Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Henning Everth

Patrick Lieven

Jens Schult

Frank Klimpel

Jens Lohmar

Dietrich Lampe

Fabian Kraus

Jörg Schwickert

Felix Braun

Sven Rosebrock

Bernward Mons

Oliver Hennig

An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, wherein the aircraft structure includes an upper shell and a lower shell that together surround an interior compartment designed for accommodating an aircraft cabin, and a pillar arrangement with at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other. An aircraft structure can be provided which is particularly efficient, in particular has a low weight and requires little space and outlay on assembly is achieved in that the interior of the support pillar has at least one flow duct for the conduction of air-conditioned air.

Aircraft structure

An aircraft refrigeration system comprises an ambient air line, through which ambient air flows and which is connected to conduct ambient air to an aircraft, an ambient air compressor, arranged in the ambient air line, for compressing the ambient air in the ambient air line, a cabin exhaust air turbine, connected to a cabin exhaust air line and coupled to the ambient air compressor in the ambient air line and configured to expand cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor, a transmission, configured to couple the cabin exhaust air turbine to the ambient air compressor and to set a speed of the ambient air compressor, and a motor, coupled to the transmission and configured to drive the ambient air compressor.

Aircraft refrigeration system having a motor-assisted cabin exhaust air turbine

A mixer assembly for mixing two air streams in a ventilation system. The mixer assembly comprises a mixing chamber, which comprises an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber, and also a shroud, which surrounds the mixing chamber wall, at least in certain portions. The shroud forms and delimits an intermediate space between the mixing chamber wall and the shroud. The mixer assembly also comprises a filter element, which fluidically connects the intermediate space to a surrounding area of the mixer assembly, the intermediate space being fluidically connected to the mixing chamber. Fluid can thus flow through the filter element into the intermediate space and further into the mixing chamber. A stowage space with a mixer assembly, an aircraft with such a stowage space and a method for producing a mixer assembly in an aircraft are also described.

Mixer assembly with surrounding filter element, stowage space with mixer assembly, vehicle with a stowage space and method for installing a mixer assembly

A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network.

Method for detecting a device that generates spurious signals in an electrical network, an electrical system and an aircraft

An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold.

Controlling an electrical consumer of an aircraft

A system for checking the positioning of components is provided. The system includes a reading device for reading in component identification information, which is provided by an identification device in a spatially limited region about a component to be checked, a locating device with at least one stationary reference device, a movement component which is movable relative thereto and a computing unit. The reading device and the locating device can be connected to the computing unit. The computing unit is set up to detect a relative position of the movement component with respect to the at least one reference device in the spatially limited region about the component to be checked and to form a data pair from the detected relative position with component identification information read in by means of the reading device and to compare it with predefined data pairs.

System and method for identifying a component

An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.

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Hamburg, Germany

Henning Everth