A spacecraft, e.g. a satellite, has an attitude control device having two magnets 3, 4 with magnetic dipole moments M1, M2. The magnets 3, 4 are spaced apart along a length axis 5 by a gap 6, and arranged with the closest faces being of the same pole. A first magnet 3,4 is connected to a rotation mechanism 7 to rotate the first magnet 3,4 about a first axis 8 which is not parallel to the magnetic dipole moment M1, M2. The first magnet 3,4 may also be rotated about a second axis 9, and the second magnet 3,4 may have a rotation mechanism 7 to rotate the second magnet 3,4 about axes of rotation 10,11. None of the axes of rotation 8,9,10,11 are parallel to the magnetic dipole moment M1, M2.
A spacecraft attitude control system and a spacecraft comprising such an attitude control system
2021-04-14
Patent
Electronic Resource
English
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