The preprint presents results of the development of the first Russian nanosatellite attitude control system. The system provides an orientation of its longitudinal axis alongwith the local intensity vector of the geomagnetic field. Magnetic and geometrical parameters of the permanent magnet and hysteresis rods are calculated. Location and method of their placement are shown. Examples of transient and steady-state motion of the satellite about its centre of mass are presented.

nanosatellite, magnetic attitude control system, hysteresis rod, permanent magnet

Theoretical and applied problems of mechanics