Free-tip rotor blades improve fuel efficiency and performance characteristics of helicopters. Outermost portion of blade pivots independently with respect to inboard portion about pitch axis parallel to blade axis, located forward of aerodynamic center. Centrifugal force acts on tension/torsion strap and biases tip nose-up. Airstream turns tip nose-down, other torques cause tip to "weathervane" to intermediate angular position resulting in net lift. Reduces fluctuations in lift, with two effects: flapwise vibratory loads on blade and vibratory loads on pitch-control mechanism reduced; negative lift produced by advancing fixed tip eliminated, reducing power required to achieve same overall lift. Applies to tilt rotors and tail rotors as well.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Helicopter Rotor Blade With Free Tip


    Beteiligte:
    Stroub, Robert H. (Autor:in) / Young, Larry (Autor:in) / Cawthorne, Matthew (Autor:in) / Keys, Charles (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.08.1992



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    HELICOPTER ROTOR BLADE

    EREMIN MIKHAIL MIKHAJLOVICH / BORISOV EVGENIJ ALEKSANDROVICH | Europäisches Patentamt | 2018

    Freier Zugriff

    HELICOPTER ROTOR BLADE

    NEKRASOV VLADIMIR IVANOVICH | Europäisches Patentamt | 2016

    Freier Zugriff

    Helicopter rotor blade

    WANG HUILING / CAI MENG / TIAN SHUQUAN et al. | Europäisches Patentamt | 2021

    Freier Zugriff

    HELICOPTER, BLADE, AND ROTOR

    HARADA MASASHI | Europäisches Patentamt | 2017

    Freier Zugriff

    HELICOPTER, BLADE AND ROTOR

    HARADA MASASHI | Europäisches Patentamt | 2017

    Freier Zugriff