Based on kappa guidance law, this paper proposes a maneuvering orbit change mode of virtual target. Kappa control algorithm is applied to the midcourse guidance in the atmosphere to maximize the missile speed at the beginning of the terminal stage. Using kappa guidance law to attack virtual targets, various trajectory changes can be realized. The speed direction of the virtual target point is determined by the spatial circle, which reduces the command jump caused by target switching. The second-order smoothing method is adopted to make the overload command transition smoothly. Finally, the effectiveness of the proposed guidance is verified by six degree of freedom simulation.