Described and illustrated is a pressure bulkhead (1) for an aircraft fuselage, comprising a sandwich structure (3) defining a central axis (5) and extending between a circumferential border area (7) which is configured for being mounted to a fuselage shell, wherein the sandwich structure (3) comprises an inner face sheet (9) extending perpendicularly with respect to the central axis (5), an outer face sheet (11) opposite the inner face sheet (9), extending perpendicularly with respect to the central axis (5), and a core assembly (13) sandwiched between the inner face sheet (9) and the outer face sheet (11), wherein the inner face sheet (9), when viewed in a radial cross section (15) along the central axis (5), has an even shape. The object of the present invention, to provide a pressure bulkhead (1) for an aircraft fuselage, wherein the required weight is reduced, is achieved in that the outer face sheet (11), when viewed in said radial cross section (15) along the central axis (5), has a convex shape, wherein the distance between the outer face sheet (11) and the inner face sheet (9) increases tangent continuously from the border area (7) to the central axis (5).
A PRESSURE BULKHEAD FOR AN AIRCRAFT FUSELAGE, AND AN AIRCRAFT COMPRISING SUCH A PRESSURE BULKHEAD
TRAVERSEE DE CLOISON A PRESSION DESTINEE A UN FUSELAGE D'AERONEF, ET UN AERONEF COMPORTANT UNE TELLE TRAVERSEE DE CLOISON A PRESSION
20.11.2016
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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