FR2595621A1 - Process for manufacturing a reinforcing structure for a component made from a composite material - Google Patents
Process for manufacturing a reinforcing structure for a component made from a composite material Download PDFInfo
- Publication number
- FR2595621A1 FR2595621A1 FR8603532A FR8603532A FR2595621A1 FR 2595621 A1 FR2595621 A1 FR 2595621A1 FR 8603532 A FR8603532 A FR 8603532A FR 8603532 A FR8603532 A FR 8603532A FR 2595621 A1 FR2595621 A1 FR 2595621A1
- Authority
- FR
- France
- Prior art keywords
- texture
- mandrel
- meshes
- fibrous texture
- fibrous
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C63/00—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor
- B29C63/18—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor using tubular layers or sheathings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/56—Tensioning reinforcements before or during shaping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
- B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
- B29K2105/0809—Fabrics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2023/00—Tubular articles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Braiding, Manufacturing Of Bobbin-Net Or Lace, And Manufacturing Of Nets By Knotting (AREA)
Abstract
Description
PROCEDE DE FABRICATION D'UNE STRUCTURE DE RENFORT POUR
PIECE EN MATERIAU COMPOSITE
La présente invention concerne la fabrication de structures de renfort pour pièces en matériau composite, et plus particulièrement pour des pièces ayant des formes de révolution ou tubulaires comme, par exemple, des pièces de moteurs fusées.METHOD FOR MANUFACTURING A REINFORCEMENT STRUCTURE FOR
COMPOSITE MATERIAL
The present invention relates to the manufacture of reinforcement structures for parts made of composite material, and more particularly for parts having forms of revolution or tubular like, for example, parts of rocket engines.
Les structures de renfort pour pièces composites de révolution ou tubulaires sont généralement réalisées par bobinage d'une texture fibreuse (fil, ruban ou bande de matériau fibreux) pour former des couches superposées sur un mandrin dont la forme est semblable à celle de la structure à fabriquer. Les couches ainsi formées peuvent être liées entre elles par exemple au moyen d'éléments de renfort radiaux ou par aiguilletage. Reinforcement structures for composite revolving or tubular parts are generally produced by winding a fibrous texture (wire, ribbon or strip of fibrous material) to form superimposed layers on a mandrel whose shape is similar to that of the structure to to manufacture. The layers thus formed can be linked together for example by means of radial reinforcing elements or by needling.
La présente invention a pour but de fournir un nouveau procédé plus particulièrement adapté à la fabrication de structures de renfort de révolution non cylindriques ou de structures de renfort tubulaires présentant des déformations locales ou globales, c'est-à-dire de structures dont la forme rend plus difficle leur fabrication par bobinage. The object of the present invention is to provide a new process more particularly suited to the manufacture of non-cylindrical reinforcement structures of revolution or of tubular reinforcement structures having local or global deformations, that is to say structures whose shape makes it more difficult to manufacture them by winding.
Ce but est atteint grâce à un procédé selon lequel, conformément à l'invention, on met en place sur un mandrin une texture fibreuse constituée par un tissu ou une trame à mailles déformables de manière à épouser la forme du mandrin par auto-adaptation de la géométrie des mailles. This object is achieved by a process according to which, in accordance with the invention, a fibrous texture consisting of a fabric or a weft with deformable mesh is placed on a mandrel so as to conform to the shape of the mandrel by self-adaptation of the geometry of the meshes.
La texture fibreuse est une bande de tissu coupée en biais ou une tresse à plat dont le maillage est suffisamment aéré pour admettre des déformations importantes sans glissement relatif des fibres. Les mailles de la texture fibreuse sont disposées avec leurs côtés ayant des inclinaisons opposées par rapport à la direction longitudinale de la structure et sont déformables en losange pour suivre les variations éventuelles de la circonférence de la structure le long de cette dernière. The fibrous texture is a strip of fabric cut at an angle or a flat braid whose mesh is sufficiently ventilated to admit significant deformations without relative slippage of the fibers. The meshes of the fibrous texture are arranged with their sides having opposite inclinations with respect to the longitudinal direction of the structure and are deformable into a diamond to follow any variations in the circumference of the structure along the latter.
