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An attitude control device for a satellite stabilized on three axes including a pitch axis comprises two solar generator wings extending in opposite directions away from a satellite body on respective longitudinal axes at least approximately parallel to the pitch axis. Two drive motors drive these w

An attitude control device for a satellite stabilized on three axes including a pitch axis comprises two solar generator wings extending in opposite directions away from a satellite body on respective longitudinal axes at least approximately parallel to the pitch axis. Two drive motors drive these wings independently of each other in rotation about rotation axes at least approximately parallel to the pitch axis to keep the wings facing the Sun with a depointing angle at most equal to a predetermined maximum depointing value. Sensors measure attitude angles and a computation system commands the drive motors according to the attitude angles. On each wing an additional surface in the form at least one vane extends longitudinally beyond the end of the wing parallel to its longitudinal axis. These additional surfaces have substantially the same surface area and are inclined about this axis relative to the wings in opposite directions by at least approximately the same angle which is less than the 90°complement of the maximum amplitude of wing depointing.

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Attitude control device for a satellite stabilized on three axes including a pitch axis, the device comprising two solar generator wings extending in opposite directions away from a satellite body on opposite respective wing longitudinal axes at least approximately parallel to the pitch axis, two dr

Attitude control device for a satellite stabilized on three axes including a pitch axis, the device comprising two solar generator wings extending in opposite directions away from a satellite body on opposite respective wing longitudinal axes at least approximately parallel to the pitch axis, two drive motors adapted to drive said wings independently of each other in rotation about respective rotation axes at least approximately parallel to the pitch axis to keep said wings facing the Sun with a depointing angle at most equal to a predetermined maximum wing depointing value, a set of sensors adapted to measure attitude angles and a computation system adapted to command the drive motors according to the attitude angles, which device further comprises on each wing an additional surface in the form at least one vane extending longitudinally beyond a free end of said each wing, parallel to said respective wing longitudinal axis of said each wing, said additional surfaces having substantially a same surface area and being inclined about said respective wing longitudinal axes of said wings relative to said wings in opposite directions at approximately a same angle a90°complement of said maximum wing depointing value.