A yaw control system of an aircraft includes an aircraft having an airframe extending along a longitudinal axis, a coaxial contra-rotating main rotor system rotatable about a first axis, and a rotor system rotatable about a second axis to move air between a first side of the airframe and a second, opposite side of the airframe. The first side and the second side are disposed on opposing sides of the longitudinal axis. The yaw control provided by operation of the rotor system is supplemental to the yaw control provided by the coaxial contra-rotating main rotor system.


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    Titel :

    ROTARY WING AIRCRAFT WITH ENHANCED YAW CAPABILITY


    Beteiligte:
    ALBER MARK R (Autor:in)

    Erscheinungsdatum :

    16.01.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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