Abstract: The mission satellite is always forced to fly in the orbital plane of the target satellite by using vector control technique.At the same time,the angle of mission satellite to target satellite to geocenter,and the objective distance between two satellites will keep constant.So the coplanar hovering orbit was achieved.The dynamic theoretical analysis of the hovering orbit was conducted.Then the radial and tangential acceleration requirements during the hovering process were deduced,and the open loop orbit control strategy was proposed.After that the energy requirements of different hovering tasks were analyzed.The dynamic simulation of the hovering process was conducted to validate the theoretic results.