An actuator control arrangement is provided comprising a pair of rotary control valves (10a, 10b) used in combination to control the operation of an actuator (12). The rotary control valves (10a, 10b) are driven synchronously through a hydraulic or mechanical coupling. Each rotary control valve has a by-pass mode which activates in the event of a jam. In addition each rotary control valve has a mechanism for activating the by-pass mode absent any jam. The actuator control arrangement further comprises a circuit coupling a pilot control (100) and/or a flight control computer (FCC) to one or both of the mechanisms for remotely switching the rotary control valve(s) from an active mode to a by-pass mode under control of a pilot or FCC.


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    Title :

    ACTUATOR CONTROL ARRANGEMENT


    Additional title:

    STELLANTRIEBKONTROLANORDNUNG
    ARRANGEMENT DE CONTROLE D'UN ACTUATEUR


    Contributors:

    Publication date :

    2018-04-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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