La mise en place de la texture fibreuse sur le mandrin peut être effectuée en fixant cette texture sur le mandrin à une extrémité longitudinale et en appliquant ensuite progressivement la texture sur le mandrin depuis cette extrémité jusqu'à l'autre extrémité longitudinale tout en exerçant une tension en direction de cette autre extrémité. Sous l'effet de cette tension, les fibres de la texture se placent automatiquement dans des positions déterminées par la forme du mandrin, d'où une grande facilité de mise en place et une bonne reproductibilité du drapage. The placement of the fibrous texture on the mandrel can be carried out by fixing this texture on the mandrel at one longitudinal end and then gradually applying the texture on the mandrel from this end to the other longitudinal end while exerting a tension towards this other end. Under the effect of this tension, the fibers of the texture are automatically placed in positions determined by the shape of the mandrel, hence great ease of implementation and good reproducibility of draping.
Les limites de déformation des mailles déterminent les valeurs maximale et minimale de la circonférence à laquelle la texture peut s'adapter. Aussi, lorsque le profil de la structure rend nécessaire, on utilisera une texture à maillage -variable dans la direction longitudinale de la structure à réaliser. The mesh deformation limits determine the maximum and minimum values of the circumference to which the texture can adapt. Also, when the profile of the structure makes it necessary, a texture with a -variable mesh will be used in the longitudinal direction of the structure to be produced.
L'invention sera mieux comprise à la lecture de la description faite ci-après à titre indicatif mais non limitatif en référence aux dessins annexés sur lesquels
- la figure 1 est une vue partielle schématique illustrant l'adaptation de la texture fibreuse au profil de la structure à réaliser par déformation des mailles de la texture suivant le procédé conforme à l'invention
- les figures 2 à 4 montrent des textures fibreuses à mailles déformables utilisables pour la mise en oeuvre du procédé selon l'invention ; et
- les figures 5 et 6 montrent schématiquement la mise en place d'une texture fibreuse sur un mandrin conformément à l'invention.The invention will be better understood on reading the description given below for information but not limitation with reference to the accompanying drawings in which
- Figure 1 is a schematic partial view illustrating the adaptation of the fibrous texture to the profile of the structure to be produced by deformation of the meshes of the texture according to the method according to the invention
- Figures 2 to 4 show fibrous textures with deformable mesh usable for the implementation of the method according to the invention; and
- Figures 5 and 6 schematically show the establishment of a fibrous texture on a mandrel according to the invention.
Sur la figure 1, la référence 10 désigne une texture fibreuse déformable constituée par un tissu à maillage aéré pour admettre des déformations importantes sans glissement relatif des fibres. La texture est équilibrée, c'est-à-dire formée de fils identiques afin d'assurer une déformabilité uniforme dans toute la texture. In FIG. 1, the reference 10 designates a deformable fibrous texture constituted by a fabric with an aerated mesh to admit significant deformations without relative slippage of the fibers. The texture is balanced, that is to say formed from identical threads in order to ensure uniform deformability throughout the texture.
La texture 10 est placée sur un corps de révolution 20 avec les mailles 11 en forme de losange disposées de manière que chaque maille ait deux sommets ou noeuds opposés N1 situés dans un même plan méridien et les deux autres sommets ou noeuds opposés N2 situés dans une même section droite. De la sorte, la texture 10 peut épouser la forme du corps de révolution 20 par adaptation de la géométrie -des mailles qui, suivant 11 évolution de la circonférence du corps 20, se déforment en losange. On notera que les fibres constitutives de la texture sont non élastiques, l'adaptation de la texture se faisant par déformation des mailles sans modification de la longueur de leurs côtés et non pas par déformation élastique des fibres. The texture 10 is placed on a body of revolution 20 with the diamond-shaped meshes 11 arranged so that each mesh has two opposite vertices or nodes N1 located in the same meridian plane and the other two opposite vertices or nodes N2 located in a same cross section. In this way, the texture 10 can match the shape of the body of revolution 20 by adapting the geometry - of the meshes which, according to the evolution of the circumference of the body 20, are deformed into a diamond. It will be noted that the fibers constituting the texture are non-elastic, the adaptation of the texture being made by deformation of the meshes without modification of the length of their sides and not by elastic deformation of the fibers.
