The methods to analyze the flutter for a control wing of a flight vehicle with control actuators have been developed : root locus method and iterative V-g method. Supersonic unsteady aerodynamic forces are obtained by the Doublet point method. The structures of the control surface are modeled by the finite element method. The actuators are considered as springs with dynamic stiffness. Fictitious mass method is adopted for an efficient modal flutter analysis. The methods are applied to the flutter analysis of a control wing with a pneumatic control actuator at the rotating axis. The flutter characteristics of the wing with dynamic stiffness are compared with those of the wings with several values of static stiffness. From these results, it is concluded that an actuator can not be replaced by a static spring and its dynamic characteristics must be properly considered for an accurate flutter prediction.
