A structural component (2) of an aircraft or spacecraft comprises a fuselage portion connection region (10) for connecting to an associated fuselage portion (5) and having a thermal expansion coefficient which is approximately matched to the associated fuselage portion (5); an inner connection region (11) for connecting to an associated installation element and having a thermal expansion coefficient which is approximately matched to the associated installation element; and a separation region (12) for connecting the fuselage portion connection region (10) and the inner connection region (11). The fuselage portion connection region (10), the separation region (12) and the inner connection region (11) are formed in one piece with one another. At least the separation region (12) has a material structure having a high heat conduction resistance (R15) such that the heat conduction resistance (R15) of the separation region (12) is higher than that of the two other regions (10, 11). The structural component (2) is formed as a composite component having a common matrix material (16). The separation region (12) comprises the matrix material (16) and a separation composite (15) having the high heat conduction resistance (R15). The one piece construction facilitates installation of the structural component (2).

    L'invention concerne une pièce structurale (2) d'un véhicule aéronautique ou spatial avec une zone de raccordement (10) avec la partie de coque, destinée au raccordement avec une partie de coque (5) associée et possédant un coefficient de dilatation thermique sensiblement adapté à celui de la partie de coque (5) associée, avec une zone de raccordement interne (11) pour le raccordement à un élément d'installation correspondant, possédant un coefficient de dilatation thermique sensiblement adapté à celui de l'élément d'installation associé, et avec une zone de séparation (12) destinée à relier la zone de raccordement (10) avec la partie de coque et la zone de raccordement interne (11). Au moins l'une des zones (10, 11, 12) possède une haute résistance à la conduction thermique (R13, R14, R15).


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    Titel :

    STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT AND A FUSELAGE COMPONENT ARRANGEMENT OF AN AIRCRAFT OR SPACECRAFT


    Weitere Titelangaben:

    PIECE STRUCTURALE D'UN VEHICULE AERONAUTIQUE OU SPATIAL ET AGENCEMENT DE COMPOSANTS DE LA COQUE D'UN VEHICULE AERONAUTIQUE OU SPATIAL


    Beteiligte:

    Erscheinungsdatum :

    10.01.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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