Abstract
The root locus and iterative V- g method have been applied to analyze the flutter for a control surface of a launch vehicle with control actuators. The actuator is considered as a spring with dynamic stiffness. The 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 actuator at a rotating axis in the supersonic region. The effect of the sweep angle on the flutter characteristics of the wing with dynamic stiffness is investigated and is compared with that of the wings with several values of static stiffness.
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