The present invention relates to a blade folding apparatus that may incorporate an overhead blade lifting system that reduces binding loads on blade pins induced by blade weight and pitch, and a folding mechanism that removes the necessity of personnel with external guide-poles to rotate main rotor blades. The apparatus may include flap locks, an overhead lifting system support structure attached to the flap locks, and two blade support beams to create and support a lifting point near each blade's longitudinal and lateral center of gravity. The blade support beams may be fitted with an articulation mechanism that lifts and/or lowers the overhead lifting structure. The apparatus facilitates rapid folding of the main rotor blades, and, when used with blade clamping mechanisms, is capable of aiding in the removal and/or the re-installation of the main rotor blades without external lifting mechanisms.


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    Titel :

    Helicopter blade folding apparatus


    Beteiligte:

    Erscheinungsdatum :

    2019-05-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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