A two-bladed, 7.5-ft diameter dynamic rotor model with 10% chord on-blade elevons driven by piezoceramic bimorph actuators was designed and tested in hover at tip speeds up to 298 ft/s. The elevon actuator succeeded in achieving deflections of +/-5 deg at the nominal rotor speed of 760 RPM. Aeroelastic and structural dynamic response characteristics were evaluated over a wide rotor speed range using frequency sweep excitation of the elevon up to 100 Hz. The CIFER post processing method was very useful for determining frequency response magnitude, phase, and coherence of measured blade root flap bending and torsion moments to elevon input, as well as elevon response to actuator input voltage. Experimental results include actuator effectiveness, effects of Reynolds number on elevon pitching moments, elevon reversal, and variation of flap bending mode responses with rotor speed and elevon excitation. The active rotor performed satisfactorily and the results provide an encouraging basis for future wind tunnel testing that will evaluate on-blade elevon effectiveness for reducing rotor blade vibratory loads.


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    Titel :

    Hover testing of a small-scale rotor with on-blade elevons


    Weitere Titelangaben:

    Der Schwebeflugtest eines kleinmaßstäblichen Hubschrauberrotormodells mit blattintegrierten Höhenruderklappen


    Beteiligte:
    Fulton, M.V. (Autor:in) / Ormiston, R.A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2001


    Format / Umfang :

    11 Seiten, 16 Bilder, 1 Tabelle, 30 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





    Aeroelastic Considerations For Rotorcraft Primary Control with On-Blade Elevons

    Ormiston, Robert A. / Rutkowski, Michael | NTRS | 2001




    Hover Test of a Mach-Scale Rotor Model with Active Blade Tips

    Bernhard, Andreas P.F. | Online Contents | 2002