Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Jean-Michel Saucray

Esteban Quiroz-Hernandez

Philippe Chareyre

Laurent Lafont

Frederic Journade

Frédéric Journade

Mathieu Bonnet

Jerome Antypas

A winglet linked to a wing of an aircraft and equipped with a configuration changing device, the winglet being configured to be deformed elastically between a first configuration in the absence of an activation loading and a second configuration in the presence of an activation loading. The configuration changing device comprises at least one blocking cable configured to hold the winglet in the second configuration and at least one blocking system which comprises a tank containing a material configured to occupy a solid state in which the material immobilizes the blocking cable and a liquid state in which the material does not immobilize the blocking cable and allows the displacement thereof. An aircraft comprises wings provided with the winglets.

Winglet equipped with a configuration changing device with low energy consumption, aircraft comprising said winglet

The aircraft includes at least one engine having contra-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes a means capable of controlling the engine or at least one of the engines such that, at a given engine speed, the large axis of the ellipse or at least one of the ellipses extends in a direction for which the vibrations generated by the engine or engines have a minimum intensity in at least one predetermined site, particularly in a predetermined area, of the aircraft.

Aircraft comprising at least one engine having contra-rotating rotors

An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Aircraft including an engine controlled by synchrophasing

A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.

Device for locking an engine on an aircraft pylon

A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Growing community of inventors

Villeneuve les Bouloc, France

Jean-Michel Saucray