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, the Sikorsky S-76. From an implementation standpoint, a root-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. At this time there has been some interest shown in this new method of reducing hub loads.


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    Titel :

    Blade root torsional dampers to reduce hub loads


    Weitere Titelangaben:

    Torsiondämpfer am Flügelansatz zur Verminderung der Nabenbelastung


    Beteiligte:
    Kottapalli, S. (Autor:in)


    Erscheinungsdatum :

    1992


    Format / Umfang :

    9 Seiten, 13 Bilder, 14 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch






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