A satellite moving on a circular equatorial orbit is considered. The satellite is equipped with a controlled magnetic moment and a controlled electrostatic charge. The problem of triaxial stabilization in the orbital frame is studied. The electrodynamic control system is proposed. In addition, to improve characteristics of transient processes, PID controller of a special form is used. With the aid of the Lyapunov direct method, asymptotic stability conditions of the program mode are obtained. The results of computer simulation are provided demonstrating the efficiency of the developed approach.