Airbus Deutschland Gmbh

Airbus Operations Gmbh

Daimler-benz Aerospace Airbus Gmbh

Daimlerchrysler Aerospace Airbus Gmbh

Airbus Operations (s.a.s.)

Hamilton Sundstrand Corporation

Airbus (sas)

Airbus Operations Sl

Deutsche Aerospace Airbus Gmbh

Daimier-benz Aerospace Airbus Gmbh

Thomas Scherer

Michael Markwart

Uwe Buchholz

Alexander Solntsev

Jens Lohmar

Dietrich Lampe

Martin Schmid

Torsten Schwan

Jens Elmers

Rainer Mueller

Dariusz Krakowski

John M Maljanian

Juergen Kelnhofer

Jürgen Kelnhofer

Markus Petrac

Matthias Witschke

Ruediger Schmidt

Oliver Schaumann

Sven Uhlemann

Ralf Schliwa

Frank Klimpel

Markus Piesker

Holger Bammann

Ahmet Kayihan Kiryaman

Didier Poirier

Hans-Juergen Mueller

Jorge Alejandro Carretero Benignos

Jan Dittmar

Olivier Verseux

Thomas Heuer

Walter S Hojnowski

Steffen Kalsow

Torsten Stengel

Klaus Petry

David Leenhouts

Harald Kull

Carsten Colberg

Benedikt Bammer

Georg Mühlthaler

Thorsten Schiek

Walter Kulcke

Nico Centofante

Rüdiger Schmidt

Heinz Fischer

Heiko Luetjens

Alvy Biccum

Michael Dreyhaupt

Jorge Molano Rembiasz

Philippe Pene

Maria Del Sagrario Juanas Fernandez

Thomas Josset

Uwe Buchholtz

Siegfried Seidler

Juergen Fischer

Martin Dechow

Michael Heesch

Volker Von Doehlen

Patrick Bäumle

Jens c/o Airbus Operations Gmbh Elmers

Michael c/o Airbus Operations Gmbh Markwart

Martin c/o Airbus Operations Gmbh Schmid

Jens c/o Airbus Operations Gmbh Lohmar

Volker Von Döhlen

An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Auxiliary power unit for an aircraft

An electric generator including a number of electric accumulators and at least one heat-sink device using a phase-change material configured to pick up the excessive thermal energy produced by one of the electric accumulators and change phase in order to absorb a large quantity of thermal energy in the form of latent heat.

Electric generator comprising a plurality of electric accumulators and at least one heat-sink device incorporating a phase-change material

An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Electric propulsion unit of an aircraft comprising a cooling system incorporating at least one front air inlet and aircraft comprising at least one such electric propulsion unit

A mixing device that is particularly suitable for use in an aircraft air-conditioning system comprising a cold air supply line adapted to supply cold air to the mixing device. A first recirculation air supply line is adapted to supply recirculation air to the mixing device. A mixing chamber is connected to the cold air supply line and the first recirculation air supply line and is adapted to supply the cold air supplied to the mixing device via the cold air supply line with the recirculation air supplied to the mixing device via the first recirculation air supply line. The first recirculation air supply line has a heat transfer portion which is thermoconductively connected to an area of a wall delimiting the mixing chamber that is at risk of icing.

Mixing device with reduced risk of icing

A mixer assembly for an air-conditioning system comprising a recirculation air line, connectable to a vehicle region to be air-conditioned, to remove recirculation air from the region, and an air-conditioning air line, connectable to an air-conditioning unit to remove conditioned air from the air-conditioning unit. A first mixing region, for mixing the recirculation air with the conditioned air, is connected to the two air lines. A second mixing region, for mixing the first mixing region air with recirculation air, is connected to the recirculation air line and the first mixing region. Also, a first supply line is connected to the first mixing region to supply air from the first mixing region to a first partial region of the vehicle region, and a second supply line is connected to the second mixing region to supply air from the second mixing region to a second partial region of the vehicle region.

