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Method and device for controlling attitude of a spacecraft

A technology of attitude control and spacecraft, which is applied in the field of attitude control of satellites and spacecraft, and can solve problems such as reducing the total angular momentum of satellites

Active Publication Date: 2017-12-05
AIRBUS DEFENCE & SPACE SAS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Currently, electric thrusters cannot replace chemical thrusters to reduce the total angular momentum of a satellite after separation if the electrical autonomy of said satellite cannot be guaranteed

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  • Method and device for controlling attitude of a spacecraft
  • Method and device for controlling attitude of a spacecraft

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Embodiment Construction

[0051] The invention involves taking a non-zero initial total angular momentum H TOT Attitude control of a spinning spacecraft. total angular momentum H TOT The axis of is hereinafter referred to as the "kinetic axis".

[0052] "Attitude control" shall be understood herein to mean at least changing the orientation of the spacecraft with respect to the kinematic axis, in other words, in a frame of reference associated with the geometry of the spacecraft known as the "aircraft frame of reference" , aligning the kinematic axis with a predetermined axis in the aircraft frame of reference.

[0053] In the following description, consider the following situation in a non-limiting manner: the spacecraft is a satellite 10, and the initial total angular momentum H TOT corresponds to the angular momentum transferred to the satellite 10 upon separation from the satellite's vehicle. For example, the satellite 10 has been placed by a vehicle in GTO (Geosynchronous Transfer Orbit) and is...

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Abstract

The present invention relates to a method (50) of controlling the attitude of a spacecraft (10) in spinning around itself with a nonzero total angular momentum HTOT, said spacecraft (10) comprising a set of inertia flywheels (20) adapted to form an internal angular momentum HACT. The method (50) of attitude control comprises a step (52) of aligning the axis of said total angular momentum HTOT with a principal axis of inertia of the spacecraft (10), in the course of which the inertia flywheels (20) are controlled so as to form an internal angular momentum HACT such that the following expression, in which J is the inertia matrix of the spacecraft (10): HACT X J-1 (HTOT J-1HTOT) - is negative if said principal axis of inertia targeted is the axis of maximum inertia of the spacecraft (10), - is positive if said principal axis inertia targeted is the axis of minimum inertia of the spacecraft (10).

Description

technical field [0001] The present invention relates to the field of attitude control of spacecraft, such as satellites, and more particularly to attitude control methods and systems for spacecraft spinning with a non-zero initial total angular momentum. [0002] "Attitude control" should be understood here to mean more specifically: changing the orientation of the spacecraft with respect to the axis of said initial total angular momentum known as the "kinetic axis", in other words, In a frame of reference associated with the geometry of the spacecraft, the kinematic axis is aligned with a predetermined axis in the frame of reference of the aircraft. Background technique [0003] In order to change the orientation of the spacecraft relative to the kinematic axis, it is known to: [0004] - stopping the rotation of the spacecraft in an inertial frame of reference by absorbing said total angular momentum by means of an inertial flywheel (reaction wheel, gyroscopic actuator), ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244B64G1/26B64G1/283B64G1/286B64G1/245
Inventor 尼古拉斯·屈耶龙菲利普·劳伦斯瓦莱里奥·莫罗
Owner AIRBUS DEFENCE & SPACE SAS
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