Orbit dynamics and control in the neighborhood of the asteroid´s center point

According to the similarity of the equations of motion between around the asteroid and in the circular restricted three-body problem (CRTBP), equilibrium theory in CRTBP are introduced to the asteroid´s satellite orbital dynamics in this paper. Using this theory, we calculate the position of equilibrium point in body fixed frame and analyze the stability of these points. By choosing a suitable initial state, we eliminate the unbounded modal effects on the orbits, which have been the Halo-orbit and Lassjous-orbit around the asteroid´s equilibrium point. A small force controller based on linear feedback control law is also designed to keep the spacecraft´s orbit round the norm orbit.