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

Document Type

Article

Subject Area(s)

Physics, Chemistry, Mechanical, Engineering

Abstract

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.

Rights

© Journal of Intelligent Material Systems and Structures, 1996, SAGE Publications

Giurgiutiu, V., Rogers, C.A., and Rusovici, R. (1996). Solid-State Actuation of Rotor-Blade Servo-Flap for Active Vibration Control, Journal of Intelligent Material Systems and Structures, 7(2), 192-202.

https://dx.doi.org/10.1177/1045389X9600700211

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