A plurality of hydraulically operated actuators (11,12) that drive a control surface (100) and a plurality of control systems (13,14) that respectively control the operation of the actuators (11,12) are included. Each of the control systems (13,14) includes a control valve (23,26), a state switching valve (24,27) and a test orifice circuit. The test orifice circuit includes a test orifice used for testing the performance of an orifice. The state switching valve (24,27) is provided such that its position can be switched between an actuator connection position, a damping position and a test orifice position.


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    Title :

    Aircraft actuator control apparatus


    Additional title:

    Stellgliedsteuerungsvorrichtung für Flugzeug
    Appareil de commande d'actionneur d'aéronef


    Contributors:
    ITO KOJI (author) / TANAKA TOSHIAKI (author)

    Publication date :

    2019-05-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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