Patent ID: 9034453
Filing Date: 2015-05-19
Classification: B64C,Y02T,Y10T

Abstract:
1. A fuselage panel made of composite material comprising: a skin having an opening, at least part of a contour of the opening is reinforced by an integrated reinforcement made of composite material defining a reinforced skin portion and the integrated reinforcement comprising a first portion having a substantially constant thickness, defining at least part of the contour of the opening, and a second portion having a ply drop-off, extending from the first portion and having a thickness that gradually decreases in a direction away from the first portion such that an average slope of the ply drop-off is between 1/40 and 1/20; at least one liner made of composite material assembled by co-curing to said reinforced skin portion such that said at least one liner is superposed on the first portion of the integrated reinforcement and attached to said reinforced skin portion and participates at least partially in defining the contour of the opening; and consolidating members, oriented along an axis that is substantially orthogonal, locally, to the surface of the skin, each of the consolidating members passing at least partially through said liner and at least partially through said reinforced skin portion, wherein the at least one liner and said reinforced skin portion each includes a same thermosetting resin, and wherein the resin of the liner and the resin of said reinforced skin portion are polymerized to one another in a connection surface area between the liner and said reinforced skin portion.