The unique configuration of the rotorcraft generates problems unknown to fixed wing aircraft. These problems include high vibration and noise levels. This paper presents the development and test results of a Terfenol-D based actuator designed to operate in an individual blade control system in order to reduce vibration and noise and increase performance on Army UH- 60A helicopter. The full-scale, magnetostrictive, Terfenol-D based actuator was tested on a specially designed testbed that simulated operational conditions of a helicopter blade in the laboratory. Tests of actuator performance (strike, force moment, bandwidth, fatigue life under operational loading) were performed.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Integrated actuation system for individual control of helicopter rotor blades


    Contributors:

    Conference:

    Smart Structures and Materials 1996: Smart Structures and Integrated Systems ; 1996 ; San Diego,CA,United States


    Published in:

    Publication date :

    1996-05-01





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Piezo-electric actuation of helicopter rotor blades

    Lieven, N.A.J. | Tema Archive | 2001


    Actuation concepts for morphing helicopter rotor blades

    Grohmann, Boris / Maucher, Christoph / Jänker, Peter | Tema Archive | 2006


    ACTUATION CONCEPTS FOR MORPHING HELICOPTER ROTOR BLADES

    Grohmann, B. A. / Maucher, C. K. / Janker, P. et al. | British Library Conference Proceedings | 2006



    Helicopter rotor-blades

    Engineering Index Backfile | 1955