Attitude motion of a satellite equipped with single flywheel and active magnetic attitude control system is considered. Time-response of the system in transient mode is studied. Characteristic exponent approximations values are obtained. Small steady-state motion near the gravitational attitude is considered. Accuracy and time-response is studied. An algorithm of arbitrary but given attitude in the orbital plane is proposed and studied. Numerical analysis is carried out.

magnetic attitude control system, flywheel, dual spin

Theoretical and applied problems of mechanics