The University of Maryland Advanced Rotorcraft Code (UMARC) is utilized to study the effects of blade design parameters on the aeroelastic stability of an isolated modern bearingless rotor blade in hover. The McDonnell Douglas Advanced Rotor Technology (MDART) Rotor is the baseline rotor investigated. Results indicate that kinematic pitch-lag coupling introduced through the control system geometry and the damping levels of the shear lag dampers strongly affect the hover inplane damping of the baseline rotor blade. Hub precone, pitchcase chordwise stiffness, and blade fundamental torsion frequency have small to moderate influence on the inplane damping, while blade pre-twist and placements of blade fundamental flapwise and chord-wise frequencies have negligible effects. A damperless configuration with a leading edge pitch-link, 15 deg of pitch-link cant angle, and reduced pitch-link stiffness is shown to be stable with an inplane damping level in excess of 2.7 percent critical at the full hover tip speed.


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    Title :

    Aeroelastic Stability of Modern Bearingless Rotors: A Parametric Investigation


    Contributors:

    Publication date :

    1994


    Size :

    8 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Aeroelastic Stability of Modern Bearingless Rotors - A Parametric Investigation

    Nguyen, K. / Ames Research Center / American Helicopter Society; San Francisco Bay Area Chapter | British Library Conference Proceedings | 1993



    Aeroelastic Stability of Modern Bearingless Rotors - A Parametric Investigation

    Nguyen, K. / Ames Research Center / American Helicopter Society; San Francisco Bay Area Chapter | British Library Conference Proceedings | 1994


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    Dull, Andrew L. / Chopra, Inderjit | NTRS | 1987