Airbus Operations Gmbh

Airbus Deutschland Gmbh

Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Sl

Alexander Solntsev

Thomas Scherer

Holger Bammann

Frank Klimpel

Ruediger Schmidt

Johannes Eichholz

Rüdiger Schmidt

Thomas Selchert

Bruno Stefes

Olivier Verseux

Jorge Alejandro Carretero Benignos

Benedikt Bammer

Alexandre Broquet

Jens Beier

James Brown

Hugo Alexandre Duart Mendes Raposeiro

Heiko Rothe

Michael Heesch

Jorge Molano Rembiasz

Maria Del Sagrario Juanas Fernandez

Hugo Alexandre Duarte Mendes Raposeiro

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

An inerting system and method for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Inerting system and method for an aircraft using exhaust air

An inerting system for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

A ram air channel arrangement for ambient air supply into an aircraft comprises a ram air channel which has a ram air inlet channel and a ram air outlet channel arranged downstream of the ram air inlet channel and in fluid communication with the ram air inlet channel. The ram air channel arrangement further comprises a cabin exhaust air line which is adapted to have cabin exhaust air flow therethrough which has been removed from an aircraft cabin and which cabin exhaust air line is connected to the ram air inlet channel and is adapted to lead the cabin exhaust air into the ram air inlet channel.

Ram air channel arrangement and method for operating a ram air channel arrangement

Device for exhaust air cooling of aircraft air-conditioning systems comprising a bypass channel that bypasses an aircraft air-conditioning system arranged downstream of a ram air channel with a ram air inlet channel portion, and merges into an outlet channel, arranged downstream of the aircraft air-conditioning system, before a discharge opening for exhaust air, a common inlet being provided for the ram air channel and the bypass channel.

Device and method for cooling exhaust air of aircraft air-conditioning systems

A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

Fresh air inlet for an aircraft

An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.

Gas exhaust diverter

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

A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air () within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.

Cooling air supply for the cooling of different systems requiring cooling air in an aircraft

Aircraft air-conditioning system () for an aircraft having a plurality of zones (), comprising a first line () for feeding cold air at an actual temperature T, a second line () which branches off a portion of the air from the first line () at a branching point () and feeds the air to a plurality of zones () of an aircraft, wherein warm air is fed through a first trim valve () into the second line () so that the air in the second line () is heated to the actual temperature T, and a first zone feed line () feeding the air downstream of the first trim valve () to a first zone (), wherein a second trim valve () is arranged in the first zone feed line (), through which valve warm air is fed into the first zone feed line () so that the air in the first zone feed line () is heated to the actual temperature Tzf, and the first line () downstream and/or upstream of the branching point () feeds cold air at least to one further zone. A second feed line () feeds air downstream of the first adjustment () to a second zone (). A heating device () can be arranged in the second feed line ().

Air-conditioning system with icing protection for an aircraft

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

A ram air channel () for the supply of ambient air in an aircraft includes a first air inlet () and a main flow channel () which extends downstream of the first air inlet (). In order to guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, i.e. both during the flight and on the ground, the ram air channel () has a second air inlet () which is independent from the first air inlet ().

Ram air channel for the supply of ambient air in an aircraft

A system () for cooling a thermally loaded device on board an aircraft comprises a distribution line () which is in communication with an installation space () of the thermally loaded device, a coolant supply line () which is in communication with a coolant source, and a heat removal line () which is in communication with a source of pressure below atmospheric pressure. A shut-off control device () is adapted so as, in a first position, to separate the distribution line () from the coolant supply line () and connect the distribution line () to the heat removal line () and, in a second position, to connect the distribution line () to the coolant supply line () and separate the distribution line () from the heat removal line ().

System and method for cooling a thermally loaded device on board an aircraft

Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, an air supply device for an OBIGGS system in an aircraft is proposed that comprises a bleed position (). By way of the bleed position (), air from an air conditioning unit () on board the aircraft can be bled and can be fed to the OBIGGS system. There is thus no need for an additional heat exchanger and an additional ram-air channel. Maintenance expenditure and air resistance are thus reduced.

Air supply for an aircraft

An air guiding flap of an aircraft wherein one surface thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface is exposed to the pressure of the relative wind flowing past the aircraft. The air guiding flap comprises an actuator for automatically opening and closing the air guiding flap which actuator cooperates with a device for controlling the position of the air guiding flap. In order to keep the stress on the air guiding flap low a force detecting device is provided which detects the force impinging on the actuator base don a difference between the prevailing pressure in the air duct and the pressure of the relative wind flowing past the aircraft. The controlling device adjusts the position of the air guiding flap such that the force impinging on the actuator at any one time is at least essentially zero.

Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap

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Hamburg, Germany

Alexander Solntsev