Abstract: A connecting device including first and second off-center rings, the second ring being positioned in the first ring. The peripheral outer surface of the first ring is frustoconical and has a smaller cross section oriented in a first direction, and the inner surface of the first ring and the outer surface of the second ring, which surfaces interact with one another, have cross sections which increase between a first cross section and a second cross section that is offset in relation to the first cross section in an opposite direction to the first direction. This arrangement makes it possible to be able to prevent the rotation of the first and second rings once their angular positioning has been adjusted.

Abstract: A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

Abstract: A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

Abstract: A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

Abstract: A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

Abstract: An anterior zone of an aircraft, having a fuselage with frames, includes a cockpit, arranged partly above a front landing gear compartment, and a service area. The floor includes: a rear main crossbeam which extends in the plane of a frame situated in the service area and which is fixed to said frame, a port main spar and a starboard main spar, the rear ends of which are fixed to the rear main crossbeam, one or more secondary crossbeams, fixed to the port and starboard main spars, and one or more auxiliary spars. The number of crossbeam/frame attachments is reduced. The dimensioning of the principal beams of the floor is optimised; the result thereof is a weight saving.

Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

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: In a fuselage portion for an aircraft, in order to reduce the assembly clearance between the soleplate of a circumferential frame and a fuselage skin in composite material while limiting the mass of the fuselage portion, a ply drop-off is used comprising two portions oriented in the circumferential direction and having different respective slopes.

Abstract: An aircraft fuselage member and a frame are linked by a clip and a spacer. An assembly includes an aircraft fuselage member, having a skin and stringers linked to the skin, a reinforcing frame, and a clip rigidly linking the fuselage member and the frame. The clip is rigidly linked to the skin via a spacer, independent from the stringers, interposed between the fuselage member and the clip. An aircraft fuselage part includes several assemblies so defined. The cost of a fuselage is thereby reduced by standardization of the clips and/or reduction of the maximum width of the stringers.

Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.

Abstract: An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.

Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.

Abstract: A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.

Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.

Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.

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 stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.

Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.