Abstract
Aeroelastic studies of a free-flying forward swept wing (FSW) aircraft have shown that the static aeroelastic divergence exhibited on cantilevered FSW's is replaced with a low-frequency flutter mode due to coupling between the wing divergent mode and the aircraft short-period mode. Studies of possible means of increasing this flutter speed have indicated that adding structural stiffness would result in prohibitive weight or drag penalties. An active flutter control system that employed the existing stability augmentation system of the aircraft was shown to increase the flutter speed by 40% without a performance penalty. The active flutter control system actually decreased the workload of the aircraft stability augmentation system. The coupling between the wing divergent mode and the aircraft short-period mode is also shown to have detrimental effects on flying qualities, ride qualities, and gust loads, but these effects are minimized by the active flutter control system.
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