Dual-spin satellite angular motion in magnetic and gravitational fields

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.