Attitude motion of a satellite equipped with magnetic control system is considered. System comprises of three mutually orthogonal magnetorquers and one three-axis magnetometer. Satellite is stabilized in orbital reference frame in equilibrium position unstable in gravitational field. Two control strategies are presented. Three-axis attitude is shown to be achievable. Accuracy in presence of disturbing torques and inertia moments uncertainty is assessed.

magnetic attitude control system, three-axis magnetometer, three-axis attitude, Kalman filter

Theoretical and applied problems of mechanics