Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.

Abstract: A method for transmitting data, a receiving method, related devices, and an aircraft equipped with the devices. The method includes determining an authentication word of the data; processing the data to obtain processed data; and transmitting the processed data on a transmission channel.

Abstract: The invention relates to a mixing system for inerting a gas volume. A first exhaust gas that is provided by a fuel cell, and a second exhaust gas that is provided by a hydrogen reformer, can be mixed to form an inert gas mixture. The mixture can be fed into the gas volume for inerting.

Abstract: A seat rail for attaching seats in aircraft is provided. The seat rail includes a profile element for attaching the seats, and a support element for attaching the seat rail in an aircraft. At least the support element is manufactured from aluminum or an aluminum alloy. The surface of the aluminum or the aluminum alloy includes, an oxide layer, and the oxide layer has been manufactured by means of hard anodic oxidation.

Abstract: An energy supply system for an aircraft comprises at least one fuel cell and at least one energy storage device, wherein the fuel cell, of which there is at least one, is coupled to the energy storage device, of which there is at least one, such that the energy storage device can be charged by means of the fuel cell.

Abstract: The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface

Abstract: The invention concerns a pressurized flooring for aircraft, provided with beams (1) including an upper sole (2), a vertical web plate (3), and a lower sole (4), the lower sole being provided with two oblique feet (7, 8) arranged on both sides of the vertical web plate and presenting a support surface (14, 15) provided for supporting pressurized curved membranes (9), characterized in that the lower sole includes a linking element (10) connecting the two oblique feet, so that said lower sole presents an enclosed section. Such a structure can be advantageously realized in composite material.

Abstract: A fire protection system for reducing the danger of fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the room to be protected.

Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.

Abstract: The invention relates to a flight control system for an aircraft comprising control surfaces and actuators associated with the control surfaces to control flight functions, including roll, yaw, pitching, and aerodynamic braking of the aircraft. The actuators associated with the control surfaces that control at least one of the flight control functions are electromechanical actuators. A part of the control surfaces associated with the electromechanical actuators is divided, where each of the divided control surfaces is comprised of at least two independent surfaces.

Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.

Abstract: A machining method for machining a superficial portion of a laminate using machine tool having a depth limiter which restricts a maximum depth of the machine tool. A guide frame having an inner guide contour restricts a maximum dimension of the superficial portion, and is secured over the superficial portion. The superficial portion is machined while the machine tool is guided by the guide contour. From another point of view, a machining apparatus for machining a superficial portion of a material is provided. The machining apparatus comprises a guide frame, an inner guide contour for guiding a machine tool, an attachment member for securing the guide frame to an attachment member, adjacent to the superficial portion, of the material.

Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.

Abstract: A method of forming a rib-spar joint during assembly of an aircraft wing, the method comprising: providing a spar with a fixedly attached rib post, the rib post having a first coordination feature; providing a rib having a web with a first tooling feature; providing a tooling component having a second tooling feature for cooperating with the first tooling feature, a second coordination feature for cooperating with the first coordination feature, and a plurality of drill bushings; fixedly attaching the tooling component to the rib web by aligning the first and second tooling features; aligning the rib with the spar by aligning the first and second coordination features; drilling fastener holes in the rib and the rib post off the drill bushings of the tooling component; removing the tooling component from the rib web; and fastening the rib to the rib post using the fastener holes to form a rib-spar joint. The method may be applied to form front and/or rear rib-spar joints.

Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

Abstract: A method for producing a curved profile from a rectilinear preform of preimpregnated fiber webs, including stacking webs on the deformable mandrel and winding the deformable mandrel and the stacked webs on a bending tool along an axis of rotation (X), the profile including a stack of N webs, at least one first part of the profile being positioned in a plane perpendicular to the axis of rotation (X) and at least one second part parallel to the axis (X) whereof a face can be in contact with the bending tool. The method includes stacking the N fiber webs on the deformable mandrel, generating a heat gradient between the face and the rest of the preform that is hotter than the face, bending, in a single phase, the N webs inserted between the deformable mandrel and the bending tool, and polymerizing the N bent webs.

Abstract: A bolted joint for connecting a cover of an opening in a primary structure of a lifting surface of an aircraft to the primary structure. The bolted joint includes two first bolted joints on either side of a symmetry axis of the cover arranged without any lateral clearance, two second bolted joints on either side of the symmetry axis on the side of the cover opposite to that of the two first bolted joints, arranged without any lateral clearance in the holes of the primary structure and with a linear lateral clearance in the holes of the cover; a plurality of third bolted joints along the border of the cover arranged without any lateral clearance in the holes of the primary structure and with a radial clearance in the holes of the cover.

Abstract: A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.

Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: A locking device for an aircraft door in a fuselage section of an aircraft includes at least one fuselage fitting disposed in a region of a sill of the fuselage section and at least one door fitting disposed in a region of a lower edge of the aircraft door and corresponding in number to the at least one fuselage fitting. The at least one fuselage fitting and the at least one door fitting are each configured to transfer at least one of a circumferential load and a radial load.