Disclosed is a space tumbling target de-
spinning control method based on a permanent
magnet eddy current effect. The method comprises the following steps: a service
spacecraft docks in the
working space of a mechanical arm, and is kept at a safety distance from a tumbling non-cooperative target; a
visual inspection system carried by the service
spacecraft measures the direction of a target
angular momentum vector H and the direction of a
spin axis position vector Zb, and the mechanical arm drives a permanent
magnet eddy current braking device at the end to an initial de-
spinning position, and the docking position is 100mm from the surface of the target in the direction of the target
angular momentum vector; the permanent
magnet eddy current braking device is started, the direction of a vector outputting an external torque T1 is corrected according to the real-time change of attitude angle in the tumbling process of the target until the angle of
nutation attenuates completely, and the rotation state of the target is changed to a single
spinning motion state; the position of the permanent magnet eddy current braking device is adjusted to the side of the tumbling non-cooperative target, the permanent magnet eddy current braking device is started to output a
brake torque T2 until the single spinning motion state attenuates completely; after the target is completely de-spun, an end
actuator is replaced with a grasping paw, and the target is captured directly by the mechanical arm.