Helicopter rotor individual blade control promises to provide a mechanism for increased rotor performance and reduced rotorcraft vibrations and noise. Active material methods, such as piezoelectrically actuated trailing-edge flaps and strain-induced rotor blade twisting, provide a means of accomplishing individual blade control without the need for hydraulic power in the rotating system. Recent studies have indicated that controlled strain induced blade twisting can be attained using piezoelectric active fiber composite technology. In order to validate these findings experimentally, a cooperative effort between NASA Langley Research Center, the Army Research Laboratory, and the MIT Active Materials and Structures Laboratory has been developed. As a result of this collaboration an aeroelastically-scaled active-twist model rotor blade has been designed and fabricated for testing in the heavy gas environment of the Langley Transonic Dynamics Tunnel (TDT). The results of hover tests of the active-twist prototype blade are presented in this paper. Comparisons with applicable analytical predictions of active-twist frequency response in hovering flight are also presented.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Hover Testing of the NASA/Army/MIT Active Twist Rotor Prototype Blade


    Beteiligte:

    Kongress:

    56th American Helicopter Society Annual Forum ; 2000 ; Virginia Beach, VA, US


    Erscheinungsdatum :

    2000-05-02



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Modeling, design, and testing of the NASA/Army/MIT active twist rotor prototype blade

    Cesnik, C.E.S. / Shin, Sang-Joon / Wilkie, W.K. et al. | Tema Archiv | 1999





    Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor

    Wilbur, M.L. / Mirick, P.H. / Yaeger, W.T. jun. et al. | Tema Archiv | 2002