Pitch or roll damping has been studied using model rotors in rocking motion. The rotors have articulated blades with spring constrained hinges and different combinations of Lock number, flapping hinge offset, and hinge constrained stiffness. By consideration of nonuniform induced velocity distribution a theoretical estimation based on the momentum and blade element theory has shown good coincidence with the experimental results. In contrast with analyses based on the vortex theory, the present theory does not require complex calculations so that analytic evaluation and quick estimation of the dynamic stability derivatives will be possible. The blade flapping behavior during sinusoidal rocking motion has also been analyzed and the mechanism of generation of direct damping and cross coupling moments clearly explained.


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    Titel :

    Pitch damping of helicopter rotor with nonuniform inflow


    Weitere Titelangaben:

    Helikopterrotor-Hoehendaempfung durch ungleichmaessigen Einfluss


    Beteiligte:
    Azuma, A. (Autor:in) / Nakamura, Y. (Autor:in)

    Erschienen in:

    Journal of Aircraft ; 11 , 10 ; 639-646


    Erscheinungsdatum :

    1974


    Format / Umfang :

    , 12 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Pitch damping of helicopter rotor with nonuniform inflow

    AZUMA, A. / NAKAMURA, Y. | AIAA | 1974




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