Abstract: A fuel cell system for an aircraft includes at least one fuel cell having a first inlet for providing a fuel, a second inlet for providing an oxidant, an outlet for removing exhaust air and a voltage outlet, an electrically operable hydraulic pump, which is integratable into a hydraulics network of the aircraft and connectable to the voltage outlet of the at least one fuel cell and a controllable hydraulic energy converter with changeable operating behaviour. The hydraulic energy converter is adapted for generating such a power demand in the hydraulics network, that the at least one fuel cell provides a predetermined volume flow of oxygen depleted air at the outlet through delivering electrical power to the hydraulic pump.

Abstract: A wall module for a cabin of a vehicle for separation of different cabin regions comprises a lower wall section having a fastener for fastening the wall module to a structurally fixed component fixed to the floor in the cabin, a surface-like rigid upper wall section converging with the lower wall section having a second fastener in a region of the wall module facing away from the lower wall section for fastening the wall module to a structurally fixed component fixed to the ceiling in the cabin. The upper wall section at least in a region comprises an arched curvature around a horizontal axis for adapting to the shape of a backrest of a seat. The wall module comprises at least one element stiffer than the upper wall section, which extends from a region adjacent the floor to a region adjacent the ceiling of the wall module.

Abstract: An aircraft structure component for laminar flow, the aircraft structure component having an outer skin with an aerodynamic surface, wherein the aerodynamic surface has a leading edge portion and a downstream portion adjacently downstream from the leading edge portion, and wherein the downstream portion of the aerodynamic surface includes a paint layer that is not present in the leading edge portion, so that an edge line is formed between the leading edge portion and the downstream portion by the beginning paint layer. An object, to provide an aircraft structure component that allows for a reduced aerodynamic drag, is achieved in that the edge line has a ramp-shaped cross section, wherein the thickness of the paint layer increases from a starting point over a predetermined ramp length to a saturation point where the full thickness of the paint layer is reached.

Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.

Abstract: A main aircraft wing slat assembly comprising a slat and two elongate slat tracks. A drive arrangement drivingly engages the two slat tracks and effects parallel synchronous movement of the slat tracks between retracted and extended positions. The connection between the slat and one or both slat tracks is realized by an interconnection portion extending between at least part of the slat and at least part of the respective slat track. The interconnection portion is elastically deformable and constructed such that a first stiffness against deformation about a first axis, is at least ten times a second stiffness against deformation about a second axis, which extends perpendicularly to the first axis and between the first and second portions of the interconnection portion, and at least ten times a third stiffness against deformation about a third axis, which extends perpendicularly to the first and second axes.

Abstract: Air conditioning system for a cabin 6 of an aircraft, the air conditioning system 1 including a pressurized air source 2, a ram air duct 3, an air amplifier 4 and a heat exchanger 5. The air amplifier 4 includes an inlet 41 for work air, a slot 42 suitable for letting the work air exit the air amplifier, and a main fluid zone 43. The inlet 41 is in fluid communication with the pressurized air source 2 and the slot 42 is arranged in fluid communication with the ram air duct 3, in such a way that the work air exiting from the slot 42 produces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct 3. The air amplifier 4 is arranged so that the ambient air is forced by the suction effect to pass from the inlet 51 to the outlet 52 of the cold side of the heat exchanger 5.

Abstract: A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Abstract: A side console for an aircraft cockpit includes a structure for mounting of an item of aircraft equipment and a complementary structure. The mounting structure and the complementary structure are formed of single-piece components articulated about an axis of articulation between a storage position in which the single-piece components are more or less folded against one another, and a position of installation in which the single-piece components extend respectively in substantially mutually perpendicular planes.

Abstract: This relates to a method of manufacturing a metallic component by additive layer manufacturing. The method comprises the step of providing a layer of granular metallic material. The layer of the granular metallic material is melted by a laser beam or electron beam which applies a defined scanning strategy, which is defined in such a way that a first region of the layer is melted before a second region of the layer such that during the subsequent solidification, residual stresses emerge in the first and the second region. These residual stresses act as integrated crack stoppers of the metallic component.

