The present invention provides an aircraft wing fuel tank filler cap and a structure in a circumferential region of the filler cap and relates to the technical field of aviation. The aircraft wing fuel tank filler cap comprises an inner filler cap, an outer filler cap, a sandwich layer, a fixing piece and a fastener; the inner filler cap is hermetically connected to a wing lower panel and the outer filler cap through the sandwich layer; the fastener is disposed in the inner filler cap; the fixing piece passes through a fixing hole in the outer filler cap and is connected with the fastener; and an intercalation sunken region at filler cap of wing lower panel provides a flat mounting region for the inner filler cap and also guarantees fitting of the outer filler cap and the panel. The metal outer filler cap in the present invention guarantees the demands on the shock resistance and lightning protection of the fuel tank filler cap and plays a role in protecting the composite inner filler cap, and meanwhile, the composite inner filler cap is capable of effectively reducing the weight of a fuel tank filler cap assembly, so that galvanic corrosion brought by a single metal alloy filler cap is avoided.


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    Titel :

    AIRPLANE WING FUEL TANK ACCESS COVER AND STRUCTURE OF PERIPHERAL AREA OF ACCESS COVER


    Weitere Titelangaben:

    TANKZUGANGSDECKEL FÜR FLUGZEUGFLÜGEL UND STRUKTUR DES PERIPHEREN BEREICHS EINES ZUGANGSDECKELS
    COUVERCLE D'ACCÈS DE RÉSERVOIR DE CARBURANT D'AILE D'AVION ET STRUCTURE DE ZONE PÉRIPHÉRIQUE DE COUVERCLE D'ACCÈS


    Beteiligte:
    MA BO (Autor:in) / LUO DAN (Autor:in) / WANG JIANLI (Autor:in) / XU JIFENG (Autor:in)

    Erscheinungsdatum :

    06.11.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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