A Mach-scaled CH-47 model rotor blade with an actively controlled servo-flap near the tip was designed, manufactured, and tested. The servo-flap was powered by an 'X-Frame' piezoelectric actuator. Using hover test data, the transfer function of the rotor (from servo-flap deflection to vertical hub shear) was determined. The servo-flap produces significant control authority, especially near the 3/rev frequency that would be important for the CH-47. Closed-loop feedback control was experimentally applied to the model rotor system. Both single frequency and combined frequency controllers were implemented on the rotor, and produced significant reduction in the vibration level. Most significantly, simultaneous control of 1/rev, 3/rev, 4/rev, 5/rev, and 6/rev harmonic vibration was successfully demonstrated. The peak vibrations were eliminated at each frequency, as well as the vibrations over a small bandwidth surrounding each peak. Comparison of continuous-time and discrete-time controllers was made. Continuous-time controllers were shown to produce more effective vibration reduction.


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    Closed-Loop Vibration Control Experiments on a Rotor with Blade Mounted Actuation

    Hall, S. / Prechtl, E. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2000



    Decentralized rotor vibration control with on-blade actuation

    Konstanzer, P. / Royal Aeronautical Society | British Library Conference Proceedings | 2005



    Solid-state actuation of rotor blade servo-flap for active vibration control

    Giurgiutiu, V. / Rogers, C.A. / Rusovici, R. | Tema Archive | 1996