A rotor blade assembly of an aircraft. The rotor blade assembly includes a blade attachment assembly rotatable with respect to a rotor hub assembly of the aircraft about a blade fold axis, and a pitch control assembly. The pitch control assembly includes a horn mount attachable to the rotor hub assembly, and a teeter bar hingedly attached to the horn mount at an interface, the interface defining a pitch control fold axis. The pitch control assembly is foldable about the pitch control fold axis when the pitch control fold axis is aligned with the blade fold axis.


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    Title :

    FOLDING HORN CONCEPT FOR RIGID ROTOR BLADE FOLD


    Contributors:

    Publication date :

    2020-12-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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