Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

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: To reduce the size of an aircraft engine, an assembly is disclosed including a nacelle section, a gas exhaust cone positioned radially towards the inside in relation to the nacelle section and forming therewith an annular gas exhaust channel, and a reverse thrust system including moveable gas diversion elements for the gas flowing in the annular channel, at least one actuator and a transmission device linking the at least one actuator to the moveable gas diversion elements. Furthermore, the actuator is located inside the gas exhaust cone.

Abstract: An engine assembly for an aircraft, comprising an engine mounting pylon comprising a primary structure forming a box closed by a front closing rib, a front engine mount comprising at least two connecting link rods that are disposed laterally on either side of the box and each comprise a first end mounted on a first fitting of the casing. The rib forms a part of the front mount, comprising at least one transverse fitting made in one piece so as to close a front end of the box and to have lugs protruding laterally on each side of the box, each lug being provided with a first orifice for mounting a second end of one of the link rods.

Abstract: A primary structure of a support pylon for an aircraft engine assembly. The primary structure includes a pyramidal part, the pyramidal part including a single rib, the single rib forming the base of the pyramidal part, and straight, upright members converging towards an apex point of the pyramidal part, a fastening interface being provided at the apex of the pyramidal part. A pyramidal part based on upright members converging towards the apex of the pyramid enables loads in the upright members to be distributed, via a simple structure. This structure furthermore enables the integration of components within the pyramidal part.

Abstract: Fixation of an aircraft engine attachment pylon to the wing of an aircraft by means of an attachment device attached to a wing structure by means of first attachment through-members. The attachment device and the attachment pylon have respective junction surfaces clamped to each other by means of second attachment through-members. The junction surfaces extend along a plane forming an angle of less than 45 degrees with a vertical direction of the aircraft. A method for assembling the attachment pylon to the wing includes the positioning of the attachment pylon facing the attachment device, and then the clamping of the respective junction surfaces of the attachment device and of the attachment pylon to each other via the second attachment through-members.

Abstract: An aircraft comprising at least one power plant linked to an airfoil by a power plant support structure comprising a primary structure housed in an aerodynamic fairing. The power plant is formed overhanging behind the airfoil, mostly or wholly above the upper surface of the airfoil. The aircraft comprises a main landing gear comprising at least one landing gear element linked to the airfoil of the aircraft by a support structure. The primary structure and the support structure of the landing gear element are formed by a common structure. The use of such a common structure allows a general optimization of the architecture of the aircraft by virtue of the synergies between the positioning of the power plant, the primary structure of its strut, and the support structure of the main landing gear.

Abstract: A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.

Abstract: In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.

Abstract: The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings.

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 link for an aircraft comprises at least two portions respectively made of metal and of composite material together forming a common section of a middle segment of the link in a plane perpendicular to a longitudinal direction of the link.

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: To optimize the structure of an aircraft tail section, an aircraft rear section comprises a fuselage section, a tail section, and a vertical stabilizer comprising a box-section structure which comprises a box-section upper part extending on the outside of the tail section, and a box-section lower part housed inside the tail section, such that the tail section is wholly supported by the box-section structure.

Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing bear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

Abstract: In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.