Airbus Operations (s.a.s.)

Aerospatiale Societe Nationale Industrielle

Airbus France

Airbis Operations S.a.s.

Airbus Operations Gmbh

Christian Fabre

Guillaume Bulin

Patrick Oberle

Alain Bignolais

Jean-Michel Rogero

Paolo Messina

Philippe Mangon

Herve Magnin

Thomas Bourdieu

Hervé Magnin

Christophe Bourdet

Stéphane Pugliese

A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.

Pivoting connection device between at least two components, aircraft comprising a cowl provided with said pivoting connection device

A method and equipment for installing a tapped insert in a cylindrical bore, the equipment including a tool body comprising a threaded end portion, the threaded end portion being adapted to a threaded inner wall portion of a cylindrical body of the tapped insert; a screw of diameter lower than a diameter of an inner bore of the tool body, the comprising at one end a thread complementary to the inner tapped aperture of the core of the tapped insert; and a positioning ring installed to slide on the tool body, the tool body and the positioning ring comprising complementary sliding means adapted to enable relative sliding of the positioning ring on the tool body in a longitudinal direction and to maintain the positioning ring on the tool body in a defined longitudinal transverse section.

Tapped insert for cylindrical bore and installation equipment for such insert

A stopper for a tank having an opening includes a body which is provided to be fixed in the opening and which has a hole, a membrane which is fixed to the body and of which a portion completely blocks the hole, a core which is fixed to the portion of the membrane which blocks the hole, and stop means which are provided to permit a movement of the core between a blocking position which corresponds to the non-broken membrane which blocks the hole, and an open position which corresponds to the broken membrane which is spaced apart from the hole, and to keep the core fixedly joined to the body in an open position. The knowledge of the characteristics of the membrane enables the force from which the stopper opens to be known.

Membrane type stopper

A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.

Fan cowl locking system

The invention relates to an aircraft turbojet nacelle including a cowling assembly () made up of four covers (). Each cover extends in arcuate shape around part of the longitudinal axis of the nacelle, in symmetrical manner about a vertical plane (P) containing the axis. On either side of said plane, the cowling assembly comprises a top cover () hinged at its top portion and a bottom cover () hinged at its bottom portion. Access to the internal space () of the nacelle is obtained by moving the covers away from the longitudinal axis by pivoting them about their hinge axes. A top cover is less heavy for handling purposes than is a single cover of the prior art.

Aircraft turbojet nacelle

A latching system for selectively securing together two components, such as the fan cowl doors of a nacelle of an aircraft, closed. The latching system generally includes an anchor and a latch. The latch has a handle movable from an open and a closed position. The handle is precluded from reaching the closed position unless the anchor and latch are secured. Also, the positioning of a keeper portion of the anchor may be adjustable.

Latching system for securing two components

The present invention relates to a tapped insert for cylindrical plain bore () of a part Acomprising a cylindrical body (), characterized in that said cylindrical body () comprises an inner bore () of frusto-conical shape, and at least one longitudinal slot (') extending into the cylindrical body () and communicating with said frusto-conical inner bore () and characterized in that the tapped insert also comprises a core () of frusto-conical shape complementary with said frusto-conical inner bore () of the cylindrical body (), said core () comprising a inner tapped aperture (), said cylindrical body () and said core () being such that said tapped insert can be holded in position and locked in said cylindrical bore () to equip said cylindrical bore with an inner taping.

A fluid ejection device for example used as a fire extinguisher in which ejected fluid is an extinguishing agent in liquid or powdery form. The device includes: a cylinder shaped tank, split hermetically, perpendicular to its axis, into two chambers by a piston, slidable axially inside the tank; a first chamber, including a non-gaseous fluid, which communicates with an ejection port closed by a cap, which can open for a pressure greater than or equal to a defined pressure in the first chamber; a second pressurization chamber to be connected to a mechanism increasing pressure in the chamber; and a mechanism to link the piston to the tank in full fixity at a storage position, which mechanism can break and release the piston for axial translation at a pressure higher than or equal to a given pressure in the pressurization chamber, to cause the fluid to be ejected.

Fluid ejection device

A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades.

Deicing device for propfan-type propeller blades

A spigot-type fastener for an aircraft is to be interposed between the structure of the aircraft and an attachment structure of the aircraft engine. The fastener is to absorb the force generated by the engine along two orthogonal axes. The fastener includes a first part, a second part, a third part, and one or more strain gauges. One end of the first part is secured to the second part. One end of the second part is separated from the first part by a clearance. The opposite end of the second part fits into a recess of the third part via a protrusion, such that the force along both axes is transmitted by the first part to the third part by the second part.

Spigot-type fastener provided with at least one means for measuring the force generated by an aircraft engine

A compact device for ejecting a fluid including two chambers separated by a separating element of piston type. One of the chambers contains the fluid intended to be ejected, the other chamber is a pressurization chamber, the pressurization of which can cause translational movement of the separating element and ejection of the fluid. The pressurization chamber includes a thimble capable of sealably separating the inside of the pressurization chamber from the side walls of the reservoir. Thus, a seal between two chambers is perfect and durable without degrading slidability of the piston.

Fluid ejection device with reinforced seal

A device for aiding the localization of an aircraft wreck submerged in a sea is arranged inside the aircraft. The device includes at least one beacon that is able to emit remotely detectable signals. Upon immersion of the aircraft in water, an ejection device automatically ejects the beacon out of the aircraft. The ejection device includes a piston system that generates an opening in the aircraft and expels the beacon accordingly. Also after immersion of the aircraft in water, a trigger device automatically triggers the emission of signals from the beacon.

Method and device for aiding the localization of an aircraft wreck submerged in a sea

A fire extinction device comprises a reservoir () of extinguishing agent and means for generating a pressurized gas () such that the gas generated () may enter the reservoir () when the extinguishing agent () is to be ejected onto a fire zone. The device of the invention comprises furthermore a refractory separating element () between the extinguishing agent () and the pressurizing gas generated (), in order to avoid heat exchanges between them and to optimise the ejection of the extinguishing agent ().

Device for increasing the effectiveness of the pressurizing gas in an extinguisher bottle

A device for mechanically linking with a rotating axis at least two parts, which is configured to extend in a longitudinal direction in coaxial bores formed respectively in the at least two parts hinged in relation to each other around the axis. The device includes: a cylindrical body including at least one end portion including at least one longitudinal slot, the cylindrical body including in the longitudinal direction a cylindrical bore extended by a frusto-conical bore extending in the at least one end portion configured to be located in another bore; an insert of frusto-conical shape substantially complementary to the frusto-conical bore, the insert including a tapped aperture extending in the longitudinal direction when the insert is accommodated in the frusto-conical bore, and a screw with a threaded end configured to cooperate by screwing with the tapped aperture of the insert allowing to lock the cylindrical body in the another bore and making a rotoide joint around axis.

Growing community of inventors

Tournefeuille, France

Christian Fabre