Mixer assembly and method for operating a mixer assembly

An aircraft air conditioning system comprises a process air source and an air conditioning unit being connected to the process air source via a process air line and being adapted to cool and expand process air supplied to the air conditioning unit from the process air source so as to provide conditioned air. A mixing chamber of the aircraft air conditioning system is connected to the air conditioning unit via a conditioned air line and is adapted to mix conditioned air supplied to the mixing chamber from the air conditioning unit with recirculation air recirculated from an aircraft region to be air conditioned to the mixing chamber via a recirculation air line so as to provide mixed air.

Aircraft air conditioning system and method of operating an aircraft air conditioning system

A mixing device for an aircraft air conditioning system includes a plurality of cold-air supply lines, which are devised to supply cold air to the mixing device. A plurality of warm-air supply lines is further provided, which are devised to supply warm air to the mixing device. A first premixing chamber is connected to the cold-air supply lines and devised to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber. A second premixing chamber is connected to the warm-air supply lines and devised to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber. Finally, a main mixing chamber is connected to the first and the second premixing chambers and devised to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber.

Mixing device for an aircraft air conditioning system

A mixer for an aircraft air conditioning system has first and second fresh air lines and first and second recirculation air lines. A first premixer is connected to the first fresh air line and the first recirculation air line, to mix the fresh air with the recirculation air thereof. A second premixer is connected to the second fresh air line and the second recirculation air line, to mix the fresh air with the recirculation air thereof. A main mixer is connected by a first premixed air line to the first premixer and by a second premixed air line to the second premixer. The main mixer is adapted to be supplied through the first premixed air line and the second premixed air line exclusively with premixed air from the first and/or the second premixer.

Mixer assembly for an aircraft air conditioning system

A cooling system for an aircraft includes an air inlet through which air from the environment of the aircraft enters a ram air channel, and an air outlet through which air emerges from the ram air channel. A heat exchanger is arranged in the ram air channel. A ventilation device is in fluid communication with the ram air channel. Also connected to the ram air channel is a distribution line to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

Ram air based cooling and ventilation system for an aircraft

The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention, a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor.

Counter electro-motoric force based functional status detection of an electro-motor

Method for controlling the temperature of feed air injected into at least one cabin zone of a passenger aircraft, the temperature of injected feed air being controlled for each cabin zone dependent on the deviation of the injection temperature actual value of the feed air from an injection temperature target value, the injection temperature target value being established using an external ambient temperature actual value and not using a temperature sensor in the at least one cabin zone.

Method for controlling the temperature of feed air injected into the cabin zone of a passenger aircraft

The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

Air inlet valve for an airplane and manufacturing method for an air inlet valve

A device for temperature control in an aircraft cabin includes a first supply control arrangement and a first pressure control arrangement. The first supply control arrangement includes an air duct and a valve arrangement that controls a supply of heated air delivered to a first temperature area of the aircraft cabin such that a first specified temperature for the first temperature zone is achieved. When the valve arrangement fails, the first pressure control arrangement operates to control a pressure of heated air supplied into the first temperature area such that the first specified temperature for the first temperature zone is achieved.

Device and method for temperature control in an aircraft cabin

A ram-air duct includes a ram-air inlet duct and a ram-air outlet duct arranged downstream of the ram-air inlet duct and in fluid communication with the ram-air inlet duct. At an inlet of the ram-air inlet duct, a first movable element is arranged and adapted to set an inlet parameter of the inlet. At an outlet of the ram-air outlet duct, a second movable element is arranged and adapted to set an outlet parameter of the outlet. The outlet parameter and the inlet parameter are linked together by a function, so that an outlet parameter corresponding to a value of the function is assigned to each inlet parameter. A controller implements the control function by actuating movements of the first and second movable elements.

Drag-optimised ram-air duct and process for controlling a mass flow of ambient air or cooling air through a ram-air duct

The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit, wherein the heat transfer unit comprises a second air supply pipe, through which a waste air heat flow to be cooled that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow, wherein the heat transfer unit comprises a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, and wherein at least a portion of the heated bilge flow is returned to the bilge area via the air discharge pipe and the bilge inlet section.

Arrangement and method for utilizing the heat of waste air for heating the bilge area of aircraft

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Hamburg, Germany

Thomas Scherer