Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations (societe Par Actions Simplifiee)

Airbus Operations Gmbh

Airbus Corporation

Eric Haramburu

Patrick Oberle

Alain Porte

Frédéric Piard

Laurent Sammito

Jean Larrochelle

Vincent Billerot

Franck Oundjian

Thierry Surply

Benoit Letay

Thomas Sauvalle

Nicolas Jolivet

Grégory Albet

Eric Masson

An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between &#x2153; and &#x2159; of the total chord between the stop point and the assembly point.

Air intake structure for an aircraft nacelle

A nacelle includes a fixed structure supporting a fixed cowl and a movable cowl, the movable cowl being movable translationally between a closing position and an opening position. A blocker door is movably mounted rotationally on the nacelle between a closed position and an open position. The nacelle includes a drive mechanism of the blocker door and of the movable cowl between the closed/closing position and the open/opening position of the blocker door/movable cowl, respectively, and vice versa, the drive mechanism includes at least one actuator fixed, to the fixed structure of the nacelle and, to a fitting fixed to the movable cowl. The drive mechanism includes, for each actuator, a flexible member having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.

Turbojet engine nacelle comprising a thrust reverser drive mechanism

A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Turbofan nacelle including a reverser flap

A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

Jet engine nacelle having a reverser flap

An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Engine mounting structure for aircraft having a beam spreader connected at four points

An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system.

Engine mounting structure for aircraft with a rear engine attachment beam forming a spreader beam

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Colomiers, France

Eric Haramburu