The invention relates to a linkage mechanism (12) for linking a flaperon (40) to a droop panel (30) of an aircraft (10), the linkage mechanism (12) comprising a support structure linkage (62), a droop panel linkage (32), and a flaperon linkage (42), wherein the support structure linkage (62) is pivotally attached at a pivot end (64) to a support structure (60) of a wing (20) of an aircraft (10), wherein the droop panel linkage (32) is pivotally attached at a first end (34) to a droop panel (30), wherein the flaperon linkage (42) is pivotally attached at a first end (44) to a flaperon (40), and wherein a second end (36) of the droop panel linkage (32) and a second end (46) of the flaperon linkage (42) are pivotally attached to a connecting section (66) of the support structure linkage (62), wherein the connecting section (66) is spaced apart from the pivot end (64) of the support structure linkage (62), such that the linkage mechanism (12) is configured to transfer a pivoting motion from the flaperon (40) into a pivoting motion of the droop panel (30). The invention provides an improved linkage mechanism (12) for linking the flaperon (40) and the droop panel (30).


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    Titel :

    LINKAGE MECHANISM FOR LINKING A FLAPERON TO A DROOP PANEL OF AN AIRCRAFT


    Weitere Titelangaben:

    VERBINDUNGSMECHANISMUS ZUM VERBINDEN EINES FLAPERONS MIT EINER DROOP-KLAPPE EINES FLUGZEUGS
    MÉCANISME DE LIAISON POUR RELIER UN VOLET-AILERON À UN PANNEAU DE CHUTE D'UN AÉRONEF


    Beteiligte:
    HENCKE MARC (Autor:in) / GIBBERT MARKUS (Autor:in) / GEHLE FLORIAN (Autor:in)

    Erscheinungsdatum :

    2019-08-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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