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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    Title :

    INTERNAL CLADDING PART FOR CLADDING A FUSELAGE STRUCTURE OF AN AIRCRAFT


    Additional title:

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


    Contributors:

    Publication date :

    2020-10-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16L PIPES , Rohre



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