Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Airbus Operations Sl

Societe Nationale Industrielle Et Aerospatiale

Alsthom

European Aeronautic Defence and Space Company Eads France

Philippe Blot

Pierre C Zahlen

Jérôme Colmagro

Tassilo Witte

Dominique Guittard

Xavier Legrand

Julien Charles

Mathieu Lannuzel

Mathieu Piana

Georgi Tsarvarishki

Gilles Bezard

Sebastien Gohier

Pascal Vinot

Julien Guillemaut

Denis Soula

Bernard Ollivaud

Ludovic Fournie

Thomas Le Hetet

Joel Bretagne

Virginie Charbonnier

Simon Deseur

Sébastien Gohier

Jean-Jacques Dittberner

Jeannick Dubillot

Stephane Chene

Cedric Gauthier

Jean-Louis Fournier

Matthieu Kneveler

Joel Besnier

Joel Chanteux

Thierry Giraudet

Joel Augereau

Romuald Guillou

Laurent Thomazeau

Xavier Lutun

Claude Le Bail

Christope Marchand

Alain Cavet

Bertrand Duthille

Serge Boude

Cédric Pupin

Marc Moret

Clément Jourdren

Matthieu Kneveller

Melania Perez-Sanchez

Cédric Belleil

Hervé Lesourne

Jean-Michel Laborie

Benoit Hochart

Stephane Bechtel

Jerome Colmargo

Christophe Marchand

Jerome Soto

Jérôme Soto

Joël Besnier

Stéphane Chéné

Cédric Gauthier

Benoît Hochart

Joël Chanteux

The disclosure proposes a method for producing a panel having an outer skin and stiffeners that have a connecting portion, and at least one projecting portion, the method comprising a step of draping layers of fibers over at least one insert such that each layer of fibers has a connecting portion and a portion that projects downwardly from the connecting portion, a step of draping a layer of fibers that forms the outer skin, and a step of bonding the layers of fibers together. The disclosure also provides a device for implementing the method.

Self-stiffened composite panel and method of producing same

A method of manufacturing a plurality of reinforcing element preforms, involving the steps of: positioning reinforcing elements on the external surface of a die; assembling the reinforcing elements thus positioned with one another so as to form a textile sleeve with a longitudinal axis and surrounding the die; moving the sleeve longitudinally toward a multi-cavity mandrel having an elongate overall shape, the multi-cavity mandrel having on its external surface a plurality of longitudinal cavities which are distributed, when viewed in cross section, around the periphery of the external surface; forming the sleeve on the plurality of peripheral cavities so that the sleeve conforms to the shape of the multi-cavity mandrel and thus adopts the shape of a set of reinforcing element preforms.

Method for manufacturing a plurality of preforms for reinforcing members

The invention relates to a process for manufacturing a textile preform from a fibrous array with continuous fibres, the process comprising a step for heating of the fibrous array between a matrix and a punch to stiffen this fibrous array. To cut down processing time, the heating step is performed by having a hot gas flow circulate through the matrix, the fibrous array and the punch.

Process for manufacturing a textile preform with continuous fibres by circulation of hot gas flow through a fibrous array

A method for producing a part made of a composite material, including a skin and at least one stiffener made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin. The method includes the steps of: producing a preform of the part by pulling the strips through a die for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die; and pressing the resulting preform in a hot press for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel.

Method for producing an extruded stiffened panel, and device for implementing same

The invention relates to a method of assembling composite material parts (). The method makes provision for:

Method for assembling elements of composite material for aircrafts, with stress relaxation in the elements

The stiffeners of a composite material panel may be protected by a structural section having a configuration absorbing edge impacts without propagation of impact energy to the protected structure. Each composite panel with protected parallel stiffeners has a multiply front face coming to an edge and extending between two lateral flanks of outside plies, symmetrically relative to a median plane (Pm). A device for protecting each stiffener includes a structural section that caps the stiffener symmetrically relative to this median plane (Pm). This structural section consists of an upper section formed above the edge and configured to envelop a space above the edge, a lower section framing the lateral flanks by longitudinal walls (Pi) fastened to these flanks, and an intermediate section bearing at least partially on the edge via transverse walls (Pb) so as to minimize the propagation of impact forces to the lower section.

Method and device for stiffener protection, and corresponding composite panel

The method of fabricating an aircraft part comprises the steps of placing in a stack comprising a preform at least one layer of a material that presents permeability to a predetermined resin that is less than the permeability of a portion of the preform that is the closest to the layer; and placing a resin presence sensor on a side of the layer that is remote from the preform.

