The invention discloses a flap control system with a load limiting function and an airplane, a coupling connecting piece is provided with a first end, a second end and a connecting section, and the first end and the second end are fixed to a first torque tube and a second torque tube respectively; one end of the driving rocker arm is fixed to the connecting section, the other end of the driving rocker arm is connected with the flap actuator, and when the flap actuator works, the driving rocker arm can be driven to rotate, and meanwhile the first torque tube and the second torque tube are driven to rotate synchronously. The driving rocker arm is fixed on the connecting section through the unloading connecting device, and when the torque tube is subjected to a load exceeding the bearing limit of the unloading connecting device, the unloading connecting device loses efficacy in connection, so that the driving rocker arm can rotate relative to the axial direction of the coupling connecting piece to realize unloading. According to the scheme, synchronous control over the flaps can be achieved, the load limiting function is added, meanwhile, the flap control system is simple in structure and reliable in control, and the flight safety of an aircraft is guaranteed.

    本申请公开了一种具有载荷限制功能的襟翼控制系统及飞机,耦合连接件具有第一端、第二端以及连接段,第一端和第二端分别与第一扭力管和第二扭力管固定;驱动摇臂一端固定在连接段上,驱动摇臂的另一端与襟翼作动器连接,当襟翼作动器工作时会驱动驱动摇臂转动,同时带动第一扭力管和第二扭力管同步转动。驱动摇臂通过卸载连接装置固定在连接段上,当扭力管受到超过卸载连接装置承受限度的载荷时,卸载连接装置连接失效,使驱动摇臂相对耦合连接件的轴向能够发生转动,以实现卸载。本申请提供的方案不仅能实现对襟翼的同步控制,而且在增加了载荷限制功能的同时襟翼控制系统的构造简单、操控可靠,保证了飞机飞行的安全性。


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    Titel :

    Flap control system with load limiting function and airplane


    Weitere Titelangaben:

    一种具有载荷限制功能的襟翼控制系统及飞机


    Beteiligte:
    SHI XIAOLONG (Autor:in) / LIU JUHONG (Autor:in) / MA CHAO (Autor:in) / MAO DE'AI (Autor:in)

    Erscheinungsdatum :

    02.04.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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