Abstract: The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.

Abstract: A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.

Abstract: The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.

Abstract: A frame of an aircraft fuselage structure made from composite material, which includes a skin and several stringers fixed on the skin. The frame includes a profile elongated in a longitudinal direction which is hollow over at least a portion of its length. The profile is mounted on two legs. Each leg, intended to be fixed on the skin, includes a first portion extending continuously over the whole length of the profile and a second portion extending from this continuous portion so as to form several openings spaced apart in the longitudinal direction of the profile, in each of which a stringer passes. The presence of the hollow profile in the frame and the structure of the legs makes it possible to dispense with clips and cleats.

Abstract: A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.

Abstract: The invention provides a self-stiffened composite panel including an external skin, an internal skin superposed on the external skin, which covers an internal face of the external skin and at least one stiffener protruding inwards relatively to the internal skin which extends along a longitudinal direction, characterised in that the stiffener is made as one piece with the internal skin and consists of a portion of the internal skin which is located at distance from the external skin. The invention also provides a process for making such a self-stiffened panel.

Abstract: A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.

Abstract: A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.