Abstract: A guidance and control strategy for attaching a vehicle to a small solar system body is presented. In order to ensure soft-landing, a prescribed line of sight and angle of sight profile satisfying restriction are planned, a sliding mode controller is designed to track the prescribed line of sight and angle of sight profile for safely soft-landing on surface of small asteroid. The robust feature of the close-loop guidance scheme is stressed. Finally, numerical simulations are conducted to verify that the given guidance and control strategy is feasible.