Attitude motion of a satellite equipped with a single flywheel and active magnetic attitude control system is considered. Time-response of the system in a transient mode with respect to the orbit inclination is studied. Comparison with the system consisting of magnetic coils only is conducted. Small steady-state motion near the gravitational orientation is considered. Accuracy and time-response is studied. An algorithm of arbitrary but given orientation in the orbital plane is proposed and studied. Numerical analysis is carried out.

active magnetic control, flywheel, averaged geomagnetic field model, time-response

Theoretical and applied problems of mechanics