Abstract: A passenger seat system for a cabin of a means of transportation includes: a passenger seat having a seat frame having a holding section and a plurality of supporting elements for coupling to a floor; and, a slide device spaced apart from the holding section and having a base and a retaining device, to be detachably fastened to the base and be coupled to a supporting element. The base has a contact surface for laying onto a cabin seat rail, a locking device for locking the base on the seat rail, and a holding device for releasably holding the retaining device. The slide device is designed to lock the retaining device on the holding device selectively in a first or a second position or to release the retaining device and, when the retaining device is released, to permit motion of the retaining device between the first and the second positions.

Abstract: A modular lavatory assembly for a vehicle cabin includes a lavatory module having a housing and a toilet system having a toilet arranged in an inner space of the lavatory module and at least one service module having at least one service unit for personal use by a passenger. The at least one service module is attached to an outside of the housing. The housing encloses an inner space, which is free from additional service modules and includes at least one recess for accessing the at least one service unit of the at least one service module from an inside of the housing with the at least one service module being configured for providing access through the at least one recess. The at least one service module includes at least one additional access for accessing the at least one service unit from outside the housing.

Abstract: This relates to a method for manufacturing a shell-like structural component for a vehicle using additive layer manufacturing. In a step of the method, a first material is applied to a region of the shell-like structural component. In another step of the method, the region of the shell-like structural component is heated by a laser beam such that the first material is added to the shell-like structural component. The shell-like structural component comprising the first material is cooled in another step such that an internal stress is generated within the shell-like structural component resulting in a bending of the shell-like structural component. This further relates to a shell-like structural component which is manufactured by a method using additive layer manufacturing.

Abstract: An indicating device for indicating a non-authorized opening of an aircraft door comprising a sensor for detecting a distance from the sensor to an object, a signaling device, a reset device coupled to the signaling device allowing the signaling device to be set into a first state following a reset operation, an enabling device, providing as an output signal, selectively, a disable signal and an enable signal, and a control device connected to the sensor, the signaling device and the enabling device. On receiving the disable signal, the control device changes into a first operating mode and on receiving the enable signal it changes into a second operating mode in which, based upon the signal received from sensor, it detects a distance change between the sensor and the object, and, on detecting a change, sets the signaling device into a second state until the reset operation is completed.

Abstract: An auxiliary power system for an airplane includes at least one fuel cell unit each with at least one fuel cell, a voltage output, a fuel intake and an outlet for reaction products, a fuel tank that is couplable with the fuel intake of the fuel cell unit, at least one compressor unit with an air intake and air outlet and an electric motor, which is couplable with a voltage output of the at least one fuel cell unit and, by way of a shaft, with the at least one compressor unit. At least the at least one fuel cell unit, the compressor unit and the electric motor are interconnected to yield a coherent unit, which continuously provides electrical power and pressurized air.

Abstract: An engine bleed air system of an aircraft, comprising a heat exchanger which comprises a rectangular core with a rectangular outlet section, a cylindrical outlet duct and a transition area between the rectangular outlet section of the rectangular core and the cylindrical outlet duct, and at least a downstream system, further comprising a flow deflector located at least in the cylindrical outlet duct, such that the outlet flow characteristics homogeneity are improved and a particular flow deflection and distribution of the outlet flow is achieved, avoiding the damage of the at least one downstream system. The invention also provides a method for homogenizing the temperature of the outlet flow of a heat exchanger outlet in an engine bleed air system of an aircraft.

Abstract: A system for stock management for on-board catering for a vehicle, in particular for an aircraft, includes a galley which is provided with a control unit for controlling the galley, wherein the control unit is designed to make available stock management data of the galley; a service unit for transporting supplies within the vehicle, wherein the stock management data comprise a stock record of the supplies transported with the service unit; and at least one operator control element which is communicatively connected to the control unit of the galley via a wireless data connection and is designed to record removal of a supply item from the service unit and/or reception of a supply item into the service unit, and to bring about updating of the stock record of the transported supplies on the basis thereof.

Abstract: A galley monument for an aircraft has a number of compartment walls and a functional wall, which has a receiving recess extending in the direction of the depth, wherein the compartment walls and the functional wall together define at least one slide-in compartment of the galley monument. The galley monument also has a display arrangement with a display device, wherein the display arrangement can be stowed in the receiving recess in a stowage position, in which the display device is at least partially accommodated in the receiving recess. Also described is an aircraft which has at least one such galley monument.

Abstract: A fastening system for passenger seats in a vehicle cabin has two or more guide rails to be integrated into or onto a cabin floor, and a plurality of slides, to be brought into engagement with the guide rails and having a flange for connection to a passenger seat to retain the passenger seat on a guide rail. Each guide rail has a profile cross section, perpendicularly to a main axis of extent (x), having a base region, a supporting region and an undercut situated therebetween. Each slide has a cavity, of complementary design with the profile cross section, and a necked region, to be brought into engagement with the undercut, thus enabling the supporting region to be enclosed by the cavity of the slide. Each slide has a rotatably mounted roller projecting into the necked region and can be brought into surface contact with a guide rail surface.

