Airbus Operations (s.a.s.)

Airbus France

Aerospatiale Societe Nationale Industrielle

Airbus (sas)

Aerospatiale Airbus

Societe Nationale Industrielle Et Aerospatiale

Tecalemit Flexibles

Airbus Operations Gmbh

Eads Airbus Sa

Creuzet Aeronautique

Aerospatial Natra

Rolls-royce Corporation

Airbus Corporation

Alain Porte

Jacques Lalane

Frédéric Chelin

Robert Andre

Gregory Albet

Matthieu Fargues

Michel Buge

Damien Prat

Fabrice Gantie

François Pons

Eric Rambaud

Frédéric Vinches

Arnaud Bourhis

Patrick Oberle

Thierry Surply

Arnaud Hormiere

Gilles Chene

Franck Dobigeon

Stéphane Dida

Julien Sentier

Grégory Albet

Florian Ravise

Franck Alvarez

Florent Mercat

St&eacute;phane Levert

Jonathan Carcone

Emeric Chancerelle

Herv&eacute; Batard

Frédéric Piard

Maxime Zebian

Eric Haramburu

Jean-Marc Martinou

Pascal Jule

Hassan Menay

Lionel Czapla

Wolfgang Brochard

Julian Mark Reed

Jean-Marc Poignonec

Herve Marche

Benjamin Thubert

Vincent Rebeyrotte

Olivier Barbara

Wolfgang Rehm

Benoit Letay

Bernard Duprieu

Thomas Sauvalle

Thomas Stevens

Danilo Ciprian

Francois Pons

Nicolas Jolivet

Martial Marro

Herve Batard

Maud Lavieille

Clément Breton

David Lambert

Nathalie Pascal

Francedillaois Cros

Franck Oundjian

Valerie Frustie

Cedric Leconte

Nathalie Papin

Sylvain Thezelais

Bruno Medda

Bruno Legeay

Franck Le Flem

Vincent Billerot

Jean Michel Rogero

Alain Dega

Thomas Gilles

Fabienne Montetagaud

Jacques Barillot-Creuzet

Caroline Halliday

Marie-Luce Zanarelli

Marie Jazet

José Manuel Martin-Oquina

Philippe Fourest

Pascal Dublineau

Hervé Batard

Irene Moreno Gonzalez

Arnulfo Carazo Mendez

St&eacute;phane Viala

Jule Pascal

Thierry Colcombet

Benoit Przybyla

Franck Colcombet

Alain Garcia

Jean-Claude Tchavdarov

Jean-Louis Lasserre

Théo Riccobene

Guillaume Ring

Theo Riccobene

Pascal Galletti

Jerome Dewitte

Emmanuel Cayrol

Nicolas Casse

Philippe Descamps

David Wattam

Jose Manuel Martin-Oquina

Stephane Viala

Valérie Frustie

A strip-form acoustic material, the strip having a length in a longitudinal direction, a width in a transverse direction, a thickness and axial ends. At least one of the axial ends of the strip, in an end portion of the length of the strip, the strip of material is folded in a substantially transverse plane.

Strip-form acoustic material having an integrated flange, and internal wall of an aircraft air intake made with this material

A resistive skin shell for an acoustic panel or inner wall of an aircraft air intake, comprising an alternation, in a transverse direction, of perforated metal bands and of composite solid bands extending in a longitudinal direction. The perforated metal bands and the composite solid bands form a smooth outer face configured to be in contact with an aerodynamic stream, and a crenelated inner face. The composite solid bands have a thickness greater than the perforated metal bands. Since the perforations are provided in metal bands, which are intrinsically resistant to wear and erosion, the future proofing of the acoustic performance of the resistive skin is guaranteed. Since the composite solid bands, which are thicker, can ensure the mechanical strength of the skin, the thickness of the perforated metal bands can be reduced, allowing perforations with dimensions that are also reduced, having a lower impact on drag.

Resistive skin shell incorporating perforated metal bands, and acoustic inner wall of an aircraft air intake formed from such resistive skin shells

An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.

Anterior part of a nacelle for an aircraft propulsion assembly, whose front frame is connected to an outer wall without penetrating it

A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

Method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device

A cellular sound insulation structure and associated aircraft, a cell of which is provided with a diaphragm which includes a membrane having at least one orifice passing through a thickness of the membrane, and at least one tube surmounting the orifice and extending from a face of the membrane into one compartment of the cell, the tube comprising a free end, forming an acoustic outlet, which is positioned at a distance (p) from the base cross section of the cell. Also, a method for manufacturing such a cellular sound insulation structure, as well as to a tool for inserting a diaphragm into a cell. Such a cellular structure makes it possible to treat a wider acoustic frequency spectrum, and its acoustic dimensioning as well as its manufacture are simplified.

Cellular sound insulation structure including a diaphragm provided with a tube configured to treat different acoustic frequencies, method for manufacturing such a cellular sound insulation structure, and associated tool

An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

Method for manufacturing an acoustic panel having a capsular skin, and acoustic panel incorporating such a skin

A method for producing an alveolar soundproofing structure in which a portion of a membrane of a diaphragm including an acoustic outlet is inserted into a hole of a perforated membrane which covers a cell of the alveolar structure, and the diaphragm is pressed into the cell with the perforated membrane becoming deformed and is fixed at that location. It also relates to the alveolar structure. Such a method enables different types of diaphragms to be inserted into different configurations of cells and enables the diaphragm to be fixed therein, in accordance with the sound frequencies to be processed.

Method for producing an alveolar soundproofing structure including a diaphragm, and alveolar soundproofing structure obtained

A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

Turbofan engine comprising a system for blocking the flow path of the bypass stream comprising veils

An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.

Multifrequency absorption acoustic panel for an aircraft nacelle

A method for manufacturing two soundproof panels of an aircraft nacelle including a duct. The manufacturing method includes a step of supplying a mold having, on a single face, a cavity for each soundproof panel, a step of producing, in the bottom of each cavity, an inner skin for being oriented towards the duct, and a curing step during which the elements present in the mold are cured in the mold. Such a method makes it possible to produce the two soundproof panels in the same mold, thus reducing the gaps between them after they have been positioned.

Method for manufacturing two soundproof panels in the same mold using two mold cavities

An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.

Aircraft engine nacelle provided with an icing protection system and associated protection method

A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.

Sound-absorbing panel with a cellular core and a de-icing system

A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

Nacelle of an aircraft propulsion assembly comprising a plurality of damper elements between a front section and a main section, and associated aircraft propulsion assembly

An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between &#x2212;20&#xb0; and +10&#xb0; over the majority of the thermal transition region.

Anterior part of a nacelle of an aircraft propulsion assembly having a thermal transition region

An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of 'recycled' sector is also described.

Air intake, nacelle and propulsion unit for monobloc sector aircraft

Growing community of inventors

Colomiers, France

Alain Porte