An integrated fuzzy sliding mode control-guidance method is developed for a missile with the dual-control configuration for the problem that the canard control may saturate at high angles of the attack, The model of the integrated guidance and control system is derived, and the dynamics for a missile with canard/tail control fins are analyzed. By using the double-sliding modes variable structure control theories, zero effort miss and a variable related to autopilot parameter are selected as two sliding surfaces. The former guarantees zero-miss distance, the latter provides a damped response, and the controller and guidance are integrated. A fuzzy link is added to the design of the controller based on the exponential reaching law method to avoid the chattering problem in sliding mode control. Finally, the simulation of the interception is carried out when the target does snake maneuver, and the results show the effectiveness of the proposed method.