| 摘要 |
An attitude control device for a satellite stabilised in three axes in an Earth orbit, comprises, between a roll, yaw and pitch attitude detection assembly (3, 4), a set (5) of at least three reaction wheels and a set of at least two magnetic coils (6X, 6Z) parallel to the roll/yaw plane: - a primary control loop adapted to determine, on the basis of attitude signals and attitude references, attitude correction signals intended for the wheels, - a secondary control loop adapted to determine, on the basis of attitude correction signals intended for the wheels, and of signals representing the behaviour of the wheels, compensation signals intended to be applied to the magnetic coils, and - a circuit for desaturation of the wheels in pitch. <IMAGE>
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