Method for controlling the attitude of a satellite aimed...

G - Physics – 05 – D

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G05D 1/08 (2006.01) B64G 1/24 (2006.01) B64G 1/36 (2006.01) B64G 1/26 (2006.01) B64G 1/28 (2006.01)

Patent

CA 2111602

ABSTRACT OF THE DISCLOSURE METHOD FOR CONTROLLING THE ATTITUDE OF A SATELLITE AIMED TOWARDS A CELESTIAL OBJECT AND A SATELLITE SUITABLE FOR IMPLEMENTING IT A method of controlling the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a frame of reference related to the satellite, the instantaneous angular velocity vector (.omega.) of the satellite is detected and, by means of an actuating assembly (16), torques are applied to the satellite which are defined by a control law as as to rotate the satellite about this direction whilst orienting an aiming axis (SR) related to the satellite in this direction, involves defining this direction of the predetermined celestial object in a frame of reference related to the satellite by a first quantity representing a first angle (.alpha.,.alpha.') measured between an axis of sight (Zs, Zs') and the projection of this direction onto a first reference plane containing this axis of sight and by a second quantity representing a second angle (.beta.') defined by this axis of sight and the projection of this direction onto a second reference plane containing this axis sight, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite, whilst a satellite for implementing the method includes a body (11); a sensor (13a, 13b) having the axis of sight (Zs); the actuating assembly (16); an attitude control unit (20) for generating signals for applying the said torques to the satellite; a unit (15) for measuring the rotation velocity; and a processing unit (21) calculating the said second quantity.

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