Reinforced aircraft fuselage panel and method of manufacture
AssigneeAirbus Operations GmbH
InventorsOlivier Harasse, Francois Parreaux-Ey
Life of this patent
Estimating the term…
Abstract
A fuselage panel made of composite material having a skin with an opening, at least part of the contour of which is reinforced by an integrated reinforcement made of composite material. The fuselage panel includes at least one liner made of composite material which is attached to and superposed on the reinforced skin portion and participates at least partially in defining the contour of the opening, the panel additionally including consolidating members, each passing at least partially through the liner and at least partially through the reinforced skin portion.
Claims10
A fuselage panel made of composite material comprising a skin having an opening, at least part of the contour of which is reinforced by an integrated reinforcement made of composite material, defining a reinforced skin portion, said integrated reinforcement defining at least part of the contour of said opening and comprising a ply drop-off,
- wherein said fuselage panel comprises at least one liner made of composite material which is attached to and superposed on said reinforced skin portion and participates at least partially in defining the contour of the opening, said panel additionally comprising consolidating members, each passing at least partially through said liner and at least partially through said reinforced skin portion.
A method of manufacturing a fuselage panel made of composite material having an opening, said method, comprising the following steps:
- creating a stack of preimpregnated fibre plies, comprising
- a plurality of plies intended to form a panel skin, comprising a first set of plies and a second set of plies,
- interposing one or more plies between the first and second sets of plies and forming an integrated reinforcement for the opening, the plies of the integrated reinforcement and those of the panel skin defining together a reinforced skin portion, and
- arranging one or more plies on the plies forming said reinforced skin portion, and forming a liner for said fuselage panel;
- then
- consolidating said stack;
- installing consolidating members passing at least partially through the liver;
- and
- trimming so as to form said opening.
Dependencies are inferred from the claim text.