1.Keldysh Institute of Applied Mathematics,Russian Academy of Sciences,Moscow,Russia;2.University of Putra,Serdang,Malaysia;3.Research Institute for Electromechanics,Istra,Russia
Abstract:
A satellite equipped with a magnetic attitude control system and a pitch flywheel has been considered. The system performance in the transient mode has been investigated. The characteristic exponent of the system have been approximated for a satellite on a circumpolar orbit. In the steady-state mode of gravitational attitude, small motions are considered in the vicinity of equilibrium. The attitude accuracy has been analyzed. The algorithm of an arbitrary but given attitude of the satellite in the orbital plane has been investigated. A numerical simulation has been performed.
