Procédé de contrôle d'attitude d'un satellite pointé vers un objet céleste et satellite adapté à sa mise en Óoeuvre.

摘要

A method for control of the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a reference frame tied to the satellite, the instantaneous angular velocity vector @ of the satellite is detected, and torques defined by a control law are applied to the satellite, via an actuation unit (16), so as to rotate the satellite about this direction whilst orienting a pointing axis @ tied to the satellite along this direction, characterised in that this direction of the predetermined celestial object in the reference frame tied to the satellite is defined by a first magnitude representative of a first angle ( alpha , alpha ') measured between an aiming axis (Zs, Zs') and the projection of this direction onto a first reference plane containing this aiming axis and by a second magnitude representative of a second angle ( beta ') defined by this aiming axis and the projection of this direction onto a second reference plane containing this aiming axis, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite. IMAGE