To deal with the risk of asteroid impacts, effective on-orbit disposal means need to be studied.The most effective on-orbit disposal way which is well recognized internationally is kinetic impact.In order to achieve the effective impact to the asteroid, it is necessary to ensure high precision guidance and control for the impactor at high relative velovity.This paper developed a deviation of image plane rectified proportional guidance method based on optical inertial integrated navigation for the requirements of the terminal high precision guidance and control in the future asteroid on-orbit disposal mission.And some mathematical simulations are made to verify the performance of the method.The simulation results show that the deviation of image plane rectified proportional guidance method can meet the requirements of the terminal high precision guidance and control at high relative velocity condition, and it can adapt to different error combinations given.This method has the advantages of low calculation cost and no risk of non-converge in iteration, and has strong engineering practical value.