An attitude control apparatus for a satellite includes: at least three electric motors, wherein the at least three electric motors are arranged in such a way that a torque may be generated with any orientation of an associated torque vector, and a controller, wherein the controller is configured to drive the at least three electric motors based on a torque controller. The torque controller is adapted to operate the at least three electric motors outside a rest state only when an acceleration torque and a braking torque are required to execute an agile attitude change maneuver. There is also described an associated method.
ATTITUDE CONTROL DEVICE FOR A SATELLITE AND METHOD FOR CONTROLLING THE ATTITUDE OF A SATELLITE
2020-01-09
Patent
Electronic Resource
English
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