This paper presents the experimental results of a hover test with a 1/8th dynamically-scaled (Froude scale) helicopter rotor model with embedded piezoceramic elements as sensors and actuators to suppress vibrations. A 6-ft diameter 2-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 performance of several rotor blade configurations were investigated using accelerometers embedded in the blade tip. The change in oscillatory rotor lift due to piezo-actuation 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 a smart rotor with induced-strain actuation of blade twist


    Additional title:

    Bewegungstest eines smarten Rotors mit Regelung der Blatt-Verstellung durch induzierte Dehnung


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


    Publication date :

    1995


    Size :

    18 Seiten, 48 Bilder, 7 Tabellen, 16 Quellen



    Type of media :

    Conference paper


    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