An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.


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    Titel :

    Actuator arrangement for a flexible control surface of an aircraft, control surface with actuator arrangement, and aircraft with flexible control surface


    Beteiligte:
    BENTIVOGLIO MARC ANTONIO (Autor:in) / BIONDINI MARCO (Autor:in) / HOEFT MICHAEL (Autor:in) / LUETTMANN HENRIK (Autor:in) / WERWER MALTE (Autor:in) / THOMAS ANDRE (Autor:in)

    Erscheinungsdatum :

    07.12.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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