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 passenger entertainment device operated by a controller associated with a vehicle passenger seat. The passenger seat includes a seat, a backrest and a pocket in a back surface of the backrest facing away from the seat. The entertainment device includes a base, a display attached to a base front surface and a cover pivotably attached to the base pivotable between a first position, in which the cover covers the display, and a second position, in which the cover exposes the display. A first fastener of the entertainment device is configured to interact with a second fastener on the seat to define a fastening system for detachably fastening the cover to the seat backrest when the cover is arranged in its second position and inserted into the seat pocket, while the base is arranged outside of the pocket with the display facing away from the seat backrest.

Abstract: A bolt comprising a threaded shaft having at least one helical thread and at least one longitudinal groove, a nut having a tapped hole configured to be screwed onto the threaded shaft, and at least one diagonal slot which includes a first opening end and a second non-opening end. The diagonal slot is inclined from the first end towards the second end in the same direction as the helical thread of the threaded shaft. An anti-rotation device is configured to rotationally immobilize the nut with respect to the threaded shaft and comprises a ring which surrounds at least the threaded shaft and which has at least one first toe configured to be housed in the longitudinal groove of the threaded shaft and in the diagonal slot of the nut, in operation.

Abstract: An aircraft comprises a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. This arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure, at least one securing member articulated to each of the first and second connecting portions. Furthermore, the first connecting portions of the two fittings are made in one piece in a single wing connector extending over essentially the entire height of the front wing spar.

Abstract: An aircraft having a fixed wing and a wing tip device at the tip thereof is disclosed. The wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A locking mechanism locks the wing tip device in the flight configuration, and includes a plurality of lugs located on each of the fixed wing and wing tip device. Locking pins are inserted through and lock together corresponding lugs when the wing tip device is in the flight configuration. A secondary locking mechanism of a plurality of blocking members prevents the removal of the locking pins from the corresponding lugs, whereby the plurality of blocking members have a common actuator.

Abstract: A stiffener for an aircraft assembly is disclosed. The stiffener provides structural stability to the aircraft assembly. The stiffener has a first stiffener part having a planar web portion and a second stiffener part arranged with the first stiffener part. The second stiffener part includes a corrugated web portion having a corrugation. The present application also relates to an aircraft assembly, a fuselage for an aircraft, an aircraft and a method of forming a stiffener for an aircraft assembly.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatable about a first hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the first hinge axis. A wing having an actuation unit with reduced complexity and weight and that is arranged entirely inside the outer contour of the wing is disclosed in which the actuation unit is arranged at one of the fixed wing and the foldable wing tip portion and is coupled to the other of the fixed wing and the foldable wing tip portion via a linkage. The linkage includes a first link element and a second link element, wherein the first link element is rotatably mounted to the one of the fixed wing and the foldable wing tip portion via a second hinge and is rotatably coupled to the second link element via a third hinge.

Abstract: A wing for an aircraft is disclosed having a fixed wing, and a foldable wing tip portion mounted to the fixed wing via a tip hinge rotatable about a tip hinge axis between an extended position and a folded position. An arresting device is provided that allows to arrest the foldable wing tip portion with respect to the fixed wing in a very precise position and at the same time can be engaged in a simple and quick manner, is achieved in that the wing includes an arresting system including a first hook mounted to the foldable wing tip portion and a second hook mounted to the fixed wing, wherein the first hook and the second hook are configured to be moved relative to one another between an arrested position, where the first and second hooks are engaged and relative movement of the first and second aircraft components is inhibited, and a release position, where the first and second hooks are disengaged and relative movement of the first and second aircraft components is allowed.

Abstract: A barrel nut for a fastener is disclosed. The barrel nut is configured to prevent axial movement of the fastener relative to a structure on which the fastener is installed. The barrel nut comprises a first part and a second part pivotable relative to the first part.

Abstract: A process for producing a sandwich component. A first covering layer is formed on a molding surface of a molding tool; a core is produced by building up a cell structure having a multiplicity of cells in a thickness direction on the first covering layer via an additive production process; and a second covering layer is formed on a deposition surface of the core, the surface being situated on the opposite side from the first covering layer. A core for a sandwich component is furthermore described, as is a sandwich component.

