In this paper we consider the special problem of stabilization of controllable orbital motion in a neighborhood of collinear libration point L2 of Sun-Earth system. The modification of circular three-body problem - non-linear Hill’s equations, which describe orbital motion in a neighborhood of libration point is used as a mathematical model. Also, we used the linearized equations of motion. We investigate the problem of spacecraft arrival on the unstable invariant manifold. When a spacecraft reaches this manifold, it does not leave the neighborhood of L₂ by long time. The distance to the unstable invariant manifold is described by a special function of phase variables, so-called “hazard function”. The control action directed along Sun-Earth line. 200 words.