Airbus Operations (s.a.s.)

Airbus France

Eads Airbus Sa

Airbus Operations Gmbh

Denis De Mattia

Gilles Batard

Mathieu Lannuzel

Olivier Chaume

Aurelien Boyeldieu

Olivier Guillemot

Christian Vivier

Bernard-Albert Colin

Bernard Colin

Sebastian Gohier

Sébastien Quillaud

Bruno Burel

An effector includes at least one contact surface configured to bear against a face of a workpiece near a zone of the workpiece that is impacted by a tool supported by the effector. The contact surface includes at least one interface made of a ductile material interposed between the contact surface and the face of the workpiece.

Effector comprising a contact surface having an interface made of a ductile material

A method of manufacturing a curved profile from a rectilinear preform of pre-impregnated fiber plies. The method includes stacking plies on a deformable mandrel and winding the deformable mandrel and the stacked plies on a bending tool along a rotation axis, the profile comprising a stack of N plies. At least one first section of the profile is arranged along a plane perpendicular to the axis of rotation and at least one second section is arranged in a plane parallel to the axis. The method includes the steps of stacking the N plies of fibers on the deformable mandrel, bending in a single step the N plies sandwiched between the deformable mandrel and the bending tool and polymerizing the bent N plies. The curved profile comprises M plies with fibers oriented at A&#xb0; relative to a longitudinal direction and M+/&#x2212;5% plies with fibers oriented at &#x2212;A&#xb0;.

Method of manufacturing a curved profile made of composite material from a rectilinear preform of fiber plies

A method for detecting a spacing defect between two adjacent strands of a layer of a fiber fabric includes positioning of the fiber fabric on a metal plate, the fiber fabric covered by an air-tight casing, removing air from between the metal plate and the casing, displacing an inductive sensor relative to the fiber fabric and identifying a defect based on a signal generated by the inductive sensor.

Method for detecting a strand gap in fiber fabric and a device for its implementation

The subject matter disclosed herein relates to a method for assembling at least one panel and frames for producing part of an aircraft fuselage, the method including shaping the panel on support surfaces of a tool, wherein it includes holding each frame clamped against at least one sliding support surface arranged in a transverse plane, the sliding support surfaces of the various frames and the support surfaces being secured to the same tool and positioned relative to one another, and in putting in place permanent attachment elements for connecting the panel and the frames. The subject matter disclosed herein also proposes a tool for implementing the assembly method.

Method for producing part of an aircraft fuselage and tool for implementing said method

A method of laying up a segment on a layup surface using a layup head that is mobile with respect to the layup surface, the layup head supporting a spool of a tape of material which includes at least one layer to be laid up from which said segment is cut and at least one interliner, the method including applying the tape of material against the layup surface and removing the interliner using a separator. The tape of material is pressed firmly by a press roller against the layup surface before the interliner is removed as the layup head moves in an advancing movement. A layup head for implementing the method and a layup machine including the layup head are also described.

Method for laying up a tape of material and device for implementing same

A method for producing, in a composite material, a component that has a re-entrant angle, includes stacking layers of fibers which have been pre-impregnated with a resin so as to obtain a preform and placing the preform in a tooling fixture in order to subject it to a polymerization cycle including a temperature cycle, with a temperature-increase phase and at least one soak at which the temperature is maintained, and a pressure cycle on the outside of the tooling fixture with a pressure-increase phase and a pressure-hold phase, with the layers of pre-impregnated fibers being able to slip against one another when the temperature of the temperature cycle is equal to or higher than a threshold temperature Tf dependent on the resin. The temperature-increase phase includes a soak at a temperature higher than or equal to Tf, the soak beginning before the end of the pressure-increase phase.

Method for producing a profile that has a re-entrant angle in a composite material from a stack of layers of fibres

A method for producing a fiber preform by winding at least one thread in a groove of a mold. The method involves using a flexible element which is capable of becoming deformed by means of flexion, in a plane which contains the winding axis, in order to penetrate into the groove in order to push the sections of the thread(s) towards the base of the groove and/or towards zones which cannot be accessed directly by the thread(s). A set of tools for implementing the method is also provided.

Method for producing a fiber preform by means of winding and set of tools for implementing the method

A device for machining a slot on a surface of a cellular structure includes a machining head that includes a chassis, a rotary tool rotating about a tool axis perpendicular to the direction of the slot, two guide wheels arranged on either side of the rotary tool that have a plurality of teeth configured and positioned such that they penetrate the cells of an alignment of the cellular structure. The machining head includes a link between the chassis and at least one guide wheel that enables a degree of freedom in a lateral direction parallel to the tool axis such that the guide wheel is movable in relation to the rotary tool in the lateral direction.

