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AssigneeAirbus Operations GmbH
InventorJerome Milliere
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A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.”
A method for assembling frames on a fuselage of an aircraft, wherein fuselage elements comprising a fuselage skin, presenting an internal side and an external side, frames and ribbands are assembled in a supply phase, the skin and the frames being made of composite materials based on carbon fibers, comprising the steps:
Dependencies are inferred from the claim text.