Abstract: A seal plate (201) for maintaining a continuous aerodynamic surface between a fixed part (302) of an aerostructure such as an aerofoil (103) and a movable surface such as a spoiler (304) is provided. The seal plate (201) includes a resilient material such as fiberglass and has an aerodynamic surface (203). It is configured to be mounted to the fixed part (302) of the aerofoil along one edge (205) and to slidably seal with the control surface (304) at a second edge (207). The seal plate (201) is stepped and has a rigid lever (217) to engage behind the control surface (304) to bend the seal plate precisely according to movement of the control surface (304) and maintain the continuous aerodynamic surface.

Abstract: A seal includes a barrel extending between a base and a top, in which the barrel has a cylindrical cavity passing through it between its base and its top, and a skirt indissociable from the barrel and extending around said barrel, in which the skirt adopts the shape of a dome of which the exterior edges extend out beyond the base starting from the top. The seal is able to divert the fluid and keep the space under the skirt fluid tight.

Abstract: A turbomachine for an aircraft comprising a thermo-acoustic system associated with a fluid circuit allowing the turbomachine engine to be supplied with fluid, the thermo-acoustic system comprising an exchanger connected to the fluid circuit and through which the fluid that is to be cooled passes, an acoustic noise-attenuation structure forming, in full or in part, a wall of the duct of a fan duct, the structure being situated some distance from the exchanger, and a pulsating heat pipe comprising a tube extending between the exchanger and the acoustic noise-attenuation structure, the tube having a serpentine form with a plurality of elbows bent over at 180° housed alternately in the exchanger and the structure.

Abstract: A door arrangement for an aircraft segment, which door arrangement comprises a passenger door, a fuselage portion accommodating the passenger door, and a girt bar for arming and disarming an emergency slide. The passenger door is movable relative to the fuselage portion between a raised position and a lowered position. The girt bar is connectable by means of a connecting arrangement to the passenger door and/or to the fuselage portion. The connecting arrangement comprises a mechanism which is configured to, during arming of the emergency slide, actuate a locking mechanism of an engagement device fastened to the fuselage portion, in such a way that the girt bar is fixed in a decouplable manner to the engagement device.

Abstract: A camera module for surveillance of a passenger cabin of an aircraft, including a covering device for securing in a longitudinal cutout of a service channel including a carrier part having a circular securing cutout and including a mounting structure at least partly surrounding the securing cutout. A camera device includes a camera housing having a mounting portion with a spherically curved outer surface, and includes a camera unit having a lens accommodated in a front cutout of the camera housing, an optical sensor for generating image data, the optical sensor being in an interior of the camera housing, and a data interface for transferring the image data, wherein the camera housing is mounted by the mounting portion in the mounting structure to be rotatable or pivotable about at least two axes, and a locking device for locking the camera housing relative to the mounting structure.

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 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 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: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door that is configured to assume a raised state and a lowered state, and a girt bar for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming when the passenger door is in the lowered state. Also an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement means being fixed to the fuselage portion.

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: 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 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: 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 direct current electrical network includes nodes linked by branches and protection elements mounted on the branches, each protection element includes a central processing unit, a current sensor, a current limiter device and a circuit breaking device, wherein: the current sensor is configured to determine the direction of the current in the branch relative to the node with which said protection element is associated; the central processing unit is configured to select, as a function of the direction of the current, a selected threshold value as one of a first value or a second threshold value greater than the first threshold value in absolute value, and to compare the value of the intensity of the current to the selected threshold value; and the current limiter device is bidirectional and is configured to limit the current passing through the branch to the selected threshold value.

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: An aircraft wing assembly including a main wing portion, a high-lift device with a flow surface including an upper skin portion and a lower skin portion, wherein the flow surface of the high-lift device comprises a first flow surface portion, a second flow surface portion and a third flow surface portion, wherein the first flow surface portion is micro-perforated for an air inflow, wherein the first flow surface portion extends on the upper skin from the leading edge in chordwise direction for 2% or less of the local chord and extends on the lower skin from the leading edge in chordwise direction for 2% or less of the local chord, and wherein the second flow surface portion is not micro-perforated and extends over the rest of the upper skin portion, and wherein the third flow surface portion is not micro-perforated and extends over the rest of the lower skin portion.

Abstract: A wing for an aircraft including a main wing, slat, and connection assembly movable connecting the slat to the main wing and including an elongate slat track. A front end of the slat track is mounted to the slat. A rear end and an intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The wing has redundant main load paths. The guide rail includes a guide rail primary structure engaging with the first roller unit and an additional reinforcement structure additionally reinforcing the guide rail primary structure in a lateral direction. The guide rail primary structure forms a first main load path. The reinforcement structure forms a redundant second main load path.

Abstract: A system for providing temperature-controlled water in an aircraft has a tank, a water temperature-controlling unit, a control unit, and a power supply terminal. The water temperature-controlling unit can be coupled to the tank to heat or to cool water situated therein. The control unit is connected to the water temperature-controlling unit to activate the water temperature-controlling unit for controlling the temperature of water in the tank to a predefined temperature. The power supply terminal can be connected to an on-board voltage source for the water temperature-controlling unit and the control unit to be supplied with electrical voltage. The system is in the form of a coherent and self-contained unit which can be integrated into a standard parking place of a galley of the aircraft. The tank is mounted so as to be exchangeable or the system has a water discharge connection which is coupled to the tank.

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.