Les noeuds N1 des mailles situés dans une même section droite étant fixés à la surface du corps 20, l'application des demi-mailles suivantes sur cette surface en maintenant une légère tension axiale (flèche T) fait que les fibres se placent suivant le plus court chemin, donc dans une position parfaitement déterminée par le profil du corps, chaque noeud N2 étant toujours situé à la même distance des noeuds NI de la même maille. Si la mise en place de la texture est réalisée progressivement, chaque point du maillage vient occuper une position déterminée. Il en résulte, outre une facilité de mise en place, une très bonne reproductibilité du drapage réalisé. The nodes N1 of the stitches located in the same cross section being fixed to the surface of the body 20, the application of the following half-stitches on this surface while maintaining a slight axial tension (arrow T) causes the fibers to be placed according to the most short path, therefore in a position perfectly determined by the profile of the body, each node N2 being always located at the same distance from the nodes NI of the same mesh. If the implementation of the texture is carried out gradually, each point of the mesh comes to occupy a determined position. This results, in addition to ease of installation, very good reproducibility of the draping carried out.
Une texture telle que celle 10 de la figure 1 peut être obtenue en découpant des bandes de tissu à 450 par rapport aux directions de chaîne et de trame (voir figure 2). Les bandes ainsi obtenues peuvent être ensuite assemblées bout à bout pour fournir une texture 10 ayant la dimension requise. L'assemblage est réalisé de façon à ne pas gêner la déformabilité du réseau de fibres, par exemple par couture en zig-zag ou par collage discontinu. Il est également envisageable de réaliser la texture 10 sous forme d'une tresse plate. A texture such as that of FIG. 1 can be obtained by cutting strips of fabric at 450 with respect to the warp and weft directions (see FIG. 2). The strips thus obtained can then be assembled end to end to provide a texture 10 having the required dimension. The assembly is carried out so as not to hinder the deformability of the fiber network, for example by zig-zag sewing or by discontinuous bonding. It is also conceivable to produce the texture 10 in the form of a flat braid.
Les mailles n'étant déformables que dans certaines limites, la texture 10 n'est adaptable qu'à des circonférences comprises entre une valeur minimale et une valeur maximale. The meshes being deformable only within certain limits, the texture 10 is only adaptable to circumferences comprised between a minimum value and a maximum value.
Lorsque le corps sur lequel la texture doit être mise en place présente des variations de circonférence importantes, on pourra conférer à la texture un maillage variable le longde l'axe de la structure à réaliser. Ceci peut être obtenu an formant la texture au moyen de bandes de tissu 10a, lOb, Oc (figure 3) découpées à 45 , assemblées bord à bord et ayant des nombres de mailles différents par unité de longueur. Ainsi, dans le cas de la figure 3, la bande de tissu lOb comprend un plus grand nombre de mailles par unité de longueur que les bandes de tissu 10a et vioc, et ces mailles sont déformées en étant allongées dans la direction longitudinale de la structure à réaliser. La bande centrale lOb permet donc une adaptation de la texture à un corps présentant une partie médiane fortement renflée. When the body on which the texture is to be placed has significant variations in circumference, the texture can be given a variable mesh along the axis of the structure to be produced. This can be obtained by forming the texture by means of strips of fabric 10a, 10b, Oc (FIG. 3) cut to 45, assembled edge to edge and having different numbers of stitches per unit of length. Thus, in the case of FIG. 3, the strip of fabric 10b comprises a greater number of meshes per unit of length than the strips of fabric 10a and vioc, and these meshes are deformed by being elongated in the longitudinal direction of the structure to achieve. The central strip 10b therefore allows an adaptation of the texture to a body having a strongly swollen middle part.
Dans le cas de textures formées par une tresse à plat, il est également possible de faire varier le maillage en utilisant des tresses plates à maillage évolutif comme illustré par la figure 4. In the case of textures formed by a flat braid, it is also possible to vary the mesh using flat braids with evolving mesh as illustrated in FIG. 4.
