Abstract: The controlled motion of a spacecraft with a solar sail in interplanetary space near the collinear libration points L₁ and L₂ of the Sun–Earth system is investigated. The equations of the circular restricted three-body problem and their modifications are used to describe the orbital motion. We present a technique for constructing the orbital motion control laws and provide an estimate of the controllability region when solving the problem of stabilization or long-term spacecraft keeping in the vicinity ofL₁ and L₂ . This technique is based on the solution of the control problem for a linearized model of the equations of orbital motion and the transfer of results to the nonlinear case. Such a technique for the construction of control laws extends the possibilities both in solving the problems of motion stabilization and in solving the problems of maneuvering in the vicinity of a collinear libration point. We estimate the controllability region for a spacecraft with a solar sail and present the trajectories of possible spacecraft motion that are provided by the solar sail orientation when flying from the vicinity of a collinear libration point. It is in these regions of space that the light pressure force can have a significant efficiency due to the relatively small magnitude of the gravitational force. As an example, we consider a model of a spacecraft with a solar sail whose sail area-to-mass ratio corresponds to the spacecraft from the implemented IKAROS project and is less than that of the CubeSat spacecraft from the implemented LightSail-2 project by an order of magnitude.