Solid-State Actuation of Rotor Blade Servo-Flap for Active Vibration Control

The basic concepts and some innovative ideas associated with the analysis, design, and experimentation of induced-strain actuators for rotor blade aeroelastic vibration control are presented and discussed. A trailing-edge servo-flap actuated by a hydraulically-amplified large-displacement induced-strain actuator is considered. Design requirements based on extensive literature review are proposed and utilized. The principle of high-power induced-strain actuation, and the energy and energy-density of several commercially-available induced-strain actuators are presented. A full-scale proof-of-concept demonstrator, designation HAHDIS Mk. 1, was designed, built, and tested. Results from static and dynamic tests are presented and discussed. Good frequency response of the full-scale proof-of-concept demonstrator was proven in the range of 1 to 30 Hz in spite of the power and current limitations of the available electronic equipment.