Abstract: A network access control method involves requesting access to a network via a wireless communication adapter for a personal electronic device. Then, an acoustic audio code output by an audio signaling device connected to the wireless communication adapter by wire is acoustically captured by the personal electronic device. A digital representation of the captured acoustic audio code is submitted from the personal electronic device to the wireless communication adapter via wireless communication. Subsequently, the wireless communication adapter authenticates the personal electronic device on the basis of the submitted digital representation of the captured acoustic audio code.

Abstract: A mobile manufacturing module comprising a platform configured to receive and support one or more interchangeable manufacturing elements and engageable with a removable positioning device that when engaged is configured to enable movement of the platform relative to a work piece, and one or more supports connected to the platform that are configured to contact a floor in order to support the platform when the removable positioning device is disengaged.

Abstract: An aircraft air conditioning system includes an ambient air line configured to have ambient air flow therethrough and being connected to a mixer of the air conditioning system to feed ambient air to the mixer, and a recirculation air line configured to have recirculation air flow therethrough and being connected to the mixer to feed to the mixer recirculation air discharged from an aircraft area to be air conditioned. A refrigerating machine of the air conditioning system includes a refrigerant circuit configured to have a refrigerant flow therethrough and being thermally coupled to the ambient air line and to the recirculation air line to transmit heat from the ambient air flowing through the ambient air line and from the recirculation air flowing through the recirculation air line to the refrigerant circulating in the refrigerant circuit, before the ambient air and the recirculation air are fed into the mixer.

Abstract: A connection system for electrically connecting a fixture in a vehicle has at least one cable, and a housing with a cable inlet and a cable outlet, and with a receiving space which is formed in the housing and extends helically along a housing axis with a receiving space cross section from the cable inlet towards the cable outlet. The cable has a cable cross section and runs completely through the receiving space from the cable inlet towards the cable outlet, with cable coils being formed. A radial extent of the cable cross section is smaller than a radial extent of the receiving space cross section. Therefore, different lengths of the at least one cable can be accommodated in the receiving space with different coil diameters being formed.

Abstract: A method for producing a component with a fibre-reinforced foam core has the steps of supplying a foam core having a first main surface and an opposite, second main surface, positioning at least one needle at the first main surface of the foam core, piercing the foam core with the needle, with the result that a needle tip penetrates through the first main surface into the foam core and then through the second main surface, hooking a reinforcing fibre into the needle tip, pulling the needle back, with the result that the reinforcing fibre is pulled through the foam core, and coating the reinforcing fibre with a resin while the needle is being pulled back.

Abstract: A skin panel with an energy-storing layer for an aircraft or spacecraft comprises structural layers for providing structural stability to the skin panel, at least one of the structural layers forming an exterior supporting layer of the skin panel and at least one of the structural layers forming an interior supporting layer of the skin panel. Primary functional layers are embedded between the exterior supporting layer and the interior supporting layer for providing functional capabilities to the skin panel. The structural layers and the primary functional layers are formed together as a composite laminate and the functional layers comprise an energy-storing layer configured as a structural electro-chemical battery. The present disclosure further pertains to a method for manufacturing such an energy-storing layer for a skin panel of an aircraft or spacecraft.

Abstract: A method for active flow control of a fluid flow that flows along a flow surface includes generating a first local velocity field in the fluid flow by introducing a first vortex structure into the fluid flow by a first flow control actuator coupled to a first actuation site of the flow surface, and introducing a second vortex structure into the first local velocity field by a second flow control actuator coupled to a second actuation site of the flow surface located downstream of the first actuation site, when a head vortex of the first vortex structure has propagated with the fluid flow downstream the second actuation site.

Abstract: A shrouded valve assembly including a valve, valve pipe and valve channel. A valve member can regulate flow of fluid through the valve channel. A valve shroud provides a valve shroud chamber and includes first and second valve shroud members fixed via valve shroud member flanges. An actuator shaft passes through the valve shroud and the valve pipe to the valve member and can move to operate the valve member to regulate flow of fluid through the valve channel. The actuator shaft extends in an actuator shaft direction passing through the valve shroud and the valve pipe. The valve shroud flanges meet at a valve shroud interface inclined at an acute angle to the actuator shaft direction. The actuator shaft passes through the first valve shroud member and not the second valve shroud member, enabling the valve to be inspected by disassembling this interface without disassembling the valve shroud members.

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: An aircraft comprises a fuselage, a set of electrical equipment items distributed in the fuselage, and a hybrid electrical power distribution and data communication network. The latter comprises a set of buses comprising at least one electrical power distribution bus extending, at least partly, in a longitudinal direction of the fuselage. A set of data links is associated with each bus of the set of buses. The bus and the associated set of data links each comprise connection points at different locations distributed along their length, forming pairs of connection points. Each of the electrical equipment items of the set of electrical equipment items is linked to a pair of connection points via a local electrical power supply link and/or via a local data link.

Abstract: A reinforcing arrangement for an opening in an aircraft fuselage structure has a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and a one-piece reinforcing structure having a thickening section and at least one projecting profile. The first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface having a thickness corresponding to a thickness of the fuselage skin surrounding the opening edge surface. The thickening section has a bearing surface matched to the opening edge surface and has a receiving section facing away from the bearing surface and surrounding a second opening. The bearing surface is in surface contact with the opening edge surface, and the reinforcing structure is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other.

Abstract: A trolley compartment for an on-board kitchen intended for installation in a transport vehicle comprises a frontal access aperture as well as a rear wall that lies opposite the access aperture. A worktop forms an upper boundary of the trolley compartment. A first cooling fluid duct, which is connectable to an interior space of the trolley compartment via at least one first cooling fluid aperture, is integrated into or arranged adjacent to the worktop. At least one first removable cooling fluid aperture cover is selectively mountable in the first cooling fluid duct over the first cooling fluid aperture to separate the first cooling fluid duct from the interior space of the trolley compartment, or demountable from the first cooling fluid duct to connect the first cooling fluid duct to the interior space of the trolley compartment via the first cooling fluid aperture.

Abstract: A system includes a vehicle monument, a hose with a fluid line, and an adapter with a triggering unit and a housing, which has a fluid connection. The fluid connection couples to a fluid mating connection, wherein the monument has a fluid main valve and a control unit for controlling the fluid main valve, an inlet of the fluid main valve couples to a fluid suction source, and a first end of the hose connects to the monument such that a first end of the fluid line is coupled to a first outlet of the fluid main valve. A second end of the hose is connected to the adapter such that a second end of the fluid line is coupled to the fluid connection, and the control unit controls the fluid main valve based on a triggering signal from the triggering unit.

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: 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: 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: 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 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 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: 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.