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.


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    Titel :

    Linkage mechanism for driving aircraft landing gear bay door


    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 :

    2018-01-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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