Method of fabricating an aircraft part by infusing resin

A mold including: a central core having a side wall with a plane external surface; an internal mold element having an internal surface facing the external surface of the central core, with surfaces inclined to the vertical in order to form an angle of clearance, and a substantially vertical external surface; an external mold element fitted against the internal mold element and having a substantially vertical internal surface facing the external surface of the internal mold element; at least one of the facing surfaces being designed to receive a substantially vertical lateral preform so that the internal mold element and the external mold element are suitable for clamping said lateral preform.

Mold adapted to receive a preform of a composite part and corresponding molding method

A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.

Method for producing a central wing box

A method of manufacturing a structure, in particular an aircraft fuselage of composite materials comprising a skin () and V-section members fastened to the skin () referred to as stiffeners (). The method comprises a step of positioning punches on a mandrel in order to form channels between the punches. The channels are disposed in at least two networks (), each channel of the same network () meeting at least one channel of another network at a node (). The method also comprises a step of positioning preforms for stiffeners in the channels such that at least two stiffeners () meet at said node () and a step of injecting resin so as to assemble the stiffeners (). A structure made as a single piece is thereby obtained.

Method of manufacturing a structure comprising a skin and stiffeners

A process for the production of a fiber profile () that is designed to fill in a space with a nail-head-shaped or half-nail-head-shaped cross-section that originates from the assembly of preforms in a T shape, of which at least one includes a curvature radius at the junction zone of the preforms, includes: supplying powder-coated fibers () to a preforming station () where the powder is activated and the fibers () move into a passage whose shapes are adapted to those of the desired profile, and then making the preformed fibers move into a shaping station () where the fiber profile () is cooled and shaped by circulating in a cavity whose shapes are adapted to those of the desired profile.

Process for the production of a profile made of composite material fibers that has a half-nail-head or nail-head cross-section

A device for laying up a dry preform having an elongated shape includes a punch that reproduces the elongated shape of the dry preform, a depositing assembly, and a mobile carrier that moves at least one of the punch and the depositing assembly. The depositing assembly deposits, onto the punch, a fibrous band including a small amount of binding agent to make up the dry preform having a cross-section with at least two non-coplanar wings. The depositing assembly also includes pressing devices that press the fibrous band, a channel that pre-shapes the fibrous band to have the cross-section, and a calibration device that applies a normal pressure to all surfaces of the dry preform that are opposite from the punch while cooling the pressed portion of the fibrous band to control a thickness of the dry preform having the cross-section.

Method and device for the automated production of dry fibrous preforms

The invention relates to an automated device for implementing a drape-forming step to form a laminated fibrous preform, which is then impregnated with resin to produce a part made of composite material. The invention relates more particularly to the production of preforms for manufacturing parts such as panels, in particular very thick panels, that extend basically in two dimensions. The device of the invention comprises a manipulator able to move and orient in space a tape laying head, said tape laying head comprising: a drum comprising a suction orifice leading to its surface and able to individually grasp a length of fabric on a mounting outside the tool and the tape laying head; means designed to subsequently place this length of fabric on the preform comprising means of compacting; and means of heating the length of fabric.

Automated drape-forming device

A process for manufacturing a piece made of composite material including a fiber preform that is embedded in a matrix, includes placing the preform in a first chamber that is delimited by a first semi-sealed wall, i.e., permeable to gas and impermeable to a product that is able to form the matrix, extracting the gases in a second chamber that is delimited by a second gas-tight wall and the first semi-sealed wall so as to obtain the diffusion of the product that is able to form the matrix in the preform, characterized in that it consists in using&#x2014;as a first semi-sealed wall&#x2014;at least one plate with a number of pipes of tapered shape that empty on either side of the at least one plate and at least one semi-sealed membrane that is superposed on the at least one plate.

Method for producing a component made of a composite material and associated device

A process for manufacturing a piece made of composite material with a hollow form and including a fiber preform () that is embedded in a matrix, includes placing the preform () in a first chamber () delimited by a mold () that is in contact with the surface of the piece to be produced outside of the hollow form and a counter-mold () that is in contact with the surface of the piece to be produced inside of the hollow form, and using a mold () that is made in at least two parts () and elements () for controlling the spacing of the at least two parts () that are contiguous using the expansion phenomenon during the polymerization phase.

Method for producing a concave-shaped in particular U-shaped piece in a composite material and device for carrying out the same

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Nantes, France

Philippe Blot