Airbus Operations (s.a.s.)

Aerospatiale Societe Nationale Industrielle

Airbus France

Eads Airbus Sa

Airbus Operations Gmbh

Robert Andre

Alain Porte

Matthieu Fargues

Eric Rambaud

Michel Buge

Benoit Letay

Loic Dussol

Benjamin Saget

Herv&eacute; Batard

Eric Inghelbrecht

An aircraft nacelle includes an air intake () followed at the upper part by a part () integral with the mast, called a cap, and at least one door () with a curved profile, and a device for encircling it in the form of at least one flexible element (), guide elements () for allowing the at least one flexible element () to follow the curved profile of the at least one door, a first anchoring point () of the at least one flexible element () integral with a first edge () of the cap and another anchoring point of the at least one flexible element () integral with a second edge () of the cap, whereby the anchoring points () allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap () and the at least one door ().

Device for shrouding an aircraft nacelle

A closing system for a fan cowling on a jet engine of an aircraft that has at least one assembly including a male contrivance integral with the cowling, and a female contrivance integral with the jet engine that has a lower element forming at least one first guide ramp and an upper element forming at least one second guide ramp, with the aforementioned female contrivance being suitable on the one hand for guiding the male contrivance during the opening and/or the closing of the fan cowling, and on the other hand providing a limitation of the radial and circumferential displacements of the male contrivance.

Closing system for an aircraft fan shroud

An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes:

Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Nacelle for aircraft comprising means of reversing thrust and aircraft comprising at least one such nacelle

Stiffening means are added into an air intake structure of an aircraft engine nacelle, to stiffen this structure, in order to prevent any modification to the shape of the structure, for example following suction of the intake lip inwards the fan duct. The stiffening means pass through the structure diagonally, in other words one of their ends is fixed, for example, in the forward direction and externally, and the other end is fixed in the aft direction and internally. These stiffening means may be added to the existing forward and aft stiffening frames.

Air intake structure for aircraft engine

A multi-component acoustically resistive layer, for acoustical attenuating panels having a cellular core () flanked, on the sound wave arrival side, with an acoustically damping layer () and, on the opposite side, with a rear reflector (), comprises a first structural component () in contact with the aerodynamic flow and formed by at least one layer of fibers connected by a suitable resin and oriented in the direction of aerodynamic flow the component () comprising a suitable quantity of open surface; a dissipating component () disposed against the surface of the first component () opposite the flow, formed by a metallic cloth; and a second structural component () formed by at least one layer of fibers connected by a suitable resin, oriented orthogonally to the direction of aerodynamic flow. The second structural component () is connected to the cellular core () and comprises a suitable open surface quantity.

Multi-component acoustically resistive layer for acoustical attenuation panel and panel thus obtained

A process for producing an acoustically resistive layer, particularly for the nacelles of aircraft jet engines. The process includes producing a structural component by using thermoplastic resins, this component having a given quantity of open surface relative to the acoustic waves to be treated. The structural component is connected to an acoustic metallic fabric having a mesh adapted to the open surface quantity of the structural component. Then, the thermoplastic resin is heated under pressure at high temperature.

Process for the production of an acoustively resistive layer, resistive layer thus obtained, and wall using such layer

An air inlet cowl for a jet engine, particularly an aeroengine, includes a leading edge deicer, a hollow leading edge defining an internal peripheral chamber, closed by a first internal partition, and an exhaust orifice, in the leading edge, connecting the internal chamber with the outside. The cowl further includes a pressurized hot air feedpipe for being connected, at its rear end away from the leading edge and passing through a second internal partition, to a pressurized hot air circuit and, at its front end toward the leading edge, to an injector of pressurized hot air into the internal chamber, a protective internal casing functioning with the first and second internal partitions to define an isolation volume enclosing the feedpipe, and an air extraction opening, in the first partition, to place the isolation volume in communication with the internal peripheral chamber. The area of this extraction opening is such that, in the event of damage to the feedpipe, the elimination of pressurized hot air in the isolation volume does not impair the protective internal casing and the injector injects into the internal chamber a pressurized hot air flow rate at least equal to 50% of the hot air flow rate in the feedpipe.

Air inlet cowl for a jet engine, provided with deicing means

A panel of composite material, in particular with a thermosetting or thermoplastic matrix, with edges and/or external surface protected from shocks and erosion, for any streamlining element for housings or nacelles of aeronautical motors, comprises, over all or a portion of its edges, a cladding which forms a border overlapping the two opposite surfaces of the panel. The border comprises a metallic cloth connected to the structure of the panel by an adhesive agent, diffused through the cloth. The panel is particularly applicable to aircraft.

Composite material panel with shock-protected edges

The object of the invention is a process for the production of a monolithic composite panel provided to be articulated on a support, particularly a panel articulated by hinges ( ) for the production of a fan hatch of a turbo reactor or of a landing gear door in an aircraft, the panel comprising openings for the emplacement of elements ( ) of service such as access doors, ports and/or ventilating grilles, characterized in that it consists in providing a network of beams ( ) as a function of the openings, avoiding the emplacements of the service elements, shaped and positioned for taking up the transmission of forces particularly between the articulation device and the panel. The invention also covers the panel obtained and the hatch particularly for use in an aircraft.

Method for making a composite panel and resulting panel

An acoustically resistive layer comprises at least one layer (,) of acoustic damping cloth and a reinforcing material comprising a sheet (,) of filaments (,) secured to the acoustically damping cloth. The filaments (,) are disposed unidirectionally, bidirectionally or multidirectionally. A process for producing such an acoustically resistive layer, comprises positioning an acoustically damping cloth (,) on a mold (,) having the shape of the layer to be obtained, and disposing on this acoustically damping cloth filaments (,) impregnated with a binder by filamentary winding, and then withdrawing the layer thus obtained from the mold, or by laying with application of pressure, and withdrawing the layer thus obtained from the mold.

Acoustically resistive layer, process for production of this layer and absorbent acoustic panel provided with at least one such layer, as well as its process for production

In an aircraft turbine, an assembly consisting of an air inlet structure, a air blower housing (22) and a connecting part (36), is fitted in such a way as to reduce noise including in the junction area between the structure and the housing. The connecting part (36) is fastened onto a rear section (20'), not provided with a honeycomb core, of the internal wall (20) of the air inlet structure. A honeycomb structure (44) is fitted inside the air blower housing (22). The space inside the rear section (20') houses a forward extension (44') of the honeycomb structure (44), or a different honeycomb structure.

Growing community of inventors

Lacroix Falgarde, France

Robert Andre