An actuation system for a control surface for an aircraft includes a first, second, third and fourth actuator, a first and second bell crank, and at least one push pull rod system. Each of the first and second bell cranks comprises a first and a second crank arm, the first and second crank arms intersect with and are joined to each other at an intersection, the first and second crank arms extend from the intersection at an angle to each other, the first bell crank is pivotally connected to the sub-structure by a first pivot extending through the first bell crank's intersection, and the second bell crank is pivotally connected to the sub-structure by a second pivot extending through the second bell crank's intersection.


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    Titel :

    ACTUATION SYSTEMS FOR CONTROL SURFACES FOR AIRCRAFT


    Beteiligte:
    POTIER KARL (Autor:in) / HERVIEUX ARNAULD (Autor:in) / VANDEVOIR SEBASTIEN (Autor:in)

    Erscheinungsdatum :

    2022-07-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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