Abstract: A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.

Abstract: A cover panel for a core panel of a structural aircraft component includes a protection cover having an outer shape corresponding to the outer shape of the core panel and including at least one cutout aperture, and at least one fabric panel mounted to the protection cover and covering the at least one cutout aperture.

Abstract: A mobile monitoring device including a data signal interface for coupling to a data line arranged in an aircraft and carrying one or more sensor signals, such that, in operation, the data signal interface branches off and receives as input signal part of the energy of the sensor signals carried on the data line such that the input signal is characteristic of the one or more sensor signals, and provide an output signal characteristic of the input signal. The mobile monitoring device further includes a wireless communication interface connected to the data signal interface for receiving the output signal and adapted to wirelessly transmit the output signal to a remote location. The present disclosure further relates to a system including an aircraft and the mobile monitoring device, and to a method of collecting sensor measurement data from a plurality of sensors of an aircraft using the mobile monitoring device.

Abstract: An aircraft luggage system comprising a luggage compartment which comprises an upper side directed towards a ceiling of an aircraft when the luggage compartment is assembled in the aircraft, a lower side directed towards a floor of the aircraft, a rear side directed towards an outer contour of the aircraft, and two side faces connect the upper side to the lower side. The lower side of the luggage compartment is rigidly connected to the side faces and the rear side of the luggage compartment. A flap, movable between a closed position and an open position, is configured to make an inner space of the luggage compartment accessible or to close it. At least one additional luggage compartment is arranged adjacent to at least one of the upper side and the lower side of the luggage compartment.

Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.

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: 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: 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: 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 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: 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 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: 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: 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: 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: 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 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

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: 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.