The topic of the article is an artificial Earth satellite in a circular near-Earth orbit. The satellite possesses a dynamical symmetry and is equipped with an electrodynamic attitude control system based on the usage of Lorentz and magnetic torques. The control torques are ensured by a controllable variation of two electromagnetic parameters of the satellite: the intrinsic magnetic moment and the static moment of charge of the first order. In the satellite's programmed motion the axis of the dynamical symmetry is inclined to the local vertical axis at a constant angle and the satellite slowly rotates around that axis. Such a rotation mode is of great importance in space missions, because it can reduce the temperature gradient effect, which may cause problems with the satellite's functioning. But this mode cannot be realized without a control because of the disturbances, among which the gravitational torque should be mentioned as the most important one. In the present paper the satellite's stabilization in the programmed attitude motion is investigated. The stated problem appears to be more complex than the problem of the uniaxial attitude stabilization of a satellite, and previously it was not treated with the use of the electrodynamic control system. On the basis of the Lyapunov direct method the conditions, under which the electrodynamic control solves the problem, were obtained. A new construction of the Lyapunov function was proposed, and using the function sufficient conditions for the asymptotic stability of the programmed motion were found in an explicit form.