Active magnetic attitude control system of a satellite equipped with a flywheel

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.