| 摘要 |
The invention relates to a method of controlling the attitude of a satellite ( 1 ) comprising two gyrodynes ( 3,4 ) and a third main actuator ( 2 ) which delivers torques at least along the Z axis. The inventive method consists in: fixing the gimbal axes, A 1 and A 2 , of the gyrodynes ( 3, 4 ) parallel to Z; setting a non-zero bias (e) between the angular momentum vectors (Formula I) of the gyrodynes; using the measurements provided by the sensors on board the satellite to estimate the kinematic and dynamic variables necessary in order to control the attitude of the satellite ( 1 ); calculating set variables in order to realise the objectives assigned to the satellite ( 1 ) attitude control system; and using the deviations between the estimated variables and the set variables to calculate control orders and to send same to the main actuators ( 2, 3, 4 ) in order to control the changing deviations over time, the control orders transmitted to the gyrodynes ( 3, 4 ) comprising orders which are used to vary the orientation of the gimbal axis thereof.
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