Abstract: A monitoring system for an aircraft cabin has a main computing unit, a galley operator control apparatus and a physically separate data distribution apparatus, having a first computing unit and a second computing unit, which is autonomous in respect of the latter, and connected via an interface circuit for data interchange. The first computing unit is set up to take a cabin output signal received from the main computing unit for providing an operating signal for operating a cabin function. The second computing unit is set up to take a control command received from a galley operator control apparatus display device as a basis for providing a switching signal prompting a power control device to switch an electrical load on or off, set up to take a cabin output signal received from the first computing unit for providing a display signal to reproduce information on the display device.

Abstract: A galley monument for an aircraft has a plurality of walls which define at least one slide-in compartment of the galley monument, and a display device which is coupled pivotably to one of the walls by an articulation device, wherein that wall to which the display device is coupled has a receiving recess into which the display device can be pivoted into a stowage position. Furthermore, an aircraft is described which has at least one such galley monument.

Abstract: An oxygen supply system includes a container housing having a container door, a latch controller coupled to a latch of the container door and configured to control the latch to releasably open the container door, a microcontroller coupled to the latch controller and configured to output a first latch deployment signal to the latch controller to cause the latch controller to open the latch, a pressure sensor coupled to the latch controller and configured to output a second latch deployment signal to the latch controller to cause the latch controller to open the latch, and an energy storage coupled to the microcontroller and the pressure sensor and configured to supply the microcontroller and the pressure sensor with electrical energy. The microcontroller includes built-in test equipment (BITE) configured to monitor and test the operability of one or more of the microcontroller, the latch controller, the pressure sensor and the energy storage.

Abstract: An aircraft air conditioning system comprises an ambient air supply line adapted to be flown through with ambient air, an ambient air cooling apparatus, which is connected to the ambient air supply line and is configured to cool the ambient air flowing through the ambient air supply line, an ambient air discharge line, which is connected to the ambient air cooling apparatus and is connectable to an aircraft cabin, in order to conduct ambient air cooled by the ambient air cooling apparatus into the aircraft cabin, a process air supply line adapted to be flown through with compressed process air, a process air cooling apparatus, which is connected to the process air supply line and is configured to cool the compressed process air flowing through the process air supply line, a process air discharge line, which is connected to the process air cooling apparatus and is connectable to the aircraft cabin, in order to conduct process air cooled by the process air cooling apparatus into the aircraft cabin, and a refrig

Abstract: A waste compaction system for a vehicle includes a moveable trolley for storing waste, and a docking station integratable into a cabin monument for inserting the trolley. The trolley includes a housing having an opening for inserting waste, a vacuum waste compacting mechanism inside the housing and a first suction port accessible from outside the housing, the first suction port being couplable with the vacuum waste compacting mechanism. The docking station and the trolley are adapted to each other such that the trolley is engageable with the docking station, and wherein the docking station includes a second suction port couplable with a suction line in the vehicle and the first suction port. Resultantly, a lightweight and efficient waste compaction system is provided, which allows moving the trolley for collecting waste inside a cabin of the vehicle.

Abstract: Inter alia, an apparatus including a ramp, the ramp configured to enable variation of a cross section of a ram air passage of the apparatus. The ramp includes a first rigid member, a second rigid member and a flexible member coupled to the first rigid member and the second rigid member. The ramp is movably mounted at two ends. Moreover, a method of varying the cross section of the ram air passage of such an apparatus by moving the ramp of the apparatus is disclosed. Further, an arrangement including such an apparatus and a ram air channel communicating with the ram air passage is disclosed.

Abstract: A magnetically levitated arrangement for contactless movement over a surface comprising a magnetizable reaction surface and a magnetically levitated unit arranged to interact with the reaction surface. The levitated unit has at least one pair of rotatable rotary magnet units, each unit rotatable about a rotation axis and having magnetic elements arranged with alternating poles and respectively substantially parallel to the rotation axis in a pole connection direction. Each rotary unit pair is formed to interact, due to rotation of the two rotary units in opposite directions relative to one another and relative to the reaction surface, in such a way with the reaction surface, that forces are generated holding the levitated unit at a distance from the reaction surface, and due to the opposite rotation directions of the rotary units of each pair, a directed drive force moving the levitated unit relative to the reaction surface is generated.

Abstract: A method for manufacturing a rivet connection of a fiber composite component. The method includes positioning a first component which contains a fiber composite material in an overlap joint with a second component, laser-drilling a shared through-hole at least through the fiber composite material of the first component, inserting a rivet into the through-hole and fixing the rivet to the first and to the second component.

Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: A computer-implemented method for space frame design involves constructing a load stress map in a geometrical boundary representation of a design space, defining attachment points and load application points in the design space, creating a starting network of interconnecting lines between each two of the attachment points and load application points in the design space, assigning load application factors to each line of the starting network of interconnecting lines based on values of the load stress map, generating potential space frame designs by culling different subsets of lines of the starting network of interconnecting lines for each potential space frame design according to variable culling parameters, evaluating the potential space frame designs with respect to optimization parameters, combining the culling parameters for the potential space frame designs the performance score of which is above a predefined performance threshold, and iterating the steps of generating potential space frame designs and e