The development of an active on-blade vibration reduction system is presented using SABT (smart active blade tips) that are driven by a piezo-induced, bending-torsion coupled actuator. The actuator beam has a graphite substructure with surface-bonded piezoceramik elements. A spanwise variation in the bending-torsion coupling and the piezo element phasing is used to generate a pure tip twist. A small scale motor, with 10 % span active tips, was tested on the hover stand, at reduced tip speed of Mach 0.25. At a mean thrust loading of 0.07, and for activation of 100 Vrms, SABT deflection amplitudes from 1.8 deg at 2/rev to 2.25 deg at 4/rev were achieved. (halfpeak-to-peak). The rotor normal force measurements show a distinct coupling of the activation with the first and second flap frequencies of the rotor. The corresponding dynamic thrust, generated by a single active tip relative to the steady thrust, ranges from 4.5 % at 2/rev to 8.3 % at 5/rev. For a 1/rev excitation, the single active tip generates a dynamic lift amplitude of 15 % of the steady rotor thrust. The same actuator beam was used to test a rotor with controllable twist blades. The active twist blades used the same main blade section as the rotor blades with the active tips, and hence were not optimized for active twist configuration. Nonetheless, a hover, a mean thrust loading of 0.07, and with activation of 100 Vrms, dynamic twist amplitudes of 0.4 deg at 4%rev and 0.5 deg at 5/rev were achieved (half peak-to-peak).


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    Titel :

    Hover testing of active rotor blade-tips using a piezo-induced bending-torsion coupled beam


    Beteiligte:
    Bernhard, A.P.F. (Autor:in) / Chopra, I. (Autor:in)


    Erscheinungsdatum :

    1998


    Format / Umfang :

    12 Seiten, 28 Bilder, 3 Tabellen, 28 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch