This paper presents the wind tunnel testing of a smart rotor model with piezoelectric bender actuated trailing-edge flaps for active vibration control. First, open-loop tests were performed at different rotor speeds, advance ratios, and collective pitch settings. Flap deflections of +/-4 to +/-6 deg. were recorded in the 1-5/rev frequency range at 1800 rpm. The rotor collective pitch and advance ratio were found to have negligible impact on actuator performance. For in-phase 3/rev actuator excitation, oscillatory thrust levels of up to +/-36 lbs (60% steady rotor thrust at 6 deg. collective) were recorded. Next, closed-loop vibration suppression tests were conducted in conjunction with a neural network controller. These tests demonstrated between 70% and 90% reduction in the 4/rev thrust, pitching moment, and rolling moment levels for 2 to 4 deg. collective. The trailing-edge flap was also used to suppress a rotating frame load (blade root flat-wise bending moment) with equally good success.


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    Title :

    Wind tunnel testing of a smart rotor model with trailing-edge flaps


    Additional title:

    Windtunneluntersuchung an einem intelligenten Rotormodell mit Hinterkantenklappen


    Contributors:
    Koratkar, N.A. (author) / Chopra, I. (author)

    Published in:

    Publication date :

    2002


    Size :

    10 Seiten, 14 Bilder, 6 Tabellen, 16 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English