An internal cladding part for cladding a fuselage structure of an aircraft comprises a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath (51) that encases the insulation core (50) in a gas-tight manner, wherein the insulation structure is disposed in the receptacle cavity between the first and the second cover layer.


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    Titel :

    INTERNAL CLADDING PART FOR CLADDING A FUSELAGE STRUCTURE OF AN AIRCRAFT


    Weitere Titelangaben:

    PARTIE DE REVETEMENT INTERNE POUR LE GAINAGE D'UNE STRUCTURE DE FUSELAGE D'UN AERONEF


    Beteiligte:
    MUELLER RAINER (Autor:in) / SCHLIWA RALF (Autor:in)

    Erscheinungsdatum :

    17.10.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16L PIPES , Rohre



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