Abstract: The motion of a spacecraft with a solar sail is considered within the restricted three-body problem of the Sun–Earth system. The equations of controlled orbital motion of the solar sail in the vicinity of the Sun–Earth collinear libration point L₁ are investigated. Modified equations of the circular restricted three-body problem of the Sun–Earth system are used to describe the controlled orbital motion of the spacecraft and to develop the control laws. Our main result is the proposed control law in the form of a feedback that provides spacecraft keeping in the vicinity of the libration point L₁ using the light pressure forces.