Abstract
These studies have shown that wing/store flutter can be stabilized with adequate stability margins using an active flutter control system which shares the aileron actuation hydraulics with the lateral control system. The flutter control system can be adapted to different store carriage configurations by adjusting the phase and gain characteristics of a generalized electronic compensation network. Control of a flutter mode can be maintained even though the hydraulic actuators are rate saturated for a significant portion of their stroking cycles. Before a flutter control system can be implemented on current aircraft actuator bandwidth should be extended and hydraulic flow rate increased. These improvements are within the current state-of-the-art. It is estimated that the flutter control system with triply redundant components will add about 270 Ib to the aircraft weight.
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