Pour la réalisation d'une structure de renfort pour pièce composite, la texture déformable est mise en place sur un mandrin dont la forme est semblable à celle de la structure à réaliser. To produce a reinforcing structure for a composite part, the deformable texture is placed on a mandrel whose shape is similar to that of the structure to be produced.
Plusieurs couches de texture de renfort sont superposées en fonction de l'épaisseur désirée. Lorsque le nombre de couches superposées est élevé, la réalisation de la structure est effectuée en plusieurs étages au cours de laquelle un nombre limité de couches est mis en place simultanément, ce nombre limité étant tel qu'il permette de contrôler correctement la mise en forme des couches en une seule passe. La première série de couches est appliquée sur le mandrin pour former un drapage qui constitue à son tour un mandrin sur lequel est appliquée la deuxième série de couches, et ainsi de suite.Several layers of reinforcing texture are superimposed according to the desired thickness. When the number of superimposed layers is high, the structure is produced in several stages during which a limited number of layers is put in place simultaneously, this limited number being such that it allows correct shaping control layers in one pass. The first series of layers is applied to the mandrel to form a layup which in turn constitutes a mandrel on which the second series of layers is applied, and so on.
Les figures 5 et 6 illustrent très schématiquement un mode de mise en oeuvre du procédé selon l'invention pour le drapage d'une texture à mailles déformables sur un mandrin en forme de tuyère de moteur fusée. Figures 5 and 6 illustrate very schematically an embodiment of the method according to the invention for draping a texture with deformable meshes on a mandrel in the form of a rocket engine nozzle.
Une gaine tubulaire 12 formée par enroulement de la texture 10 sur elle-même en plusieurs couches superposées est disposée autour du mandrin 20. A une extrémité, la gaine 12 est fixée à la surface du mandrin, par exemple par cerclage (en 13 sur la figure 5) puis, à partir de cet ancrage, elle est appliquée contre la surface du mandrin en exerçant, dans le sens de la progression, une légère traction qui assure l'alignement des fibres. A tubular sheath 12 formed by winding the texture 10 on itself in several superimposed layers is arranged around the mandrel 20. At one end, the sheath 12 is fixed to the surface of the mandrel, for example by strapping (at 13 on the FIG. 5) then, from this anchoring, it is applied against the surface of the mandrel by exerting, in the direction of progression, a slight traction which ensures the alignment of the fibers.
L'application ou compactage des couches formant la gaine 12 est obtenue localement par exemple par l'action de molettes libres 14 disposées circulairement autour de la structure en formation et capables de se déplacer radialement tout en maintenant sur la structure un effort sensiblement constant. L'ensemble des molettes 14 est déplacé en translation continue parallèlement à l'axe du mandrin 20 à partir de l'extrémité de fixation de la gaine 12 (flèche F1) tandis que le mandrin est entraîné en rotation continue sur lui-même (flèche F2). Le compactage effectué par les molettes 14 peut être complété efficacement par l'action d'une frette mobile 15 maintenue sous tension par passage dans la gorge d'une poulie 16 soumise à une force élastique (flèche F3) tendant à l'écarter du mandrin.La frette 15 et la poulie 16 (uniquement représentées sur la figure 5) sont déplacées en translation avec les molettes 14, immédiatement derrière celle-ci. La frette 15 sous tension contribue ainsi à appliquer la gaine 12 contre la surface du mandrin et progresse régulièrement du fait de son enroulement à l'avant et de son déroulement à l'arrière par suite de la rotation continue du mandrin. The application or compaction of the layers forming the sheath 12 is obtained locally for example by the action of free wheels 14 arranged circularly around the structure in formation and capable of moving radially while maintaining a substantially constant force on the structure. The set of knobs 14 is moved in continuous translation parallel to the axis of the mandrel 20 from the fixing end of the sheath 12 (arrow F1) while the mandrel is driven in continuous rotation on itself (arrow F2). The compaction carried out by the knobs 14 can be effectively completed by the action of a movable hoop 15 kept under tension by passing through the groove of a pulley 16 subjected to an elastic force (arrow F3) tending to move it away from the mandrel .The hoop 15 and the pulley 16 (only shown in Figure 5) are moved in translation with the knobs 14, immediately behind it. The hoop 15 under tension thus contributes to applying the sheath 12 against the surface of the mandrel and progresses regularly due to its winding at the front and its unwinding at the rear as a result of the continuous rotation of the mandrel.
