An aircraft steering system (10A) includes: a first actuator (21) attached to a wing main body (11); a horn arm (13) configured to transmit an output of the first actuator (21) to a flight control surface (12); and a second actuator (22) that is a rotary actuator and attached to the flight control surface (12). At least one of the first actuator (21) and the second actuator (22) is an electromechanical actuator (EMA). A first end of the horn arm (13) is coupled to an output terminal (21a) of the first actuator (21), and a second end of the horn arm (13) is fixed to an output terminal (22a) of the second actuator (22). The second actuator (22) is attached to the flight control surface (12) such that a turning axis of the output terminal (22a) is parallel to or coincides with a fulcrum axis (hinge line) of the flight control surface (12).


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    Title :

    AIRCRAFT STEERING SYSTEM INCLUDING ELECTROMECHANICAL ACTUATOR


    Additional title:

    FLUGZEUG-LENKSYSTEM MIT ELEKTROMECHANISCHEM STELLANTRIEB
    SYSTÈME DE DIRECTION D'AÉRONEF COMPRENANT UN ACTIONNEUR ÉLECTROMÉCANIQUE


    Contributors:

    Publication date :

    2022-03-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16H Getriebe , GEARING



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