Abstract: Method for manufacturing a stiffened one-piece composite structure having a panel (2a) and at least one stiffener, which are produced by fiber lay-up, by infusion of resin in an infusion tool (1) that shapes the stiffened structure through the use and incorporates an autonomous heating device realized by inner heating resistors and a covering heating sheet (1i). After placing the infusion tool (1) under vacuum and setting the temperature thereof, the resin is infused into the fibers via the infusion media, prior to demolding of the infused structure followed by trimming.

Abstract: A method for manufacturing an aircraft door with an integral structure. The method includes the following steps: producing a forged blank (7); die-cutting the forging blank (7) between a substantially smooth lower die (8) and an upper die (9) defining a plurality of cells and producing a die-cut part having a honeycomb structure having an open face and a closed face closed by a wall; an inner wall of the honeycomb structure is machined to define at least one recess defined by a web connecting the closed face and the open face and a base protruding substantially perpendicular to the web on the open face of the die cut component.

Abstract: Method for manufacturing an aircraft door having a monolithic structure, including the following steps: producing a forged blank; die-cutting the forged blank between a substantially smooth lower die and an upper die defining cells, and producing a die-cut part with a cellular structure having an open face and a face closed by a wall; machining the internal walls of the cellular structure to define at least one recess delimited by a web connecting the closed face and the open face and by a base projecting substantially perpendicular to the web, on the open face of the die-cut part.