Advanced guidance missiles employ blended control of aero-fin and reaction-jet to improve the guidance performance against highly maneuverable targets. The blended control requires multiple inputs and multiple outputs (MIMO) control system design, the design process is much complex than that of conventional aero-fin autopilot. This paper describes a autopilot design for a missile with aero-fin and reaction-jet using the Coefficient Diagram Method (CDM). Performance and stability trade-off study using the CDM is summarized. It is shown that MIMO autopilot design problem can be decomposed into feedback and feedforward controller design problems. A reasonable form of the controller is suggested using the coefficient diagram. A feedback controller is designed using the algebraical approach. The form of the controller has the same form as the conventional design. A wash-out type feedforward controller achieving the minimum fuel consumption is designed using the same manner. It is shown that the feedforward controller can be designed independently of the feedback controller. Improved response and robustness against the reaction-jet force saturation of the designed control system is proven by the simulation.