The invention discloses an aircraft actuating system based on a dual-redundancy electro-hydraulic actuator, and relates to the technical field of electro-hydraulic control. A left wing actuation system and a right wing actuation system of the system respectively comprise an aileron actuation subsystem, a leading edge flap actuation subsystem, a trailing edge flap actuation subsystem, a spoiler actuation subsystem and a hydraulic driving system. The empennage actuating system comprises an elevator actuating subsystem, a rudder actuating subsystem and a hydraulic driving system; each subsystem comprises a dual-redundancy electro-hydraulic actuator, a control system and a control system, the dual-redundancy electro-hydraulic actuator comprises a four-cavity hydraulic cylinder, an open valve control unit, a closed pump control unit and a displacement sensor; the highly-integrated four-cavity hydraulic cylinder is adopted as an actuator of the aircraft actuation system, the closed pump control unit and the open valve control unit are combined to form a heterogeneous redundant actuation system, the weight and the size of the aircraft actuation system can be reduced, and the reliability is improved.

    本发明公开一种基于双余度电液执行器的飞机作动系统,涉及电液控制技术领域;该系统的左翼作动系统和右翼作动系统均包括副翼作动子系统、前缘襟翼作动子系统、后缘襟翼作动子系统、扰流板作动子系统和液压驱动系统;尾翼作动系统包括升降舵作动子系统、方向舵作动子系统和液压驱动系统;并且各个子系统均包括:双余度电液执行器;而双余度电液执行器包括:四腔液压缸、开式阀控单元、闭式泵控单元和位移传感器;本发明采用高度集成四腔液压缸作为飞机作动系统的作动器,结合闭式泵控单元和开式阀控单元组成异构冗余的作动系统,能够减轻飞机作动系统的重量和体积,并提升可靠性。


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    Titel :

    Aircraft actuating system based on dual-redundancy electro-hydraulic actuator


    Weitere Titelangaben:

    一种基于双余度电液执行器的飞机作动系统


    Beteiligte:
    LIANG TAO (Autor:in) / QUAN LONG (Autor:in) / LI ZEPENG (Autor:in) / XIA LIANPENG (Autor:in) / GE LEI (Autor:in) / WANG XIANGYU (Autor:in)

    Erscheinungsdatum :

    15.11.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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