A new method of reducing helicopter rotor hub loads and marginally improving rotor performance by the introduction of large values of blade root torsional damping is presented. Basic theoretical considerations imply that these benefits in hub loads can come about by changes to the blade elastic torsional deflection. This basic theory was analytically verified by using a fully coupled aeroelastic rotorcraft analysis as applied to a modern, articulated rotor blade, namely that of the Sikorsky S-76. From an implementation standpoint, a rotor-based torsional damping device may be more practical than one that involves a major portion of the blade span. Also, a root-based device may allow for the retrofitting of existing helicopter rotor blade/hub configurations.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Blade root torsional dampers to reduce hub loads


    Beteiligte:

    Kongress:

    AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference ; 1992 ; Dallas, TX, United States


    Erscheinungsdatum :

    01.01.1992


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Blade root torsional dampers to reduce hub loads

    Kottapalli, S. | Tema Archiv | 1992



    Torsional Dampers and Alternative Systems to Reduce Driveline Vibrations

    Drexl, Hans Jürgen | SAE Technical Papers | 1987


    Torsional Dampers and Alternative Systems to Reduce Driveline Vibrations

    Drexl,H.J. / Fichtel und Sachs,DE | Kraftfahrwesen | 1987


    Torsional-vibration dampers

    Baker, J.G. / Den Hartog, J.P. | Engineering Index Backfile | 1931