B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 1/00 (2006.01) B64C 1/06 (2006.01)
Patent
CA 2742901
In the case of a structural component (2) of an aircraft or spacecraft comprising 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), at least one of the regions (10, 12, 11) has a high heat conduction resistance (R13, R14, R15).
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).
Airbus Operations Gmbh
Oyen Wiggs Green & Mutala Llp
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