Abstract: A nacelle comprising a fixed structure with a fixed cowl and a duct, a mobile assembly with a chassis forming a frame and a mobile cowl, the chassis being mobile, relative to the fixed structure, in translation between an advanced position and a retracted position to open an opening through the frame between the duct and the outside. The mobile assembly comprises at least one threaded rod parallel to the direction of displacement and fixed to the chassis through the frame. The fixed structure comprises an outer, an inner, and at least one intermediate box fixed to the inner box and to the outer box. For each threaded rod, the fixed structure comprises a motorized ball nut which meshes with the threaded rod, and an actuator which turns the ball nut and is fixed to at least one box from among the outer, the inner, or the intermediate box.

Abstract: A device for controlling a door of a vehicle includes a drive unit that pivots the door between closed and open positions, wherein the closed and open positions define a pivoting range of the door. The device includes a control unit to control the drive unit. The device also includes a sensor unit that monitors the pivoting range. The sensor unit transmits a collision signal when an object is in the pivoting range while the drive unit is pivoting the door. The control unit transmits a switch-off signal to the drive unit if the control unit receives the collision signal.

Abstract: An aircraft structural deformation sensor system comprises a deformation sensor arrangement comprising one or more transceiver(s), each transceiver matched to at least one corresponding transponder and configured to be attached to a support component. The deformation sensing arrangement is configured such that one or more range values between the at least one transceiver and the at least one corresponding transponder is determinable by the transceiver. A deformation controller is configured to process the one or more range values from the transceiver(s) and compute a deformation state of the deformable component relative to the support component.

Abstract: A turbomachine for an aircraft, comprising a thermoacoustic system associated with a fluid circuit that serves to supply the engine of the turbomachine with fluid. The thermoacoustic system comprises an exchanger which is connected to the fluid circuit and in which there flows a fluid that is to be cooled, an acoustic attenuation structure which is distinct from the exchanger and which forms all or part of a wall of the fan duct, and at least one heat-duct tube comprising a portion that is entirely received in the acoustic structure and a portion with an end that is received in the exchanger, and a single curved elbow with a non-zero angle between the two portions.

Abstract: An aircraft having a retractable landing gear assembly configured to support some of the weight of the aircraft via one or more wheels, and another retractable non-wheeled landing gear assembly or device configured to support some of the weight of the aircraft via one or more “low-friction” supports such as an air cushion is disclosed. The aircraft may have a maximum take-off weight between 100 and 150 tonnes. There may be two main landing gears each carrying two wheels, a nose landing gear, and a central non-wheeled landing gear providing the low friction vertical support when the aircraft is moving on the ground/operating surface.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.

Abstract: An assembly with an aircraft fuel tank is disclosed having a captive nut with an internal thread, a secondary structure, and a fastener which secures the secondary structure to the fuel tank. The fastener has a shaft which passes through the secondary structure and has an external thread coupled to the internal thread of the captive nut. The fuel tank has a fuel tank element with a hole, and the captive nut has a sleeve which is located in the hole with an interference fit between an outer surface of the sleeve and an inner surface of the wall of the hole.

Abstract: A device for lacquer transfer is disclosed including a frame, a transfer roller with a circumferential lateral wall, and a nozzle for dispensing lacquer, wherein the nozzle is connected to the frame, wherein an outside contact surface of the lateral wall comprises several depressions, wherein the transfer roller is mounted rotatably about an axis of rotation at the frame, wherein the nozzle is arranged contactless to or in direct contact with the outside contact surface of the lateral wall for dispensing lacquer into respective depressions in the lateral wall while the transfer roller is rotated about the axis of rotation, and wherein the transfer roller is configured to roll with the outside contact surface on a work surface of a work piece for transferring the lacquer from the depressions to the work surface of the work piece.

Abstract: A support member configured to support a first structure within an aperture of a second structure is disclosed. The support member comprises a bracket for attaching the support member to the second structure; and a funnel part. The diameter of the base of the funnel is less than or equal to the diameter of the aperture, and is substantially equal to the diameter of a part of the first structure to be supported by the support member.

Abstract: A gas dehumidification device having two heat exchangers, each including a first and second fluid line. Each second fluid line at least partially surrounds the respective first fluid line. Each heat exchanger thermally couples a fluid in the respective heat exchanger second fluid line with a first coolant on an outside surface of the respective heat exchanger second fluid line. The gas dehumidification device further comprises a two-position valve. In a first position, a fluid comprising a higher temperature than the first and/or second coolant is conducted into the first heat exchanger first fluid line and in the second position, the fluid is conducted into the second heat exchanger first fluid line. A controller is configured to place the valve selectively into the first or second position.