Surface machining device for a cellular structure

A method for testing a batch of material used to obtain layers of fibers includes taking a specimen from the batch of material, exerting a tensile force on the specimen, heating the specimen so as to relax the fibers if the specimen contains stresses, after a predetermined period of time, no longer heating and no longer exerting the tensile force on the specimen, measuring a residual extension of the specimen which corresponds to a variation in length of at least a part of the specimen in the direction of the tensile force, before and after the tensile force, and considering the batch of material not to be compliant if the residual extension exceeds a given threshold.

Method for testing a batch of material used for obtaining layers of fibres intended for manufacturing a composite material component

A device for deposition of fibers on a support () for producing a panel with an axis of revolution, includes a deposition head () and elements for positioning the deposition head relative to the support (), with the positioning elements of the deposition head having kinematics including a first translation in a first direction (X) that is parallel to the axis of revolution, a second translation in a second direction (W) making it possible to come more or less close to the head of the support, a first rotation (C) around a first rotary axis combined with the second direction (W), and a second rotation (B) around a second rotary axis that is perpendicular to the first and second directions, wherein the kinematics of the positioning elements of the head include a third rotation (A) around a third axis of rotation that is parallel to the first direction (X).

Device for deposition of fibers upon a frame with concave circular sections

A method for machining a through-hole in a wall of a component, includes setting in rotation on itself a cutting tool about a rotation axis and setting the rotation axis of the tool in rotation about a first orbital rotation axis parallel to, and eccentric by an eccentricity E with respect to, the rotation axis of the tool. The method further includes setting the first orbital rotation axis in rotation, over at least one revolution, about a second orbital rotation axis parallel to, and eccentric by an amount f with respect to, the first orbital rotation axis, the eccentricity being fixed. This configuration makes it possible to balance the elements located between the rotation axis of the tool and the first orbital rotation axis, so that the rotation axis can thus be set in rotation about the first orbital rotation axis at high rotational speeds that contribute toward increasing productivity.

Method for machining a through-hole in a component and machining device for implementing the said method

A tool for machining a curved profile along an axis of rotation X, said curved profile comprising at least one first section along a plane perpendicular to the axis of rotation X and at least one second section parallel to the axis of rotation X. The tool includes blocks, each having a clamping surface against which the profile can take support. The blocks include positioning elements against which the first section and the second section of the profile can take support, and an apparatus arranged to immobilize the profile which is adapted to occupy a first activated state, wherein it immobilizes the profile, and a second deactivated state, wherein it does not immobilize the profile. The tool includes manual presses for maintaining the profile flattened against the positioning elements until the profile immobilizing apparatus is in the activated state.

Machining tool for an aircraft fuselage frame

A method for producing a curved section piece from a rectilinear preform of preimpregnated fiber layers includes stacking layers on a deformable mandrel and winding the mandrel and bending the stacked layers on a bending tool on a rotation axis in a single phase and polymerizing the bent layers. The section piece includes a stack of N layers, at least a first portion of which is placed in a plane perpendicular to the rotation axis (X) and at least one second portion parallel to the axis (X) including at least one layer of fibers oriented at 0&#xb0; along the length of the perform. The N fiber layers are stacked on the mandrel. A neutral fiber is placed on a portion of the mandrel closer to the rotation axis (X) than the last layer of fibers oriented at 0&#xb0; stacked on the 0second portion parallel to the rotation axis (X).

Method for producing a curved section piece of composite material from a rectilinear preform of fibre layers

A method for obtaining a composite material part from a preform of layers of fibers pre-impregnated with resin stacked on top of one another on a tool, the preform being delimited by a lower surface, an upper surface, and a peripheral flank. The method includes attaching to the tool, after the last layer has been laid, a peripheral part comprising a wing adapted to cover the peripheral edge of the upper surface, so as to create, in the periphery of the preform, a peripheral cavity adjacent to the flank of the preform and, before the polymerization phase, to withdraw the gas present in the peripheral cavity so as to tension filaments of the preform by exerting a traction force at the ends of the filaments.

Method for obtaining a composite material part incorporating a tensioning step of the filaments and tool for its implementation

A method for producing a curved profile from a rectilinear preform of preimpregnated fiber webs, including stacking webs on the deformable mandrel and winding the deformable mandrel and the stacked webs on a bending tool along an axis of rotation (X), the profile including a stack of N webs, at least one first part of the profile being positioned in a plane perpendicular to the axis of rotation (X) and at least one second part parallel to the axis (X) whereof a face can be in contact with the bending tool. The method includes stacking the N fiber webs on the deformable mandrel, generating a heat gradient between the face and the rest of the preform that is hotter than the face, bending, in a single phase, the N webs inserted between the deformable mandrel and the bending tool, and polymerizing the N bent webs.

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Basse Goulaine, France

Denis De Mattia