A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.


    Access

    Download


    Export, share and cite



    Title :

    LINKAGE MECHANISM FOR DRIVING AIRCRAFT LANDING GEAR BAY DOOR


    Contributors:
    LV JUN (author) / MENG QINGGONG (author) / ZHANG PU (author) / JIANG HAO (author) / YANG SHANGXIN (author) / ZHANG HENGKANG (author) / MA JIAN (author)

    Publication date :

    2016-05-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Linkage mechanism for driving aircraft landing gear bay door

    LV JUN / MENG QINGGONG / ZHANG PU et al. | European Patent Office | 2018

    Free access

    Landing gear door damping mechanism for aircraft

    VEERABADRAN KAROUNEN | European Patent Office | 2016

    Free access

    Four-bar linkage unlocking mechanism of aircraft landing gear

    PAN XIAOQUAN / ZHANG LIJUN / JIA JIN et al. | European Patent Office | 2024

    Free access

    AIRCRAFT LANDING GEAR BAY DOOR

    SCOTTO ALINE / ITASSE MAXIME / BÜSCHER ALEXANDER et al. | European Patent Office | 2023

    Free access

    Aircraft landing gear hatch door

    SCOTTO IRENE / ETAS MAXIM / BUSCHER ALEXANDER et al. | European Patent Office | 2023

    Free access