METHOD FOR MANUFACTURING A T-SHAPED COMPOSITE PART BY RESIN-TRANSFER MOULDING

Ce procédé de fabrication d'une pièce composite en T par moulage par transfert de résine, comprend les étapes consistant à : - constituer une préforme avec un empilement sensiblement plan (A) de plis et avec deux empilements en L (B, C) de plis, - placer ladite préforme de sorte que lesdits empilements en L (B, C) se retrouvent entre deux noyaux (M1, M2) d'un outil de moulage (M) par transfert de résine, - faire entrer et ressortir des fibres à travers ledit empilement plan (A) selon une direction perpendiculaire ou quasi-perpendiculaire à cet empilement (A) et de manière à former des boucles (b) à l'intérieur des parties (81, 82) desdits empilements en L (B, C) qui sont sensiblement perpendiculaires audit empilement plan, - fermer l'outil de moulage (M), - injecter de la résine dans l'outil de moulage (M), et à - chauffer l'outil de moulage (M) de manière à durcir la résine.

METHOD FOR PRODUCING A COMPOSITE SANDWICH PANEL WITH A HONEYCOMB CORE

La présente invention se rapporte à un procédé de fabrication d'un panneau sandwich composite (1,100) à âme alvéolaire (2) présentant une pluralité d'alvéoles (4) délimitées chacune par au moins une paroi formée à partir d'au moins une cloison (5,150), caractérisé en ce qu'au moins une partie desdites cloisons sont intégrées à une peau support (3) du panneau sandwich lors d'une étape de moulage de résine; ainsi qu'à un tel panneau obtenu par ce procédé. The present invention relates to a method for manufacturing a composite sandwich panel (1,100) with a cellular core (2) having a plurality of cells (4) each delimited by at least one wall formed from at least one partition (5,150), characterized in that at least a portion of said partitions are integrated with a support skin (3) of the sandwich panel during a resin molding step; as well as to such a panel obtained by this method.

METHOD FOR PRODUCING FOAM PANELS, ESPECIALLY FOR THE FIELD OF AERONAUTICS

The present disclosure is related to a method for producing a cellular panel which includes a cellular structure sandwiched between first and second stiff skins. The method includes the following steps: preparing at least two blocks of cellular material; disposing the two blocks on a base ply of dry fabric, while maintaining a space between the two blocks; folding the base ply around the two blocks so as to envelop the two blocks; filling in the space with a reinforcing ply; covering the base ply with a covering ply, on a side where the reinforcing ply has been introduced; injecting resin to an assembly obtained in the previous step; and curing the assembly. 1. A method for producing a cellular panel comprising a cellular structure sandwiched between first and second stiff skins , said method comprising the following steps:preparing at least two blocks of cellular material;disposing said at least two blocks on at least one base ply of dry fabric, while maintaining a space between said two blocks;folding said at least one base ply around said two blocks so as to envelop said two blocks;filling in the space with at least one reinforcing ply;covering said base ply with at least one covering ply, on a side where said at least one reinforcing ply has been introduced;injecting resin to an assembly obtained in the previous step; andcuring the assembly.2. The method according to claim 1 , wherein said at least one base ply is pierced subsequently so as to obtain an acoustic absorption panel;3. The method according to claim 1 , wherein said at least one reinforcing ply is formed by an overlength of at least one end of said at least one base ply.4. The method according to claim 2 , wherein said at least one reinforcing ply is formed by overlengths of two ends of said at least one base ply.5. The method according to claim 1 , wherein said at least one reinforcing ply is formed by a ply distinct from said at least one base ply.6. The method according to claim 5 , wherein said ...

METHOD FOR MANUFACTURING A COMPOSITE SANDWICH PANEL WITH HONEYCOMB CORE

The present disclosure provides a method for manufacturing a composite sandwich panel with an alveolar core. The alveolar core exhibits a plurality of cells each delimited by at least one wall formed from at least one partition. In particular, a portion of the partition is integrated to a support skin of the composite sandwich panel during a resin molding step.

Tool for banding mechanical components and banding method using such a tool

The present invention relates to a tool for banding mechanical components. It also relates to a banding method using such a tool. The tool for banding mechanical components has: at least one jaw (21) having at least one holder (22) for a component to be banded, at least one part (20) that is fixed relative to said jaw (21), and at least one actuator (28) for mobilizing said at least one jaw (21) when the component to be banded is detected in a banding position on a band.

