Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

Antoine Cousin

Laurent Caliman

Jérôme Gaillardo

Jerome Cassagne

Lionel Czapla

Thomas Deforet

Florian Ravise

Pascal Gardes

Frédéric Ridray

Laurent Cazeaux

Simon Vanderbauwede

Lionel Sillieres

Denis Brossard

Antoine Boudou

Claire Maffre

A turbofan with a sliding element, rotary blades that can rotate between stowed and deployed positions, and a maneuvering system which moves each blade when the sliding element moves and which includes, for each blade, a rotary main shaft, for each main shaft, a transmission lever rigidly secured to the main shaft, at least two connecting strips articulated to one another, wherein each connecting strip is associated with at least three main shafts, the transmission levers of which are articulated to the connecting strip, and a drive system which rotates the first connecting strip when the sliding element moves. The use of rotary blades on the sliding element and the simplified maneuvering system makes the assembly more lightweight compared to the use of conventional reverser doors.

Turbofan comprising a series of rotary blades for closing off the duct for the secondary stream

An aircraft nacelle including an automatically-operated locking device for limiting deformations of the cowl. This automatically-operated locking device includes at least one locking post connected to the cowl, at least one latch able to move between a first position corresponding to a locked state in which the latch prevents the locking post from becoming distanced from a fixed structure and a second position corresponding to an unlocked state in which the latch allows the locking post to become distanced from the fixed structure, at least one return system configured to hold the latch in its second position corresponding to the unlocked state, the cowl holding the latch in its first position when the cowl is in the closed position and allowing the latch to pivot toward its second position when the cowl is in the open position.

Aircraft nacelle comprising a cowl and an automatically-operated locking device that limits the deformation of the cowl

An acoustic absorption structure comprising a plurality of resonators. Each resonator comprises a first chamber which has a first mouthpiece delimited by an edge pressed against an inner surface of a porous zone of a skin so that the first chamber and the skin delimit a first cavity, a second chamber, in which is positioned the first chamber, which delimits, with the first chamber, a second cavity, at least one acoustic orifice passing through the first chamber, at least one drainage orifice passing through the first chamber and at least one drainage hole passing the second chamber, each drainage orifice and each drainage hole being configured to limit an accumulation of fluid in the resonator. Also, an aircraft propulsive assembly or an aircraft comprising the acoustic absorption structure are provided.

Acoustic absorption structure comprising a liquid drainage system and propulsive assembly comprising such an acoustic absorption structure

A turbofan engine with a nacelle including a runner translationally mobile between advanced and back-off positions to open a window between a stream and an outside, a plurality of blades, each rotatable on the runner between retracted and deployed positions, and a maneuvering system displacing each blade and comprising, for each blade, a shaft rotatable on the runner and to which the blade is fixed, and a toothed segment on the shaft, and a toothed arc rotatable on the runner about a longitudinal axis, the tooth arc teeth meshing with the toothed segment teeth, a slip translationally mobile on the runner in a plane at right angles to the longitudinal axis between first and second positions, a connecting rod mounted articulated between the slip and the toothed arc, a rib integral to the fixed structure, and a guiding U integral to the slip and which straddles the rib.

Turbofan engine comprising a series of rotary blades for blocking the stream of the bypass air

A nacelle comprising a fixed structure with a fixed cowl and a duct, a mobile assembly with a chassis forming a frame and a mobile cowl, the chassis being mobile, relative to the fixed structure, in translation between an advanced position and a retracted position to open an opening through the frame between the duct and the outside. The mobile assembly comprises at least one threaded rod parallel to the direction of displacement and fixed to the chassis through the frame. The fixed structure comprises an outer, an inner, and at least one intermediate box fixed to the inner box and to the outer box. For each threaded rod, the fixed structure comprises a motorized ball nut which meshes with the threaded rod, and an actuator which turns the ball nut and is fixed to at least one box from among the outer, the inner, or the intermediate box.

Jet engine nacelle comprising a mobile assembly and a reinforced fixed structure

A turbofan having a nacelle including a slider mobile in translation between advanced and retracted positions to open a window between a duct and the exterior, a plurality of blades, each being mobile in rotation on the slider between stowed and deployed positions, and a maneuvering system that moves each blade and includes, for each blade, a shaft mobile in rotation on the slider and on which the blade is fixed, an arm having a first end fixed to the shaft and a second end, an arc which is coaxial with the longitudinal axis and is rotatably mounted on the slider, about the longitudinal axis, a lever mounted in articulated fashion between the arc and the second end of the arm, and an actuation system which rotates the arc in one direction and in the other.

Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct

An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle.

Engine fastener for an aircraft

An aircraft engine mounting device attachment arrangement includes a fitting perforated with two orifices, and two ball joints respectively housed in the orifices. The arrangement also includes two anti-rotation systems used to lock the ball joints in their orifices, the system including a main plate traversed by an external ring of the ball joint and including tappets cooperating with notches provided on the ring, the system including a main plate traversed by a main plate of the ball joint and including tappets cooperating with notches provided on the ring. In addition, the plates are connected rigidly to each other.

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L'Union, France

Antoine Cousin