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.
展开▼
