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    CONNECTING ROD MECHANISM FOR CONTROLLING AIRCRAFT LANDING GEAR HATCH DOOR
    2.
    发明公开
    CONNECTING ROD MECHANISM FOR CONTROLLING AIRCRAFT LANDING GEAR HATCH DOOR 审中-公开
    PLEUELSTANGENVORRICHTUNG ZUR STEUERUNG DER HECKKLAPPE EINES FLUGZEUGFAHRWERKS

    公开(公告)号：EP2987723A1

    公开(公告)日：2016-02-24

    申请号：EP14855588.1

    申请日：2014-08-20

    申请人： Commercial Aircraft Corporation Of China Ltd ,  Commercial Aircraft Corporation Of China Ltd Shanghai Aircraft Design and Research Institute

    发明人： LV, Jun ,  MENG, Qinggong ,  ZHANG, Pu ,  JIANG, Hao ,  YANG, Shangxin ,  ZHANG, Hengkang ,  MA, Jian

    IPC分类号： B64C25/16

    CPC分类号： B64C25/20 ,  B64C25/10 ,  B64C25/16

    摘要： Disclosed is a linkage mechanism (100) for driving an aircraft landing gear bay door, comprising: a primary torsion tube (10) comprising a first portion located inside a landing gear bay and a second portion outside the landing gear bay; a first drive apparatus connected between the first portion and a strut (201) of a landing gear (200) so as to transfer the driving force of the strut to the primary torsion tube (10); a secondary torsion tube (20) comprising an inner end portion located inside the bay and an outer end portion located outside the bay; a secondary drive apparatus connecting the primary torsion tube (10) and the secondary torsion tube (20) outside the bay; and two third drive apparatuses respectively connected between the inner end portion of the secondary torsion tube (20) and one of the bay doors. The secondary drive apparatus is located outside the landing gear bay, saving on space inside the bay, and reducing interference between motion mechanisms. A single side of the secondary torsion tube (20) transfers torque so that synchronism of the bay door is high. The number of components is reduced and power drive performance is high.

    摘要翻译： 公开了一种用于驱动飞机起落架舱门的联动机构（100），包括：主扭矩管（10），包括位于起落架舱内的第一部分和起落架舱外部的第二部分; 连接在起落架（200）的第一部分和支柱（201）之间以将支柱的驱动力传递到主扭转管（10）的第一驱动装置; 第二扭转管（20）包括位于所述隔间内部的内端部分和位于所述托架外部的外端部分; 将所述主扭力管（10）和所述副扭转管（20）连接在所述托架外部的次级驱动装置; 以及分别连接在二次扭转管（20）的内端部和其中一个托架门之间的两个第三驱动装置。 二次驱动装置位于起落架舱外部，节省了舱内空间，减少了运动机构之间的干扰。 二次扭转管（20）的单侧传递扭矩，从而间隔门的同步性很高。 组件数量减少，动力驱动性能较高。