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.


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    Titel :

    CONNECTING ROD MECHANISM FOR CONTROLLING AIRCRAFT LANDING GEAR HATCH DOOR


    Weitere Titelangaben:

    PLEUELSTANGENVORRICHTUNG ZUR STEUERUNG DER HECKKLAPPE EINES FLUGZEUGFAHRWERKS
    MÉCANISME DE BIELLE DESTINÉ À COMMANDER UNE PORTE DE TRAPPE D'UN TRAIN D'ATTERRISSAGE D'AÉRONEF


    Beteiligte:
    LV JUN (Autor:in) / MENG QINGGONG (Autor:in) / ZHANG PU (Autor:in) / JIANG HAO (Autor:in) / YANG SHANGXIN (Autor:in) / ZHANG HENGKANG (Autor:in) / MA JIAN (Autor:in)

    Erscheinungsdatum :

    19.09.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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