TOOL FOR BANDING MECHANICAL COMPONENTS AND BANDING METHOD USING SUCH A TOOL

A tool for shrink-fitting mechanical parts includes a fixed portion, a movable portion movable relative to the fixed portion, a support for a part to be shrink-fitted, a docking part for docking the tool on a hoop, and an actuator displacing the movable portion when the part to be shrink-fitted is detected in a shrink-fitting position on the hoop receiving the part. In particular, the fixed portion includes a fixed jaw and a housing, and the movable portion includes a movable jaw and a housing. The support and the docking part are disposed in the corresponding housing, respectively, so that the support and the docking part determine sets of parts to be shrink-fitted and/or of hoop parts for the tool. The housings dispose on the tool the docking part and the support with geometric reference to the hoop. 1. A tool for shrink-fitting mechanical parts , comprising:at least one fixed portion comprising a fixed jaw and at least one housing;at least one movable portion comprising a movable jaw and at least one housing, said movable portion being movable relative to said fixed jaw;at least one support for a part to be shrink-fitted, said support disposed in at least one of said housings;at least one docking part for docking the tool on a hoop, said docking part disposed in at least another of said housings;said at least one support and said at least one docking part configured to determine sets of parts to be shrink-fitted and/or of hoop parts for the tool;said housings configured to dispose on the tool said at least one docking part and said at least one support with geometric reference to the hoop receiving the part to be shrink-fitted; andat least one actuator displacing said at least one movable portion when the part to be shrink-fitted is detected in a shrink-fitting position on the hoop.2. The tool according to claim 1 , wherein said movable jaw cooperates with a fluid cylinder engaged by a movable rod thereof through the hoop and the part to be shrink-fitted during ...

METHOD FOR MANUFACTURING A T-SHAPED COMPOSITE PART BY RESIN-TRANSFER MOULDING

The invention relates to a method for manufacturing a T-shaped composite part by resin-transfer moulding, which includes the steps involving: creating a preform having a substantially planar stack (A) of plies and having two L-shaped stacks (B, C) of plies; placing said preform such that said L-shaped stacks L (B, C) meet between two cores (M1, M2) of a resin-transfer moulding tool (M); inserting and removing fibres through said planar stack (A) in a direction perpendicular or quasi-perpendicular to said stack (A) and such as to form loops (b) inside the portions (81, 82) of said L-shaped stacks (B, C) that are substantially perpendicular to said planar stack; closing the moulding tool (M); injecting the resin into the moulding tool (M); and heating the moulding tool (M) in order to cure the resin.

Method for producing foam panels, especially for the field of aeronautics

The invention relates to a method for producing foam panels, especially for the field of aeronautics, comprising the steps consisting in: providing at least two blocks of foam material (19a, 19b); arranging said two blocks on at least one ply of dry fabric (21 a, 2b), a so-called "base ply", maintaining a space (23) between said two blocks; folding said base ply (21 a, 21 b) around said two blocks (19a, 19b) so as to envelop them; filling the space (23) between the two blocks (19a, 19b) with at least one so-called "reinforcing" ply of fabric (211a, 211b, 212a, 212b); covering the base ply (21a, 21b) with at least one so-called "covering" ply of dry or fresh fabric (29), on the side where the reinforcing ply was inserted (211 a, 211 b, 212a, 212b); injecting the assembly produced in this way with resin; and baking the assembly produced in this way.

Method for producing a composite sandwich panel with a honeycomb core

A method for producing a composite sandwich panel (1, 100) with a honeycomb core (2). The present invention relates to a method for producing a composite sandwich panel with a honeycomb core having a plurality of cells (4) each delimited by at least one wall formed from at least one partition (5, 150), characterised in that at least one portion of said partitions is integrated with a skin support (3) of the sandwich panel during a resin moulding step; and to such a panel obtained by this method.

METHOD FOR MANUFACTURING A T-SHAPED COMPOSITE PART BY RESIN-TRANSFER MOLDING

A method for manufacturing a T-shaped composite part by resin transfer molding, includes the following steps: making a preform with a planar stack of plies and with two L-shaped stacks of plies; placing the preform so that the L-shaped stacks meet between two cores of a resin transfer molding tool; inserting and removing fibers through the planar stack in a direction perpendicular or quasi-perpendicular to the planar stack and so that loops are formed inside a portion of the L-shaped stacks which are substantially perpendicular to the planar stack; closing the resin transfer molding tool; injecting a resin into the resin transfer molding tool; and heating the resin transfer molding tool to cure the resin.

