Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Esteban Quiroz-Hernandez

Jean-Michel Saucray

Laurent Lafont

Frederic Journade

Jean-Pierre Demortier

Sylvain Raynaud

Christophe Bouchet

Marc Vie

Frédéric Journade

Mathieu Bonnet

Sébastien Blanc

Jerome Antypas

Robin Vernay

François Cusset

Alexandre Grattard

Jérôme Antypas

Jean Michel Saucray

A method and device for adjusting performance variables of an aircraft. The device which is intended for adjusting performance variables, the performance variables being generated by at least one performance module, includes an auxiliary data input unit for entering into a flight management system correction data intended to be used for adjusting at least one associated performance variable, and a correction unit for carrying out a correction, the correction including adjusting the associated performance variable on the basis of the input correction data.

Method and device for adjusting performance variables of an aircraft

An actuating system comprising a hydraulic actuator provided with a cylindrical cavity containing a piston configured to slide within the cylindrical cavity and a rod. The piston separates the cylindrical cavity into a first actuating chamber and a second actuating chamber. A first servo valve comprises a sheath including a first slider configured to slide within a cavity of the sheath on the basis of command signals from a command system. The cavity of the sheath comprises a first command chamber and a second command chamber on either side of the first slider. The first actuating chamber is fluidically connected to the first command chamber, and the second actuating chamber is fluidically connected to the second command chamber.

System for actuating a control surface of an aircraft

In order to eliminate or at least to reduce a possible unbalance of the propulsive system, counterweights are brought in locations that are provided on the hub envelope, near the ends of the latter and away from the planes of the propellers. More particularly, the counterweights are provided as discrete elements located in two planes spaced from the propellers and orthogonal to an outer surface of the hub envelopes, or are provided as a non-uniform mass ring.

Method for balancing a propulsive system having non-hull contra-rotating propellers

According to the invention, at least one of the counterweights () is mobile mounted on a guiding slot () coaxial to the hub envelope () that surrounds the hub () of the corresponding propeller (), the movement of said mobile counterweight () along said guiding slot () being controlled on the basis of an estimation of the possible unbalance of said propulsive system ().

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.

Rear part of an aircraft including an engine support structure assembled so as to oscillate on the fuselage

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Toulouse, France

Esteban Quiroz-Hernandez