A hydraulic servo actuation system and method for an aircraft are disclosed. The hydraulic servo actuation system comprises a hydraulic redundancy configuration device which comprises hydraulic input interfaces and hydraulic output interfaces, the hydraulic input interfaces comprise a first set of input interfaces and a second set of input interfaces, the first set of input interfaces are connected to a first hydraulic system, and the second set of input interfaces are connected to a second hydraulic system. The hydraulic redundancy configuration device also includes a control valve assembly that switchably connects the hydraulic output interface of the hydraulic redundancy configuration device to the first set of input interfaces or the second set of input interfaces. A servo actuator is connectable to a hydraulic output interface of the hydraulic redundancy configuration device and is used to drive a flight control surface of the aircraft.

    公开了一种用于飞行器的液压伺服作动系统和方法。该液压伺服作动系统包括液压余度配置装置,其包括液压输入接口和液压输出接口,液压输入接口包括第一组输入接口和第二组输入接口,第一组输入接口连接至第一液压系统,第二组输入接口连接至第二液压系统。液压余度配置装置还包括控制阀组件,其可切换地将液压余度配置装置的液压输出接口连接至第一组输入接口或第二组输入接口。伺服作动器可连接至液压余度配置装置的液压输出接口并且用于驱动飞行器的飞行控制面。


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    Titel :

    Hydraulic servo actuation system and method for aircraft


    Weitere Titelangaben:

    一种用于飞行器的液压伺服作动系统和方法


    Beteiligte:
    WANG XIAOYING (Autor:in) / LIU ZHIYU (Autor:in) / HONG QIAN (Autor:in)

    Erscheinungsdatum :

    23.01.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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