A satellite moving in the gravitational and magnetic fields of Earth is considered. The possibility of designing an integrated attitude control system that combined magnetic and Lorentz control systems is being studied. The expediency of such an association is shown. The effectiveness of the constructed electrodynamic attitude control system for stabilization of different programmed motions of the satellite is confirmed. An algorithm for constructing control torques is shown for each of the considered problems. The results of the computer simulation are presented. The three-axial stabilization of a satellite in the orbital frame requires restoring and dissipative components of control torques. In general case for monoaxial stabilization of a satellite in the orbital frame the control parameters can be constructed as a sum of restoring, dissipative, and compensating components. Stabilization in two-axis programmed rotation requires one to compensate for the specified gyroscopic torque, and an additional term can be introduced into one of the control vectors. For the problem of three-axial stabilization in the Koenig frame, the gravity gradient torque can be compensated by means of the Lorentz torque. Finally, the three-axial stabilization of a satellite in the magnetoLorentz frame also involves the creation of a compensating torque.