METHOD FOR MANUFACTURING A COMPOSITE SANDWICH PANEL WITH HONEYCOMB CORE

The present disclosure provides a method for manufacturing a composite sandwich panel with an alveolar core. The alveolar core exhibits a plurality of cells each delimited by at least one wall formed from at least one partition. In particular, a portion of the partition is integrated to a support skin of the composite sandwich panel during a resin molding step. 1. A method for manufacturing a composite sandwich panel with an alveolar core exhibiting a plurality of cells each delimited by at least one wall formed from at least one partition , wherein at least one portion of said partition is integrated to a support skin of the composite sandwich panel during a resin molding step.2. The method according to claim 1 , wherein the partition is integrated to the support skin at least at one of its ends.3. The method according to claim 2 , wherein said at least one partition is inserted before the integration in the resin.4. The method according to claim 1 , wherein said at least one partition is at least partially realized by resin molding simultaneously with a step of molding the support skin by said resin.5. The method according to claim 4 , further comprising a step of setting up composite plies and/or preforms in at least one molding space of said at least one partition.6. The method according to claim 1 , further comprising a step of installing at least one septum inside at least one of the plurality of cells.7. The method according to claim 1 , wherein the support skin is a solid inner skin of the composite sandwich panel.8. A mold for realizing a composite sandwich panel comprising at least one main shell substantially defining claim 1 , with a corresponding closing cover claim 1 , an outer general volume of the composite sandwich panel to be realized claim 1 ,wherein said mold comprises at least one secondary mold to be placed inside said at least one main shell during molding, providing the main shell with a molding space of a support skin, andwherein said at ...

PROCESS FOR PRODUCING CELLULAR PANELS, IN PARTICULAR FOR THE AERONAUTICAL FIELD

Ce procédé comprend les étapes consistant à : - préparer au moins deux blocs de matériau cellulaire (19a, 19b), - disposer ces deux blocs sur au moins un pli de tissu sec (21a, 2b) dit « pli de base », en maintenant un espace (23) entre ces deux blocs, - rabattre ce pli de base (21a, 21b) autour de ces deux blocs (19a, 19b) de manière à les envelopper, - remplir l'espace (23) entre les deux blocs (19a, 19b) d'au moins un pli de tissu dit «de renfort» (211a, 211b, 212a, 212b), - recouvrir le pli de base (21a, 21b) d'au moins un pli de tissu sec ou frais dit «de couverture» (29), du côté où l'on a introduit le pli de renfort (211 a, 211 b, 21 2a, 21 2b), - injecter l'ensemble ainsi obtenu de résine, et à - cuire l'ensemble ainsi obtenu. This method comprises the steps of: - preparing at least two blocks of cellular material (19a, 19b), - arranging these two blocks on at least one fold of dry tissue (21a, 2b) called "base fold", while maintaining a space (23) between these two blocks, - fold down this base fold (21a, 21b) around these two blocks (19a, 19b) so as to envelop them, - fill the space (23) between the two blocks ( 19a, 19b) of at least one fold of so-called "reinforcing" fabric (211a, 211b, 212a, 212b), - covering the base fold (21a, 21b) with at least one fold of dry or fresh fabric said "Blanket" (29), on the side where the reinforcing ply (211 a, 211 b, 21 2a, 21 2b) has been introduced, - inject the thus obtained resin assembly, and - to cook the together thus obtained.

PROCESS FOR PRODUCING CELLULAR PANELS, IN PARTICULAR FOR THE AERONAUTICAL FIELD

METHOD FOR MANUFACTURING A PREFORM FOR COMPOSITE MATERIALS COMPRISING NON-DEVELOPABLE GEOMETRIES

Procédé de mise en forme d'une préforme fibreuse de tissus et/ou fibres unidirectionnelles, qui une fois conformée à sa géométrie finale présente des zones non développables. Le procédé consiste à exercer une traction sur des fibres, lors du conformage de la préforme, afin de consommer la sur-matière générée par les formes non développables. Process for shaping a fibrous preform of fabrics and / or unidirectional fibers, which once conformed to its final geometry has non-developable areas. The method consists in exerting a traction on fibers, during the conformation of the preform, in order to consume the over-material generated by the non-developable forms.

METHOD FOR MANUFACTURING A PREFORM FOR COMPOSITE MATERIALS COMPRISING NON-DEVELOPABLE GEOMETRIES

A method of fabricating a composite sandwich panel with a honeycomb core, mold for making it and sandwich panel.

Tool for banding mechanical components and banding method using such a tool

The present invention relates to a tool for banding mechanical components. It also relates to a banding method using such a tool. The tool for banding mechanical components has: at least one jaw (21) having at least one holder (22) for a component to be banded, at least one part (20) that is fixed relative to said jaw (21), and at least one actuator (28) for mobilizing said at least one jaw (21) when the component to be banded is detected in a banding position on a band.

METHOD FOR MANUFACTURING SANDWICH COMPOSITE PANEL WITH ALVEOLAR SOUL

La présente invention se rapporte à un procédé de fabrication d'un panneau sandwich composite à âme alvéolaire présentant une pluralité d'alvéoles délimitées chacune par au moins une paroi formée à partir d'au moins une cloison, caractérisé en ce qu'au moins une partie desdites cloisons sont intégrées à une peau support du panneau sandwich lors d'une étape de moulage de résine ; ainsi qu'à un tel panneau obtenu par ce procédé. The present invention relates to a method for manufacturing a composite sandwich panel having a cellular core having a plurality of cells each delimited by at least one wall formed from at least one partition, characterized in that at least one part of said partitions are integrated with a support skin of the sandwich panel during a resin molding step; as well as to such a panel obtained by this method.

