The feasibility of solid-state actuation of helicopter servo-flap for rotor blade active control was studied theoretically and experimentally. The design requirements (force, disdplacement, and energy) for this application were indentified. The capabilities of commercially available induced-strain actuators were reviewed and the enrgy feasibility of the induced-strain actuation was established. To achieve implementation of a large-displacement induced-strain actuator, the hydrostatic amplifiaction principles were adopted for experimental confirmation a full-size hydraulically-amplified high-displacement induced-strain (HAHDIS Mk.1) proof-of-concept demonstrator was redesigned and built. The HADIS Mk. 1 demonstrator was subjected to static and dynamic testing in CIMSS laboratory. After initial testing, improvements of the HAHDIS Mk. 1 device were implemented to reduce the internal frictional losses. The improved HAHDIS Mk. 1a actuator was subjected to extensive dynamic testing in the 1 to 30 Hz frequenzy range. The no-load frequency response curve showed excellent behaviour ofer the full frequency range, in spite of the power and current limitations of the electronic equipment. Further tests using a realistic intertial load were also performed, and fully proved the capability of the HAHDIS Mk 1a actuator to achieve full flap actuation over the required ferquency range. For in-flight implementation of the HAHDIS principle, a modular HAHDIS Mk. 2 conceptual design capable of installation within the restricted space and geometry of an actual helicopter blade has been proposed and discussed, and its potential benefits in terms of high frequency response and reactive power recirculation have been highlighted.
Solid-state actuation of rotor blade servo-flap for active vibration control
Die Anwendung von festen Aktoren zur aktiven Schwingungsdämpfung von Rotorflügeln
Journal of Intelligent Material Systems and Structures ; 7 , 2 ; 192-202
1996
11 Seiten, 13 Bilder, 2 Tabellen, 12 Quellen
Article (Journal)
English
Active Rotor-Blade Vibration Control Using Shaft-Based Electromagnetic Actuation
Online Contents | 2006
|Kaman K-190 servo flap rotor control
Engineering Index Backfile | 1948
|Kaman K-190 servo flap rotor control
Engineering Index Backfile | 1948
|