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: 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: The subject of the invention is an aircraft fuselage frame element (101, 102, 103) characterized in that it comprises a portion of cross member (1a, 101a, 102a) and a section of frame (1b, 101b, 102b) brought together into a single part; an assembly of aircraft fuselage frame and cross members that comprises a frame element of the invention, for which the frame element (1) connects an upper frame (5), a floor cross member (3) and a lower frame (4), and comprises a segment (1c) that replaces a floor strut; an assembly of aircraft fuselage and cross members for which the portion of cross member of the frame element (101, 102) forms a cargo cross member of the aircraft or forms a cross member for mounting the luggage bins.

Abstract: The method of fabricating an aircraft comprises the following steps: fastening two lateral floor portions, each firstly to a fuselage element and secondly to supports that are connected to the fuselage element; and then bringing a middle floor portion between the lateral portions and connecting it to the lateral portions.

Abstract: An intermediate support structure (10) for the cockpit of an aircraft comprises a raised floor (11) and at least one structural element (12,13) extending as an arch above the raised floor, said arched structure (12, 13) being adapted to hold in position at least one item of equipment (51) in the upper part of the cockpit, and comprises means for mounting said intermediate structure (10) onto a fuselage primary structure (100), defining a portion of the cockpit of an aircraft.

Abstract: A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures (62) that are arranged on both sides of the opening, at the level of which (5) there is provided at least one stop (56) that provides the uptake of radial forces exerted by the door, characterized in that each vertical substructure (62) includes at least three walls made of composite material that are connected to one another to form a closed and hollow profile in such a way as to obtain a box structure.

Abstract: The invention relates to a fuselage element comprising a fuselage segment (1a) comprising a skin (3a), and junction means (6) for connecting the skin of said segment (1a) to an adjacent segment (1b). The segment (1a) extends along the longitudinal axis (X) of the fuselage, and the skin (3) includes at least one first section (10) at least one end of said segment (1a). The fuselage segment (1a) comprises at least one longitudinal stiffening element (5a) for the fuselage. The junction means (60) are arranged so as to contact an outer surface (30) of said first section (10) of the skin (3a), and the stiffening element (5a) partially extends at the junction means (6) along the longitudinal axis (X).

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: An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support.

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 floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember.

Abstract: The method of fabricating an aircraft comprises the following steps: fastening two lateral floor portions, each firstly to a fuselage element and secondly to supports that are connected to the fuselage element; and then bringing a middle floor portion between the lateral portions and connecting it to the lateral portions.

Abstract: The present invention includes a card memory device (20) comprising a microprocessor (2), a plurality of memory units (5-12) for storage of digital data, the memory units (5-12) being embedded in the card memory device (20). A selecting device (3, 4) is provided for selecting one of the memory units (5-12) and for routing address information and data to the selected memory unit (5-12), both the microprocessor (2) and the selecting device (3, 4) being embedded in the card memory device (20). The card memory device integrates components into a thin flexible memory card with surface contacts (1) so that the components can cooperate as a compact unit providing environmental sealing and secure access to several Mbytes of digital data. A specially designed set (1) of contacts (21-25) are also described which reduce the risk of electrostatic discharge. The card memory device (20) may be used for secure control of a personal computer.