The invention provides an internal cladding part for cladding a fuselage structure of an aircraft, which 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 that encases the insulation core in a gas-tight manner, wherein the insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

    本发明提供一种用于装饰飞行器的机身结构的内饰板部件,包括:面型地延伸的第一覆盖层;面型地延伸的第二覆盖层;芯层,所述芯层被布置在所述第一覆盖层与所述第二覆盖层之间并且与所述第一覆盖层和所述第二覆盖层相连,所述芯层限定接收空腔;以及隔离结构,所述隔离结构具有多孔的隔离芯和气密地包裹所述隔离芯的、抽真空的箔外壳,其中所述隔离结构被布置在所述第一覆盖层与所述第二覆盖层之间的接收空腔中。


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    Titel :

    Internal cladding part for cladding fuselage structure of aircraft


    Weitere Titelangaben:

    用于装饰飞行器的机身结构的内饰板部件


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

    Erscheinungsdatum :

    27.10.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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