A passive vibration reduction device in which the conventional main rotor blade pitch link is replaced by a spring/damper element is investigated using a comprehensive rotorcraft analysis code. A case study is conducted for a modern articulated helicopter main rotor. Correlation of vibratory pitch link loads with wind tunnel test data is satisfactory for lower harmonics. Inclusion of unsteady aerodynamics had little effect on the correlation. In the absence of pushrod damping, reduction in pushrod stiffness from the baseline value had an adverse effect on vibratory hub loads in forward flight. However, pushrod damping in combination with reduced pushrod stiffness resulted in modest improvements in fixed and rotating system hub loads.


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    Title :

    Dynamically Tuned Blade Pitch Links for Vibration Reduction


    Contributors:

    Conference:

    Annual Forum of the American Helicopter Society ; 1994 ; Washington, DC, United States


    Publication date :

    1994-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Dynamically tuned blade pitch links for vibration reduction

    Milgram, J. / Chopra, I. / Kottapalli, S. | Tema Archive | 1994





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