Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Sl

Till Marquardt

Andreas Westenberger

Lars Frahm

Martin Arendt

Guillaume Gallant

Geza Schrauf

Philip Wright

André Anger

Alberto Gallegos Elvira

Jose Luis Martinez Munoz

Carsten Koeppen

Sebastian Thiel

Kasidit Leoviriyakit

Anna-Katrin Wengorra

Kaya Sahin

Rainer Tegtmeyer

Elisa Alvarez López-Herrero

Michael Wießmeier

Matthias Wolff

Alexander Broer

Marco Dias Figueiredo

An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T) distinct from the first section (T) and from the second section (T). The third section (T) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Aircraft fuselage intended to receive two tanks designed to contain liquid hydrogen

An aircraft fuel cell system includes a fuel cell which has an oxidant inlet for supplying an oxygen-containing medium to the fuel cell. An oxidant supply line has a first end which is connected to the oxidant inlet of the fuel cell. A second end of the oxidant supply line is connectable to a used air outlet of a cabin of the aircraft. A heat exchanger is located in the oxidant supply line and thermally couples the oxygen-containing medium flowing through the oxidant supply line and a second medium flowing through an air conditioning process air line of an air conditioning unit, the heat exchanger being located downstream of a cabin air compressor in the air conditioning process air line.

Aircraft fuel cell system

The present invention relates in to a device for supplying mechanical power to start at least one engine, with a power supply device for supplying electrical power with an alternating voltage and constant frequency; and with a number, N1, of conversion devices for the conversion of the supplied electrical power to a respective mechanical power for a respective engine, wherein a respective conversion device has a cascade starter generator for direct conversion of the supplied electrical power to mechanical power, wherein the cascade starter generator has a first stator, a second stator, a first rotor and a second rotor, the first stator being integrally formed with the second stator and the first rotor being integrally formed with the second rotor. The present invention further relates to an aircraft comprising such a power distribution network and a method for supplying mechanical power to start at least one engine in an aircraft.

Device and method for converting supplied electrical power into mechanical power to start at least one engine

A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.

Cooling system on the basis of suction of a boundary layer

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Hamburg, Germany

Till Marquardt