PURPOSE: To provide a control device capable of controlling an airframe stably as commanded even with a large change in the dynamic characteristic of the airframe due to flight conditions.

CONSTITUTION: On the basis of the information of an inertia device 4 for detecting the motion of an airframe, an attitude angle to the main streamline velocity is computed by an incidence angle computing part 5 and a roll attitude angle computing part 8, and a compensation gain computed by a control compensator gain computing part 7 from the data of an aerodynamic table part 6 is set to a control compensator 1. The attitude angle to the main streamline velocity is thereby computed, and the control compensator gain is set using a corresponding aerodynamic fine coefficient, so that the limitation of the attitude angle to the main streamline velocity is little. This results in realizing a control device with little degradation in stability and performance even with the change of flight conditions so as to be capable of controlling the airframe stably as commanded.