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This paper presents the bench-top testing of a piezoceramic C-block driven active flap system designed to suppress the vibrations of a helicopter rotor blade. The C-block actuators are curved benders designed to generate a larger force output than a straight bender, while providing deflections large enough to eliminate the need for external leveraging systems necessary with stack driven systems. The actuators power a balanced active flap designed to minimize the effect of air speed and rotor speed on flap deflection. Quasi-static experimentation at 1 Hz produced maximum angular flap deflections of 8.4° peak-to-peak. Dynamic tests were conducted over a 40 Hz frequency range demonstrating the ability to generate significant flap deflections both before and after the first natural frequency. Over the 40 Hz range, the flap deflections never dropped below 8° pp, with a first natural frequency of 27 Hz. The flap deflection reached a maximum value of 13.6° pp at 40 Hz. If the applied voltage is increased to the maximum allowable level, it is predicted that flap deflections as large as 20° pp can be achieved.

Bench-top characterization of an active rotor blade flap system incorporating C-block actuators