A first actuator (14a) drives a control surface (103a) by being operated by supply of pressure oil from a first aircraft central hydraulic power source (104) including a first aircraft central hydraulic pump (104a) . A second actuator (14b) drives the control surface by being operated by supply of pressure oil from a second aircraft central hydraulic power source (105) including a second aircraft central hydraulic pump (105a) . A backup hydraulic pump (18) is installed inside a wing (102a) of the aircraft (100) and is provided so as to be able to supply pressure oil to the first actuator (14a) when a loss or degradation in a function of at least one of the first aircraft central hydraulic power source (104) and the second aircraft central hydraulic power source (105) occurs. A maximum discharge pressure of the backup hydraulic pump (18) is set to be greater than maximum discharge pressures of the first aircraft central hydraulic pump (104a) and the second aircraft central hydraulic pump (104b).


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    Title :

    Aircraft actuator hydraulic system


    Additional title:

    Flugzeughydraulikantriebssystem
    Système hydraulique d'actionneur d'avion


    Contributors:

    Publication date :

    2018-04-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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