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: 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: A fiber-optic communication system for an aircraft including: a light source operable to generate light; a transceiver in optical communication with the light source, the transceiver including a control input and a reflector; an optical fiber in optical communication with the transceiver; and a light detector in optical communication with the optical fiber. The transceiver is operable to generate an amplitude modulated light signal by selectively reflecting the light received from the light source into the optical fiber using the reflector according to information received at the control input. The light detector is operable to receive the amplitude modulated light signal from the optical fiber and to detect an amplitude of the amplitude modulated light signal to extract the information.

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: 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 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 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 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: The invention is a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has a plurality of shafts rotatable about respect shaft axes, including an output shaft. The output shaft is operable to pivot about the axis of rotation of another shaft axis spaced from the output shaft axis. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: A device for adjusting the position of structural elements of a structure of an aircraft, comprising a measurement tool for determining a value for the actual position of each structural element, a processing and calculation system for comparing each value of the actual position determined by the analysis system with a corresponding theoretical value, and for determining therefrom an adjustment value, an adjustment tool configured to be attached in use to a structural element, comprising at least one measurement sensor configured to measure a distance between the measurement sensor and the structural element, a calculator for comparing the value measured by the measurement sensor with the corresponding adjustment value, and for deriving therefrom corrective actions to finalize adjustment of the structural element, and a communication system for exchanging information between the adjustment tool and the processing and calculation system.

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 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: 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: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

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.