An object of the present invention is to provide an electric actuator having a structure capable of reducing an external force or impact acting on a screw shaft when a piston rod is at a stretched position. An electric actuator (1) includes a first port (6), a second port (7), and a cylinder chamber connecting passage (9), the first port (6) is formed on an inner face of a rod-side cylinder chamber (5a) of a cylinder body (2), the second port (7) is formed on an inner face of a head-side cylinder chamber (5b) of the cylinder body (2), the cylinder chamber connecting passage (9) connects the first port (6) and the second port (7). In the electric actuator (1), a piston part (4a) of a piston rod (4) closes the first port (6) when the piston rod (4) advances.


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    Titel :

    Electric actuator for aircraft landing gear


    Weitere Titelangaben:

    Elektrischer Aktuator für Flugzeugfahrwerk
    Actionneur électrique pour train d'atterrissage d'aéronef


    Beteiligte:
    HIRAI MASANORI (Autor:in)

    Erscheinungsdatum :

    2019-07-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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