Abstract: A cabinet comprising at least one screen allowing display of data necessary for a flight-control of an aircraft connected to at least one avionics module for management of the data. The screen at least partially forms one of the sides of the cabinet and the module or modules are installed inside the cabinet. The cabinet has a base allowing the screen or screens to be placed at a desired height. As a result, a length of cable between screen and avionics modules is reduced to a minimum.

Abstract: A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

Abstract: To reduce the bulk of an aircraft toilet which includes a toilet bowl and a washbasin, the washbasin is movably mounted in the toilet to be able to adopt at least two distinct positions relative to the toilet bowl, including a retracted position adopted to bring the toilet into a configuration of use of the bowl, and a deployed position adopted to bring the toilet into a washbasin configuration, a position in which the washbasin is arranged above the bowl.

Abstract: A supporting structure of optimized volume includes at least two vertical structural elements having a front face and a rear face. Modules including electronic equipment items are fixed onto the front face of the vertical structural elements. Use in particular can be for the integration of avionics modules on aircraft.

Abstract: A cabinet comprising at least one screen allowing display of data necessary for a flight-control of an aircraft connected to at least one avionics module for management of the data. The screen at least partially forms one of the sides of the cabinet and the module or modules are installed inside the cabinet. The cabinet has a base allowing the screen or screens to be placed at a desired height. As a result, a length of cable between screen and avionics modules is reduced to a minimum.

Abstract: To reduce the bulk of an aircraft toilet which includes a toilet bowl and a washbasin, the washbasin is movably mounted in the toilet to be able to adopt at least two distinct positions relative to the toilet bowl, including a retracted position adopted to bring the toilet into a configuration of use of the bowl, and a deployed position adopted to bring the toilet into a washbasin configuration, a position in which the washbasin is arranged above the bowl.

Abstract: A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a decor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the decor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.

Abstract: A nose section of an aircraft comprising a centered flight deck, making it possible to offer a direct forward field of view towards the outside of the aircraft, the forward visibility of the pilot towards the outside taking priority, and an indirect lateral field of view afforded by image displays displaying images representing the lateral environment of the centered pilot and obtained from an image capturing device.

Abstract: A supporting structure of optimized volume includes at least two vertical structural elements having a front face and a rear face. Modules including electronic equipment items are fixed onto the front face of the vertical structural elements. Use in particular can be for the integration of avionics modules on aircraft.

Abstract: Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin.

Abstract: Process for linear transparency friction stir welding of a flange of a stiffener onto at least one panel for an aircraft, wherein a weld bead is made along the flange of the stiffener and wherein the weld bead extends in cross-section from a first lateral edge to an opposite second lateral edge of the stiffener flange. System for the implementation of the above welding process, which includes three welding heads arranged as a triangle, each of which includes a rotating pin as well as a shoulder extending at the base of said rotating pin.

Abstract: A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.

Abstract: In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.

Abstract: This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning.

Abstract: The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical.

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

Abstract: The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

Abstract: In the method of making an aircraft a mandrel is caused to pass through frames carried by a magazine; and as it passes through, the frames are transferred onto the mandrel.

Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.