A design procedure is presented for the installation of simple pendulums on the blades of a helicopter rotor to suppress the root reactions. The procedure consists of a frequency response analysis for a hingeless rotor blade excited by a harmonic variation of spanwise airload distributions during forward flight, as well as a concentrated load at the tip. The structural modeling of the blade provides for elastic degrees of freedom in flap and lead-lag bending plus torsion. Simple flap and lead-lag pendulums are considered individually. Using a rational order scheme, the general nonlinear equations of motion are linearized. A quasi-steady aerodynamic representation is used in the formation of the airloads. The solution of the system equations derives from their representation as a transfer matrix. The results include the effect of pendulum tuning on the minimization of the hub reactions.


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    Title :

    Helicopter vibration suppression using simple pendulum absorbers on the rotor blade


    Contributors:

    Conference:

    National Specialists Meeting on Helicopter Vibration ; 1981 ; Hartford, CT


    Publication date :

    1981-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







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