The paper deals with a satellite in a circular near-Earth orbit. The satellite interacts with the geomagnetic field by the Lorentz and magnetic torques. The gravitational disturbing torque acting on the satellite attitude dynamics is taken into account as the largest disturbing torque. The octupole approximation of the Earth's magnetic field is used. Satellite electromagnetic parameters, namely the electrostatic charge moment of the first order and the intrinsic magnetic moment are the controlled quasiperiodic functions. Control algorithms for the satellite electromagnetic parameters, which allow the satellite attitude position to be stabilized in the orbital frame were obtained. The cases of direct and indirect equilibrium positions in the orbital frame are investigated. The total stability of the satellite stabilized orientation is proved both analytically and by PC computations. (C) 2014 Elsevier Masson SAS. All rights reserved.