Planar Problem Motion Stabilization Using the Rotational Motion and the Light Pressure Forces at the Collinear Libration Point

This article represented the controlled planar orbital motion of a spacecraft with a solar sail. The motion of a spacecraft is described by using the Hill’s problem of the circular restricted three-body problem of the Sun–Earth system. The attitude motion is determined by using the Euler dynamic equations and the quaternion kinematic equation. The spacecraft keeping planar problem in a neighborhood of a collinear libration point using the example of a solar sail is investigated. The orientation problem of a solar sail solving by constructing a feedback control as a special function of phase coordinates. This function is represent the linear approximation of a stable invariant manifold in a neighborhood of a libration point. Problem of spacecraft attitude control motion with a flywheel is considered. Numerical simulation of the controlled motion of a spacecraft at a libration point is carried out. The numerical estimations of the control law parameters and controlled motion are given.