momentum of said satellite in a plane orthogonal to the direction of thrust of said thrust power.

Description

Technical field [0001] The invention belongs to the field of satellite orbit and attitude control. The invention is particularly advantageously (but not limited to) applied to the case of a telecommunication satellite equipped with an electric propulsion device in a geostationary orbit (GEO). Background technique [0002] It is known that satellites in earth orbit are subject to many interferences. On the one hand, interference tends to cause the satellite to move relative to the position of the set point in its orbit, and on the other hand, it tends to modify the attitude of the satellite relative to the set point. [0003] In order to keep the satellite basically at the set point position and the set point attitude, it is necessary to perform orbit control and attitude control on the satellite. [0004] Orbital control is to limit the changes of orbital parameters. Orbital parameters are usually expressed by the inclination, longitude and eccentricity of the satellite orbit. In ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/26B64G1/28
CPCB64G1/242B64G1/283B64G1/286B64G1/262B64G1/2425F02K9/84B64G1/26
Inventor 瓦莱里奥·莫罗吉恩·菲舍尔
Owner AIRBUS DEFENCE & SPACE SAS
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