An aircraft includes a fuselage and a wing extending from each lateral side of the fuselage. A nacelle is pivotably se cured to each wing. The nacelle has a rotor located thereat, with the rotor having a rotor tip path plane defined by rotation of the rotor about a rotor axis of rotation. When the rotor tip path plane is changed relative to the wing, the nacelle pivots relative to the wing about a nacelle hinge axis to reduce flapping required by the rotor. A method of operating an aircraft includes changing a rotor tip path plane orientation relative to a wing of the aircraft. The rotor disposed at a nacelle, with the nacelle pivotably secured to the wing. The nacelle is pivoted relative to the wing to reduce an overall tip path plane change requirement of the rotor.


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    Title :

    COMPLIANT ENGINE NACELLE FOR AIRCRAFT


    Contributors:

    Publication date :

    2017-07-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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