La tension des fils de la texture est obtenue par traction sur l'extrémité libre de la gaine 12. Cette tension peut être complétée en donnant aux molettes 14 un léger angle de dérive a par rapport à la trajectoire hélicoîdale de la zone de contact avec la structure en formation ; il en résulte en effet une force d'entraînement sensiblement axiale qui s'exerce sur la texture déformable et facilite la mise en place des mailles dans la zone compactée. The tension of the texture threads is obtained by pulling on the free end of the sheath 12. This tension can be supplemented by giving the knurls 14 a slight angle of drift a relative to the helical trajectory of the zone of contact with the structure in training; this in fact results in a substantially axial driving force which is exerted on the deformable texture and facilitates the positioning of the meshes in the compacted zone.
Lorsque le mandrin 20 présente une zone de diamètre réduit, le maintien de la gaine 12 appliquée contre la surface du mandrin dans cette zone est assurée au moyen d'une frette fixe telle que 17 (figure 6). When the mandrel 20 has a zone of reduced diameter, the sheath 12 applied against the surface of the mandrel in this zone is maintained by means of a fixed hoop such as 17 (FIG. 6).
Lorsque le compactage de la gaine 12 est terminé, l'extrémité restant libre de celle-ci est à son tour fixée sur la surface du mandrin. Ensuite, selon l'épaisseur désirée pour la structure à réaliser, une ou plusieurs gaines supplémentaires peuvent être mises en place successivement de la même façon. When the compaction of the sheath 12 is finished, the remaining free end of the latter is in turn fixed to the surface of the mandrel. Then, depending on the thickness desired for the structure to be produced, one or more additional sheaths can be successively put in place in the same way.
Lorsque le drapage de la texture de renfort est terminé, la structure ainsi obtenue peut être éventuellement renforcée radialement par couture ou mise en place d'éléments de renfort radiaux. La fabrication de la pièce composite est ensuite terminée de façon en soi bien connue par densification de la structure de renfort poreuse obtenue. Cette densification est réalisée par exemple par imprégnation liquide et traitement thermique ou par infiltration chimique en phase vapeur. When the layup of the reinforcement texture is finished, the structure thus obtained can be optionally reinforced radially by sewing or fitting of radial reinforcement elements. The manufacture of the composite part is then completed in a manner well known per se by densification of the porous reinforcement structure obtained. This densification is carried out for example by liquid impregnation and heat treatment or by chemical vapor infiltration.
Le matériau constitutif de la texture dépend bien entendu de l'application envisagée. Pour une utilisation impliquant une exposition à des contraintes thermomécaniques sévères, la texture est de préférence réalisée avec des fibres #réfractaires, notamment des fibres en carbone ou en céramique ou en un précurseur de ces matériaux, par exemple des fibres de PAN (polyacrylonitrile) préoxydé précuseur du carbone. La densification de la structure est réalisée par dépôt d'un matériau qui dépend également de l'utilisation envisagée de la pièce composite, par exemple du pyrocarbone ou un autre matériau réfractaire tel que le carbure de silicium déposés en phase vapeur. The material constituting the texture naturally depends on the intended application. For use involving exposure to severe thermomechanical stresses, the texture is preferably produced with refractory fibers #, in particular carbon or ceramic fibers or in a precursor of these materials, for example fibers of PAN (polyacrylonitrile) preoxidized carbon precursor. The densification of the structure is carried out by deposition of a material which also depends on the envisaged use of the composite part, for example pyrocarbon or another refractory material such as silicon carbide deposited in the vapor phase.
Bien que l'on ait envisagé l'application du procédé conforme à l'invention à la réalisation d'une structure de révolution, on comprendra aisément que ce même procédé est utilisable pour réaliser des structures de formes plus complexes, par exemple des structures tubulaires présentant des déformations locales (bordures de trou, bossages, méplats,...) ou des déformations globales (tubes de section non circulaire, tubes cintrés,..). Although consideration has been given to the application of the process according to the invention to the production of a structure of revolution, it will readily be understood that this same process can be used to produce structures of more complex shapes, for example tubular structures with local deformations (hole edges, bosses, flats, ...) or global deformations (tubes of non-circular section, bent tubes, ...).
