Abstract: A method for adjusting play in a high-lift system of an aircraft with several flaps, moved by a drive unit with the aid of driving stations connected to a driveshaft, includes disengaging the mechanical connections between the driveshaft and the driving stations in the first position, displacing the individual drive levers by mechanically driving a gear input of the associated rotary actuator such that the individual drive levers come into mechanical contact with a stop in a second position, spaced apart from the first position, and are pretensioned by a certain torque, rotationally fixing the gear inputs of the rotary actuators, adapting the length of connecting links between the respective drive levers and a support arm carrying the associated flap such that a position of the associated flap corresponding to the position of the stop is reached, and reconnecting the driving stations to the driveshaft pretensioned to have no play.

Abstract: A trolley for collecting waste includes: wheels, a steering handle, and a housing with a bottomwall and a sidewall extending vertically from the bottomwall, wherein the housing forms a waste chamber, wherein the sidewall comprises an opening, wherein a flap is connected by a first bearing to the sidewall of the housing, such that the flap is pivotable about a horizontal flap axis between a closing position and an opening position. The flap in its closing position closes the opening of the sidewall, and the flap in its opening position opens the opening in the sidewall, wherein the handle is connected by a second bearing to the housing, such that the handle is pivotable about a handle axis between a first handle position and a second handle position, and the handle is linked to the flap by a mechanical linkage, such that pivoting the handle from its second handle position to its first handle position results in a pivoting of the flap from its opening position to its closing position.

Abstract: A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power.

Abstract: A method for starting up electric or electronic devices, in particular devices in or for an aircraft or spacecraft, including: supplying at least one location identification which contains at least one piece of information about the location of a respective device; detecting a supplied location identification for one device in each case; transmitting the detected location identification to the respective device; and parameterizing the respective device by means of the transmitted location identification. The present invention also provides a start-up apparatus, a server system and a system.

Abstract: A method for emergency ventilating and pressurizing an aircraft cabin comprises determining a cabin pressure within the aircraft cabin and determining an ambient pressure in an aircraft environment. Descent of the aircraft is initiated when the cabin pressure falls below a predetermined threshold value. A supply of ambient air from the aircraft environment into the aircraft cabin is initiated, when, during descent of the aircraft, a differential pressure between the cabin pressure and the ambient pressure falls below a first calculated threshold value. The supply of ambient air into the aircraft cabin and an operation of an air outflow valve of a cabin pressurization system of the aircraft are controlled such that a flow of ambient air into the aircraft cabin corresponds to at least a predetermined minimum value and the differential pressure between the cabin pressure and the ambient pressure does not fall below a second calculated threshold value.

Abstract: A passenger supply system installed in a passenger supply channel (PSC) on board a vehicle, such as an aircraft. The supply system comprises a rail track configured to be mounted along the PSC. The supply system further comprises an indiv panel mounted on the rail track and connectable to the PSC for supplying a passenger with conditioned air, medical outlet and/or oxygen. The indiv panel comprises a crossover area. The supply system further comprises a passenger supply unit mounted on the rail track and connectable to the PSC for supplying the passenger with light, visual information and/or sound information. The supply unit comprises an overlapping area. The supply unit and the indiv panel are configured such that in a mounted state of the supply unit and of the indiv panel the overlapping area of the supply unit at least partially overlaps with the crossover area of the indiv panel.

Abstract: An adapter for receiving a vehicle attendant seat in a cabin of a vehicle comprises a flat retaining body, a receiving device for a vehicle attendant seat, at least one first pivoting means and at least one first securing means. The at least one first pivoting means is arranged on a pivoting edge of the retaining body and is adapted for forming a hinge with at least one correspondingly formed second pivoting means. The receiving device is arranged on a surface of the at least one retaining body, which surface extends parallel to the plane, and is adapted for mechanically connecting the vehicle attendant seat with the at least one retaining body. Thus in a vehicle cabin a vehicle attendant seat may be accommodated in a very space-saving manner even at locations to which in conventional vehicle operation access is required.

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: The invention pertains to a connecting device for connecting a first structural component and a second structural component that can be moved relative to the first structural component in an articulated fashion such that three rotatory degrees of freedom are provided.

Abstract: A vehicle body includes a primary vehicle structure and interior vehicle fittings as well as a coupling device for fastening the interior vehicle fittings to the primary vehicle structure. The coupling device is configured to generate a magnetic field, so as to fasten the interior vehicle fittings to the primary vehicle structure without contact. Methods for assembling a vehicle body as well as an edifice are also described.