MECHANICAL PIECE TOOL AND FREQUENCY METHOD USING SUCH TOOL

Device and method for automatically routing patches near a patch gripper

Ce dispositif d’acheminement automatique de patchs pour système de drapage (6) comprenant un préhenseur (8) de patch (4) comprend un emplacement (16) destiné à accueillir un enroulement de matière (18) destinée à la réalisation de patchs (4), un système de déroulement (22) de matière, et un système de positionnement (24) d’un patch (4) destiné à pouvoir être positionné en regard du préhenseur (8) de patch (4). Figure pour l’abrégé : Fig 1 This device for automatically routing patches for a draping system (6) comprising a gripper (8) for the patch (4) comprises a location (16) intended to accommodate a winding of material (18) intended for the production of patches (4 ), an unwinding system (22) of material, and a positioning system (24) for a patch (4) intended to be able to be positioned facing the gripper (8) of the patch (4). Figure for abstract: Fig 1

METHOD FOR MANUFACTURING SANDWICH PANEL COMPOSITE WITH ALVEOLAR SOUL

Préhenseur, notamment pour l'application d'une pièce en nid d'abeille sur une surface cible et automate pourvu d'un tel préhenseur

Ce préhenseur pour la préhension d'une pièce en nid d'abeille et le dépôt de la pièce sur une surface cible comprenant des éléments de préhension (11) montés sur un support (10) et destinés chacun à être insérés dans une cellule interne (C) de la pièce en nid d'abeille, lesdits éléments de préhension comprenant une surface de préhension déplaçable latéralement par rapport au support de manière à venir en contact avec un élément de paroi latéral de la cellule interne.

Systeme de decoupe d’une bande de materiau composite

L’invention concerne une installation (10) de fabrication de pièces découpées dans des bandes en matériau composite (16) comportant un dispositif d’acheminement (20) selon une direction longitudinale (L) apte à convoyer une bande (16) depuis un rouleau (14) jusqu’à une zone (22) de récupération, un dispositif (24) de découpe surmontant le dispositif d’acheminement (20), apte à découper dans la bande (16) des pièces (28) de formes déterminées, un dispositif d’évacuation (30) de pièces découpées au-dessus de la zone de récupération (22), et un dispositif (32) de séparation de la bande (16) et d’un voile (18), le dispositif (32) de séparation étant agencé avant le dispositif de découpe (24), caractérisé en ce que le dispositif d’acheminement (20) comporte au moins un interstice (40) enjambé longitudinalement par la bande (16), et en ce que l’outil de découpe (26) est configuré pour couper la bande (16) au droit dudit interstice (40). Figure pour l'abrégé : Figure 4.

Préhenseur, notamment pour l’application d’une pièce en nid d’abeille sur une surface cible et automate pourvu d’un tel préhenseur

Ce préhenseur pour la préhension d’une pièce en nid d’abeille et le dépôt de la pièce sur une surface cible comprenant des éléments de préhension (11) montés sur un support (10) et destinés chacun à être insérés dans une cellule interne (C) de la pièce en nid d’abeille, lesdits éléments de préhension comprenant une surface de préhension déplaçable latéralement par rapport au support de manière à venir en contact avec un élément de paroi latéral de la cellule interne. Figure pour l’abrégé : Fig 6b

Dispositif et procédé d’acheminement automatique de patchs à proximité d’un préhenseur de patch

Ce dispositif d’acheminement automatique de patchs pour système de drapage (6) comprenant un préhenseur (8) de patch (4) comprend un emplacement (16) destiné à accueillir un enroulement de matière (18) destinée à la réalisation de patchs (4), un système de déroulement (22) de matière, et un système de positionnement (24) d’un patch (4) destiné à pouvoir être positionné en regard du préhenseur (8) de patch (4). Figure pour l’abrégé : Fig 1

Procédé d’usinage de parois pour une turbomachine

Le présent document concerne un procédé d’usinage d’une paroi (302) en matériau composite à matrice céramique comprenant une première face (305) et une seconde face (303) opposées, le procédé comprenant au moins les étapes : déposer une couche sacrificielle (304) sur au moins une partie de la première face (305), usiner ladite paroi (302) avec un outil d’usinage (312) au travers la seconde face (305) de sorte que l’outil d’usinage (312) traverse la couche sacrificielle (304), retirer la couche sacrificielle (304), et dans lequel la couche sacrificielle (304) est agencée pour empêcher une désagrégation de la paroi (302) au cours de l’usinage de ladite paroi (302). Figure à publier avec l’abrégé : [Fig. 3]