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8603532A FR2595621B1 (en) | 1986-03-12 | 1986-03-12 | METHOD FOR MANUFACTURING A REINFORCING STRUCTURE FOR A PART MADE OF COMPOSITE MATERIAL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8603532A FR2595621B1 (en) | 1986-03-12 | 1986-03-12 | METHOD FOR MANUFACTURING A REINFORCING STRUCTURE FOR A PART MADE OF COMPOSITE MATERIAL |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2595621A1 true FR2595621A1 (en) | 1987-09-18 |
| FR2595621B1 FR2595621B1 (en) | 1988-11-04 |
Family
ID=9333055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR8603532A Expired FR2595621B1 (en) | 1986-03-12 | 1986-03-12 | METHOD FOR MANUFACTURING A REINFORCING STRUCTURE FOR A PART MADE OF COMPOSITE MATERIAL |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR2595621B1 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0425099A2 (en) * | 1989-09-28 | 1991-05-02 | Milliken Europe N.V. | Stabilised fabrics |
| FR2723881A1 (en) * | 1994-08-26 | 1996-03-01 | Zhao Yong Gao | Prodn. of fluoro:polymer based, metal braid reinforced corrosion protection prod. |
| EP0842757A1 (en) * | 1996-11-15 | 1998-05-20 | COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN-MICHELIN & CIE | Method and apparatus for producing a rim preform |
| WO2001038625A2 (en) * | 1999-11-24 | 2001-05-31 | Snecma Moteurs | Method for making a bowl in thermostructural composite material, resulting bowl and use of same as crucible support |
| FR2812889A1 (en) * | 2000-08-11 | 2002-02-15 | Snecma Moteurs | Production of single-piece bowl, used as crucible support in monocrystalline silicon manufacture, comprises stacking deformable fibrous reinforcement strata on form corresponding to bowl, followed by densification |
| WO2002083494A1 (en) * | 2001-04-11 | 2002-10-24 | Albany International Corp. | End portions for a flexible fluid containment vessel and a method of making the same |
| US6675734B2 (en) | 2001-04-11 | 2004-01-13 | Albany International Corp. | Spiral formed flexible fluid containment vessel |
| US7107921B2 (en) | 2001-10-30 | 2006-09-19 | Albany International Corp. | End portion for a flexible fluid containment vessel and a method of making the same |
| US7775171B2 (en) | 2003-01-21 | 2010-08-17 | Albany International Corp. | Flexible fluid containment vessel featuring a keel-like seam |
| WO2013096202A1 (en) * | 2011-12-21 | 2013-06-27 | GKN Aerospace Services Structures, Corp. | Bias fiber control during wrapping of a fabric preform for a composite component |
| US9869036B2 (en) | 2015-04-13 | 2018-01-16 | Gkn Aerospace Services Structures Corporation | Apparatus and method for controlling fabric web |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6739274B2 (en) | 2001-04-11 | 2004-05-25 | Albany International Corp. | End portions for a flexible fluid containment vessel and a method of making the same |
| US6718896B2 (en) | 2001-10-30 | 2004-04-13 | Albany International Corp. | Fabric structure for a flexible fluid containment vessel |
| US6832571B2 (en) | 2001-10-30 | 2004-12-21 | Albany International Corp. | Segment formed flexible fluid containment vessel |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1170414A (en) * | 1956-05-15 | 1959-01-14 | Hays Mfg Co | Improvements in the manufacture of plastic tubes |
| GB962881A (en) * | 1963-01-30 | 1964-07-08 | Studebaker Corp | Improvements in or relating to machines for laying up hollow laminated articles |
| GB1046584A (en) * | 1963-03-15 | 1966-10-26 | Elektrotechnische Handels En I | Process for applying a reinforced plastic coating to a metal lamp post |
