The objectives of the present investigation are: Develop a mathematical model to respresent the blade-pendulum system. A single nonuniform rotor blade with a hingeless hub restraint undergoing coupled flapwise bending, chordwise bending, and torsion vibrations is considered. Simple pendulum absorbers are individually treated for both flap and lead-lag types of motion. The blade is excited by an azimuthal harmonic variation of spanwise airload distributions associated with the elastic deformations and the cyclic pitch environment of forward flight; Find the dynamic response characteristics of the blade-pendulum system, using the transfer matrix method; Determine the optimum pendulum tuning to suppress the hub reactions. This entails the minimization of these reactions by appropriate variations of the pendulum parameters for a given excitation frequency. The pendulum parameters include the uncoupled pendulum frequency, hinge spanwise location and pendulum mass; and Conduct a parametric study of the optimum tuned configuration. The parameters to be varied include pendulum hinge offset, precone, prepitch and pretwist.


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    Titel :

    Helicopter vibration suppression using simple pendulum absorbers on the rotor blade


    Weitere Titelangaben:

    Unterdrueckung der Hubschrauberschwingungen mittels einfacher Pendelabsorber fuer das Rotorblatt


    Beteiligte:
    Pierce, G.A. (Autor:in) / Hamouda, M.H. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1982


    Format / Umfang :

    140 Seiten


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch




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