The invention provides a large sweepback flap driving mechanism which comprises a steering engine assembly, a driving rotating shaft, a rotating shaft support, a rocker arm, a fixed connecting rod, a supporting connecting rod and a connecting rod support, one end of the steering engine assembly is fixedly connected with a fuselage, and the other end of the steering engine assembly is rotationally connected with the driving rotating shaft; the driving rotating shaft is rotationally connected with the rotating shaft support; the rotating shaft support is fixedly connected with the machine body to support the driving rotating shaft; the rocker arm is rotationally connected with the driving rotating shaft and the fixed connecting rod; the fixed connecting rod is fixedly connected with the flap assembly; two ends of the supporting connecting rod are rotationally connected with the fixed connecting rod and the connecting rod support; the connecting rod support is fixedly connected with the machine body to support the supporting connecting rod; according to the large-sweepback flap driving mechanism, the driving rotating shaft is driven to rotate through stretching and retracting of the steering engine assembly, and the flap assembly is retracted and released parallel to the course through the driving rotating shaft, the rocker arm, the fixed connecting rod and the supporting connecting rod four-connecting-rod mechanism. According to the flap driving mechanism, the risk that the sliding rail is jammed due to uneven stress in the retracting and releasing process is avoided, and meanwhile the occupied space is smaller.

    本发明提供了一种大后掠角襟翼驱动机构,包括:舵机组件、驱动转轴、转轴支座、摇臂、固定连杆、支撑连杆和连杆支座,舵机组件一端与机身固定连接,另一端与驱动转轴转动连接;驱动转轴与转轴支座转动连接;转轴支座与机身固定连接以支撑驱动转轴;摇臂分别与驱动转轴和固定连杆转动连接;固定连杆与襟翼组件固定连接;支撑连杆两端分别与固定连杆和连杆支座转动连接;连杆支座与机身固定连接以支撑支撑连杆;其中,该大后掠角襟翼驱动机构通过舵机组件的伸缩带动驱动转轴转动,通过驱动转轴、摇臂、固定连杆和支撑连杆四连杆机构实现襟翼组件平行于航向的收放。本发明襟翼驱动机构避免了收放过程中因受力不均滑轨卡涩的风险,同时占用空间更小。


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    Titel :

    Large sweepback flap driving mechanism


    Weitere Titelangaben:

    一种大后掠角襟翼驱动机构


    Beteiligte:
    GAO SHUO (Autor:in) / MA HONGZHONG (Autor:in) / TIAN XIAO (Autor:in) / LI XUAN (Autor:in) / KANG ZHIBO (Autor:in)

    Erscheinungsdatum :

    24.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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