Abstract: A system for detecting radome damage. The system comprises a sensor unit and a processing unit. The sensor unit is configured to continuously register external impacts on a radome. The processing unit is electrically connected to the sensor unit. The processing unit is configured to compare the external impacts registered by the sensor unit with reference data. The processing unit is further formed to determine, based on the comparison, whether damage to the radome has occurred due to one or more events associated with the external impacts. Furthermore, a radome comprising the system, a flying object and a corresponding method are provided.

Abstract: A method for manufacturing a structural assembly comprising at least two assembly components interconnected by means of a thermoplastic plastics material, and useful in the field of aviation or space travel. First, a first assembly component and a second assembly component are provided and arranged so as to form an arrangement. Second, the arrangement is subjected to creep forming at a temperature which is selected in such a way that the thermoplastic plastics material melts at least in part during the creep forming so as to connect the first assembly component and the second assembly component. The invention further relates to structural assemblies, in particular for an aircraft or spacecraft, and to an aircraft or spacecraft comprising a structural assembly of this type.

Abstract: A system for moving loads in an aircraft, comprising a cargo hold floor and at least one roller track comprising a plurality of rollers, defining a plane of movement for the load, arranged one behind the other in the hold floor. At least one guide track is provided in the floor extending parallel to the roller track. At least one transfer vehicle is detachably received in the guide track, movable along the guide track. At least one locking device is configured, in a locking position, to block movements of a load relative to the roller track parallel to the movement plane and perpendicular to the movement plane and, in a release position, to allow relative movements. The locking device is configured to be actuated by a transfer vehicle in the guide track to shift the locking device out of the release position into the locking position, or vice versa.

Abstract: A tyre monitoring device configured to be mounted on a wheel is described. The device includes a pressure sensor for sensing an inflation pressure of a tyre on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tyre pressure; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tyre pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Abstract: A turbofan with a fan casing and a nacelle which comprises a fixed structure, a movable assembly with a movable cowl and a slide, which is translationally movable between an advanced position and a retreated position in which the movable cowl is moved away from the fan casing in order to define a window open between a duct and the outside of the nacelle, a plurality of blades, each being mounted rotatably on the slide, where each blade is movable between a retracted position in which the blade is outside of the duct and a deployed position in which the blade is across the duct, a set of actuators for moving the slide and an operating system configured to move each blade from the retracted position to the deployed position, and vice versa.

Abstract: A flow body for a vehicle includes at least one planar skin section with an outer side, an inner side and at least one opening that penetrates the skin section, as well as at least one active flow control device that is designed for moving an air volume. The at least one active flow control device includes an air discharge section that is fluidically connected to the at least one opening, wherein the air discharge section and the at least one planar skin section are manufactured by a layer manufacturing process in the form an integral component that is free of joints, and wherein the air discharge section at least partially supports the skin section in a load-bearing fashion.

Abstract: To reduce complexity, solve tolerance problems and increase reliability and customer satisfaction, a door switch arrangement for a lavatory of an aircraft is provided, wherein, to generate signals which indicate a current status of the lavatory door, the door switch arrangement uses a sensor device with contactlessly operating reed sensors.

Abstract: For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: A monument has a connection device, a fluid source and a compartment for the installation of a modular unit. The connection device is intended for connecting the fluid source to a modular unit installed in the compartment. The connection device includes two line sections. It is connected to the fluid source via one line section and can be connected to a modular unit via the other line section. The connection device is arranged so as to be displaced in the compartment on a predefined track between a connection position and an operating position. In the connection position the connection device is further from the rear end of the compartment than in the operating position. The connection device can be connected, in the connection position, via the second line section to a modular unit arranged outside the compartment. Also described is a system including a monument and a modular unit.

Abstract: A fitting mount for a vehicle washroom, which comprises an adapter element and a basic mount. The adapter element has a coupling device, at least one opening, which is configured to receive a fitting component, and a circumferential guide surface. The basic mount has a first attachment device for attaching the basic mount, a second attachment device, which is configured to be coupled to the coupling device of the adapter element and to be attached detachably to this, and an internal guide surface, which is configured to at least partially enclose the circumferential guide surface of the adapter element.