The experimental results are presented of a hover test with a one-eighth dynamically scaled (Froude scale) helicopter rotor model with embedded piezoceramic elements as actuators to suppress vibrations. A 6-ft-diameter two-bladed bearingless rotor model was built with banks of piezoelectric torsional actuators capable of manipulating blade twist at harmonics of the rotational speed. The twist performances of several rotor blade configurations were investigated using accelerometers embedded in the blade tip. The change in oscillatory rotor lift due to piezoactuation was measured by a hub balance. Experimental results show that linear twist distributions of up to 0.6 deg, resulting in increases of up to 10 % of the nominal rotor lift, are possible with existing piezoceramic technology. Although the twist amplitudes attained in this experiment were less than the target value (1-2 deg), it is expected that partial reduction of hub vibration can be achieved with the current smart rotors.


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    Title :

    Hover testing of smart rotor with induced-strain actuation of blade twist


    Additional title:

    Schwebeflug-Prüfung eines mit Verstellelementen versehenen Hubschrauber-Rotors mit induzierter Verformungssteuerung der Blattverdrehung


    Contributors:
    Chen, P.C. (author) / Chopra, I. (author)

    Published in:

    AIAA Journal ; 35 , 1 ; 6-16


    Publication date :

    1997


    Size :

    11 Seiten, 15 Bilder, 3 Tabellen, 20 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English







    Hover Testing of a Smart Rotor With Induced-Strain Actuation of Blade Twist

    Chen, P. / Chopra, I. / American Institute of Aeronautics and Astronautics| ASME| ASCE | British Library Conference Proceedings | 1995