FIELD: space engineering.
SUBSTANCE: invention relates to devices for controlling the orientation of a spacecraft by its interaction with the geomagnetic field, namely for removing the kinetic moment of inertial executive bodies. The device includes a block of electromagnets with inductors, a micro-computer, a block of reversible switches and a control device for reversible switches, a block of current sensors, a block of DC voltage converters, a block of angular velocity sensors, a block of flywheel motors and a magnetometer. In the magnetic system, electromagnets ensure the formation of high values of magnetic moments along the associated X, Y, Z axes of the spacecraft.
EFFECT: increased efficiency and reliability of the magnetic system.
1 cl, 4 dwg
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