The development and open-loop hover testing of a smart rotor model with trailing-edge flaps for individual blade control of helicopter vibration are presented. First, the University of Maryland Advanced Rotorcraft Code was used to size the trailing-edge flap and to determine the flap-deflection requirements for vibration suppression in the wind tunnel. Next an analytic model for the coupled actuator-flap-rotor system was used to develop a multilayer piezoelectric bender configuration that was capable of meeting the flap-deflection requirements. Based on this study, a matched set of six smart rotor blades were fabricated in-house. The four-bladed smart rotor model was tested in the open-loop mode in hover using a Bell-412 Mach-scaled hub. Flap deflections of +/-4 to +/-6 deg were recorded in the 1-5/rev frequency range at the model operating speed of 1890 rpm. The flap deflection increased to +23 deg at 8/rev because of actuator resonant amplification. Rotor collective pitch was found to have negligible impact on actuator performance. The maximum control effectiveness was observed close to the blade flatwise bending and torsion natural frequencies. For 3/rev actuator excitation oscillatory thrust levels of up to +/-10 lb (45 N) (60% steady rotor blade thrust at 6-deg collective) were recorded, thereby demonstrating the open-loop control authority of the actuator-flap system.


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    Titel :

    Open-loop hover testing of a smart rotor model


    Weitere Titelangaben:

    Untersuchung der Frequenzcharakteristik piezoelektrisch angetriebener Aktivschwingungsbegrenzer an den Rotorblättern eines Hubschrauberrotors


    Beteiligte:
    Koratkar, N.A. (Autor:in) / Chopra, I. (Autor:in)

    Erschienen in:

    AIAA Journal ; 40 , 8 ; 1495-1502


    Erscheinungsdatum :

    2002


    Format / Umfang :

    8 Seiten, 10 Bilder, 1 Tabelle, 21 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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