The invention relates to an actuator (4) for controlling a horizontal stabiliser (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabiliser (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the housing (23, 26).


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    Titel :

    Actuator for Controlling a Horizontal Stabilizer of an Aircraft


    Beteiligte:
    ANTUNES BRUNO (Autor:in) / GOUARD CHRISTIAN (Autor:in) / GORECKI HERVÉ (Autor:in) / MEHEZ JÉRÔME (Autor:in) / HUMANES JESUS-ANGEL (Autor:in)

    Erscheinungsdatum :

    2016-11-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16H Getriebe , GEARING / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein



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