Abstract: A tooling assembly for integrating a central part of the fuselage of an aircraft. The tooling assembly comprises a tooling train which comprises a succession of movable carriages arranged behind one another and which are able to carry one or more items of aircraft equipment to be integrated into the central part of the aircraft. Such a tooling train, which extends over at least a length of the central part of the fuselage, makes it possible to integrate, at the same time, items of aircraft equipment produced in the form of elongate modules, thus reducing the time for integrating the items of aircraft equipment.

Abstract: A sealed bottom in the frame of a cockpit with centered pilot is disclosed for increasing the bulk inside the radome and making it possible to improve the optimization of the volumes. The sealed bottom includes a semi-cylindrical central part having four edges that are parallel in pairs, two curved edges, and two straight edges and a planar peripheral part extending at least partially around the central part. The peripheral part (22) is located in the plane of the straight edges of the central part and linked thereto. This configuration will allow to free up space to increase the number of passengers or reduce the size of the aircraft.

Abstract: An electrical and electronic bay for an aircraft includes a central area forming a free space, a peripheral side area provided for the arrangement of supporting structures and being placed around said central area, and a lower area placed below the central and peripheral side areas and in which the access opening is placed in said central area. Such an electrical and electronic bay is used in particular to optimize the areas dedicated to the incorporation of electronic equipment in aircraft.

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 pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

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: An aircraft comprising an air conditioning device positioned at least in part in the nosecone of the aircraft. This novel integration architecture makes it possible to reduce the volume of the belly pan of the aircraft and improve the aerodynamic performance thereof.

Abstract: A method for installing a wiring harness in an aircraft. The method comprises using cables having first ends secured to the harness and winding means onto each of which is wound one of said cables so as to lift up said harness by exerting a tensile force. The first ends of the cables are distributed along at least a section of the harness so as to distribute the tensile forces over the section.

Abstract: To facilitate the thermophonic insulation of an aircraft section, a method comprises engaging first respective parts of flexible structures, respectively connected to two flat mattresses, with a support device, by leaving free respective second parts of the flexible structures arranged at a distance from the first parts, then curving the two mattresses, by virtue of the mutual bringing together of the second parts, then inserting the support device into the aircraft section, and detaching each mattress from the support device and fixing each mattress to an aircraft structure delimiting the aircraft section.

Abstract: A rear pressure bulkhead for aircraft with a semi-recessed integrated engine or, for aircraft of which the cross section of the tail cone in the region of the pressure bulkhead is of the ovoid type with inwardly curving side walls is provided. The cross section of the tail cone of such aircraft is atypical and subjected to loadings that make the application of a known shape of pressure bulkhead unsuitable. The integral membrane of which the geometric shape includes the combination of two substantially spherical half-caps and of a portion of a cylinder of substantially circular cross section joining the two half-caps, the free edges of the cylinder portion being slightly inwardly curved. Such a geometry allows the pressure bulkhead to withstand the loadings present in this zone.

Abstract: A tool for transporting and installing an insulation blanket in a single piece on a component, for example of an aircraft. The component can have a double-curvature surface like a sealed back which makes the installation difficult given the planar nature of the blanket. The transporting and installing tool operates like an umbrella without fabric at which the ribs are provided with removable attachment devices allowing removable fixing to the insulation blanket. The tool is simple and easy to handle for rapid installation that can be carried out by a single operator.

Abstract: An aircraft is disclosed having a lifting body housing a passenger cabin including a forward portion bounded laterally by at least one portion of a leading edge of the lifting body. The passenger cabin includes at least one lateral luggage storage device housed in the concavity formed by the leading edge portion and includes an opening towards the interior of the passenger cabin.

Abstract: A cabin space dedicated to passengers and, beneath said cabin space, an under-cabin space which extends along the longitudinal axis of said aircraft. The under-cabin space comprises, distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are able to carry out functions necessary for the operation of the aircraft. The two lines of sets of systems are disposed respectively in two lateral zones of the under-cabin space which are spaced apart transversely from one another and enclose a free central zone which extends along the longitudinal axis of the aircraft. This arrangement thus eliminates any technical zone from the under-cabin space, thereby facilitating the internal layout and maintenance.

Abstract: A cabinet designed to accommodate at least one item of electronic equipment and a system for interconnecting such a cabinet with the external networks for blowing and extracting air. The system includes at least one of a blowing inlet and an extracting outlet including a plurality of orifices and at least one hollow structural upright as a part of the blowing circuit or of the extracting circuit.

Abstract: An air intake system for an aircraft having a ventral fairing and comprising a scoop having a ventral wall with a first coupling and an opening. The scoop is movable between a flush position in which the ventral wall is flush with the ventral fairing and a catchment position in which the opening is beneath the ventral fairing, and the ventral wall is pierced by a through hole designed to be connected to a flexible pipe of an air conditioning unit. A hatch is movably mounted on the scoop between an open position not blocking the opening and a closed position blocking the opening, the open position can be attained only when the scoop is in the catchment position. A return element forces the hatch into the closed position, and a plug has a second coupling which cooperates with the first coupling to removably secure the plug.

Abstract: A front landing gear comprising an undercarriage and a landing gear bay, the undercarriage including a single wheel, a landing gear strut and a stay rod, the undercarriage being movable between a retracted position in which it is stowed inside the landing gear bay and a deployed position in which it extends mainly outside the landing gear bay and the aircraft, the wheel then extending in a median longitudinal plane of the aircraft. The landing gear strut is laterally offset, extending in a plane strictly parallel to the plane of the wheel. The landing gear strut is articulated about a longitudinal axis pivot connection such that, when the undercarriage is moved between its retracted and deployed positions, the landing gear strut moves in a transverse plane. The front landing gear is particularly suitable for an aircraft of flying wing type.

Abstract: An aircraft comprising a fuselage which has a central part with a cross section of constant geometry which comprises a floor. The floor comprises two lateral portions which are fixed respectively to two opposite lateral edges of the fuselage and which enclose a central portion to which they are fixed. One of the lateral floor portions is fixed to the central portion so as to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage. The cross section thus deforms homogeneously when the fuselage is pressurized and the floor is not involved in maintaining the shape of the fuselage.

Abstract: A device for positioning a first piece relative to a second piece. The first piece comprises a free end with a first bore and the second piece comprises an engagement part with a second bore intended to come into correspondence with the first bore. The first and second bore are drilled to the definitive diameter thereof prior to the relative positioning thereof. The device comprises one or more positioning elements, which are able to position the first bore relative to the second bore along at least one of three geometric axes.

Abstract: In order to facilitate the thermoacoustic insulation of an aircraft portion, a method for manufacturing a thermoacoustic insulation module for an aircraft comprises a step of providing a mat configured to provide thermoacoustic insulation of an aircraft portion, followed by a step of attaching a bendable structure to the mat, followed by a step of bending the bendable structure, along a bending axis parallel to a longitudinal direction of the mat, such that the bendable structure forms a load-bearing structure supporting the mat in a curved shape.

Abstract: In order to facilitate the thermoacoustic insulation of an aircraft portion, a thermoacoustic insulation module for an aircraft comprises a mat and a load-bearing structure detachably attached to the mat and supporting the mat in a curved shape, with an axis of curvature parallel to a longitudinal direction of the mat. A thermoacoustic insulation method for insulating an aircraft portion comprises a step of inserting the thermoacoustic insulation module into the aircraft portion, followed by a step of detaching the mat from the load-bearing structure, followed by a step of attaching the mat to an aircraft structure delimiting the aircraft portion, followed by a step of removing the load-bearing structure from the aircraft portion.