Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Sl

Airbus Operations Gmbh

Airbus Corporation

Franck Alvarez

Rémi Amargier

Pascal Pome

Alain Porte

Benedikt Bammer

Lionel Czapla

Damien Prat

Kotaro Fukasaku

Christophe Labarthe

Jean-François Allias

Nicolas Jolivet

Salvatore Demelas

Norberto Simionato Neto

Emeric Chancerelle

Damien Mariotto

Jacques Lalane

Laurent Lafont

Frederic Journade

Frédéric Vinches

Frédéric Goupil

Delphine Jalbert

Olivier Verseux

Frédéric Journade

Olivier Raspati

Benoît Penven

Emmanuel Vardelle

Anthony Roux

Mathieu Mahe

Olivier Ciet

Milan Tasic

Jean Francois Allias

Fabien Latourelle

Jean-Victor Lapeyre

Emmanuel Mermoz

A propeller-type propulsion system for aircraft, comprises a propeller, a plurality of electric motors comprising nested coaxial respective driveshafts, and a gearbox having an output shaft onto which the propeller is mechanically coupled, and an input shaft to which the coaxial driveshafts of the electric motors are mechanically coupled. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Propeller-type propulsion system for an aircraft

A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Propulsion unit with propeller and electric motor comprising an adapted primary structure, and aircraft having at least one such propulsion unit

A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

Propeller propulsion unit for an aircraft

A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Electric propulsion system of an aircraft

A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Disclosed is an air intake arrangement for an aircraft. The arrangement includes an air intake orifice, which is configured to bleed off a flow of external air, pass the external air through at least one air passage channel and ventilate a confined zone of the aircraft. An aerodynamically controlled shut-off means, comprised of a controllable mobile element and control means, is configured to regulate flow of the external air through the air passage channel to vary a cross section of the air passage channel relative to aircraft speed. The control means are arranged in the air passage channel and include an aerodynamic surface configured to apply a lift force to the control means to vary the cross section of the air passage channel as the flow of external air passes through the channel and toward the confined zone.

Air intake arrangement for a vehicle, in particular an aircraft

The object of the invention is an aircraft nacelle that comprises at least one part, called a door (), that moves relative to a stationary part () and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer () that is connected to the door () that comprises an attachment surface () and at least one attachment element (), and, on the other hand, at least one stop () that is connected to the stationary part () against which said indexer () can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (), oriented in the radial direction, is arranged upstream from the stop () in said direction, said at least one stop () comprising a surface relative to the door arranged essentially at the attachment surface () of the indexer ().

Fuse link device between a mobile part and a fixed part of an aircraft nacelle

An air intake arrangement includes a mobile plate controlled by at least one fluid communication passage or opening extending between the outer and inner surfaces of the mobile plate. The fluid communication passage or opening is located at least in the vicinity of a limited downstream area of the outer surface, is at a high pressure when the aircraft flies at cruising speed, and is capable of transmitting the high pressure to an extended area of the inner surface. The air flowing through the air intake arrangement may be used to refresh an enclosed area with electrical or mechanical equipment.

Air intake arrangement for an aircraft

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Toulouse, France

Franck Alvarez