Abstract: Production methods for producing a fibre-reinforced metal component having a metal matrix which is penetrated by a plurality of reinforcing fibres are provided. One method includes depositing in layers reinforcing fibres in fibre layers, depositing in layers and liquefying a metal modelling material in matrix material layers, and consolidating in layers the metal modelling material in adjacently deposited matrix material layers to form the metal matrix of the fibre-reinforced metal component. Here, the metal component is formed integrally from alternately deposited matrix material layers and fibre layers. An alternative method includes introducing an open three-dimensional fibrewoven fabric consisting of reinforcing fibres into a casting mould, pouring a liquid metal modelling material into the casting mould and consolidating the metal modelling material to form the metal matrix of the fibre-reinforced metal component.

Abstract: A service module for supplying passengers in a passenger space of a means of transport, in particular of an aircraft, and to a service system having a service channel and a plurality of such service modules. The service module comprises at least one service component arrangement having one or more service components for individually supplying one or more passengers, and a cabin lighting unit for illuminating the passenger space of the means of transport, in particular of the aircraft.

Abstract: The present invention provides a seat adjustment device for an aircraft or spacecraft, comprising: a seat rail for connection to a floor; and a seat connection for connection to at least one seat; and a worm is provided which can be actuated to adjust the seat connection relative to the seat rail.

Abstract: The invention relates to a system and a method for preventing inadvertent slide deployment for an aircraft, comprising at least one sensor for sensing the proximity of a person in front of an aircraft door, and at least one optical warning means operable to provide an optical indication in the vicinity of a slide arming lever when the sensor detects the proximity of a person in front of the aircraft door. The system according to the invention provides an effective prevention for inadvertent slide deployment that is capable to guide trained and untrained persons to the information they need in order to disarm the slide in sufficient time before the door handle is gripped and pulled to open the aircraft door in normal operation conditions.

Abstract: An arrangement in a cabin of an aircraft includes a plurality of passenger seats, which create seat rows arranged between at least one aisle and a cabin wall. At least one first section has at least one row with a first number of passenger seats and at least one second section has at least one seat row with a second number of passenger seats, that is below the first number, are created. The at least one seat row of the first section and the at least one seat row of the second section directly border on the at least one aisle. In the second section between a passenger seat facing the cabin wall and the respective cabin wall a stowage compartment is arranged, which is positionable on a cabin floor.

Abstract: A handling system for handling objects in a vehicle comprises a storage apparatus that is positionable outside a vehicle cabin, an access device that is positionable in a vehicle cabin, and a transport device for transporting objects between the storage apparatus and the access device. The storage apparatus comprises a storage space and a connection station that is connectable to the transport device, wherein the storage apparatus comprises at least one drive device for moving carriers on which objects to be stored are held. The handling system comprises at least one guiding device that with the drive device guides the carriers on at least one circular path within the storage space. The storage space thus comprises a vertical flat shape that results in a significantly smaller reduction in the available cargo volume in a vehicle, while at the same time maximizing the design space available for passenger seats.

Abstract: The present invention relates to an electronic device including a display module and an electronics module arranged in a common housing, wherein the common housing is completed by a front cover, wherein the display module is arranged directly adjacent to the front cover, wherein the electronics module includes a printed circuit board having multiple layers and a plurality of electronic components attached to the printed circuit board, wherein the electronics module is arranged adjacent to the display module and wherein the printed circuit board includes a first layer and a second layer delimiting the printed circuit board on opposing sides, wherein the first layer is an electromagnetic interference shielding layer and the first layer is arranged facing the display module.

Abstract: An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

Abstract: A double-deck airplane that facilitates passenger embarking/disembarking and cargo loading/unloading operations in order to maximize the number of flight missions carried out in a given time. The floors of its upper and lower decks are planar surfaces extending continuously inside the fuselage in at least the inner space of the fuselage intended for the payload; the lower deck is located at a height from the ground that allows carrying out passenger embarking/disembarking via equipment incorporated in the airplane without any external airport ground equipment; passenger and/or cargo compartments are distributed on the upper and/or lower decks; and the lifting structure is disposed in the airplane in a manner that none of its components crosses the upper and lower decks.

Abstract: A method for triggering a first emergency measure associated with an aircraft emergency comprising the steps of determining a risk level for an aircraft emergency and triggering the first emergency measure if the risk level exceeds a first threshold for the first emergency measure is described and claimed. The risk level is determined by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. The first threshold is adjusted according to a position of the aircraft over ground. Furthermore, a system for use onboard an aircraft for triggering a first emergency measure and an aircraft comprising such a system are disclosed.