The stabilization of the motion of the space station in a circumlunar orbit using a tether system, taking into account the impact of the Earth’s gravitational field, was investigated. Comparison of two configurations of the space tether system is carried out. The first configuration included a station and a small spacecraft. In the second case, the space system tethered consisted of a space station and two small spacecraft. It was supposed that the space tether system is deploying according to a given control program in the direction of the local vertical. The tethers are represented as weightless and inextensible mechanical rods. A mathematical model has been developed that describes the plane motion of the space system, using Newton’s laws and the theorem on the change in angular momentum. It has been established that the symmetrical configuration of the system with two small spacecraft has an advantage in terms of solving the problem of gravitational stabilization of the movement of the lunar station (the error of stabilization of the station relative to the vertical decreases).