| DE2065706A1 (en) * | 1970-10-15 | 1975-04-17 | Bayer Ag | Reinforced plastic tube - comprises a knitted tubular sheath impregnated with heat setting resin |
| EP0012167A1 (en) * | 1978-12-11 | 1980-06-25 | Deutsche Carbone AG | Method of making a shaped article of reinforced material and shaped article so produced |
| EP0045896A2 (en) * | 1980-08-07 | 1982-02-17 | URANIT GmbH | Process and apparatus for producing fibre reinforced wound hollow bodies |
| GB2133337A (en) * | 1983-01-06 | 1984-07-25 | Secr Defence | Radome manufacture |
-
1986
- 1986-03-12 FR FR8603532A patent/FR2595621B1/en not_active Expired
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1170414A (en) * | 1956-05-15 | 1959-01-14 | Hays Mfg Co | Improvements in the manufacture of plastic tubes |
| GB962881A (en) * | 1963-01-30 | 1964-07-08 | Studebaker Corp | Improvements in or relating to machines for laying up hollow laminated articles |
| GB1046584A (en) * | 1963-03-15 | 1966-10-26 | Elektrotechnische Handels En I | Process for applying a reinforced plastic coating to a metal lamp post |
| DE2065706A1 (en) * | 1970-10-15 | 1975-04-17 | Bayer Ag | Reinforced plastic tube - comprises a knitted tubular sheath impregnated with heat setting resin |
| EP0012167A1 (en) * | 1978-12-11 | 1980-06-25 | Deutsche Carbone AG | Method of making a shaped article of reinforced material and shaped article so produced |
| EP0045896A2 (en) * | 1980-08-07 | 1982-02-17 | URANIT GmbH | Process and apparatus for producing fibre reinforced wound hollow bodies |
| GB2133337A (en) * | 1983-01-06 | 1984-07-25 | Secr Defence | Radome manufacture |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0425099A3 (en) * | 1989-09-28 | 1992-03-04 | Milliken Europe N.V. | Stabilised fabrics |
| EP0425099A2 (en) * | 1989-09-28 | 1991-05-02 | Milliken Europe N.V. | Stabilised fabrics |
| FR2723881A1 (en) * | 1994-08-26 | 1996-03-01 | Zhao Yong Gao | Prodn. of fluoro:polymer based, metal braid reinforced corrosion protection prod. |
| US6367531B1 (en) | 1996-11-15 | 2002-04-09 | COMPAGNIE GéNéRALE DES ETABLISSEMENTS MICHELIN - MICHELIN & CIE | Method and device for the manufacture of a rim preform |
| EP0842757A1 (en) * | 1996-11-15 | 1998-05-20 | COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN-MICHELIN & CIE | Method and apparatus for producing a rim preform |
| FR2755897A1 (en) * | 1996-11-15 | 1998-05-22 | Michelin & Cie | METHOD AND DEVICE FOR MANUFACTURING RIM PREFORM |
| US5985072A (en) * | 1996-11-15 | 1999-11-16 | Compagnie Generale Des Etablissements Michelin - Michelin & Cie | Method and device for the manufacture of a rim preform |
| US6837952B1 (en) | 1999-11-24 | 2005-01-04 | Snecma Moteurs | Method for making a bowl in thermostructural composite material |
| WO2001038625A3 (en) * | 1999-11-24 | 2001-12-20 | Snecma Moteurs | Method for making a bowl in thermostructural composite material, resulting bowl and use of same as crucible support |
| WO2001038625A2 (en) * | 1999-11-24 | 2001-05-31 | Snecma Moteurs | Method for making a bowl in thermostructural composite material, resulting bowl and use of same as crucible support |
| FR2812889A1 (en) * | 2000-08-11 | 2002-02-15 | Snecma Moteurs | Production of single-piece bowl, used as crucible support in monocrystalline silicon manufacture, comprises stacking deformable fibrous reinforcement strata on form corresponding to bowl, followed by densification |
| WO2002083494A1 (en) * | 2001-04-11 | 2002-10-24 | Albany International Corp. | End portions for a flexible fluid containment vessel and a method of making the same |
| US6675734B2 (en) | 2001-04-11 | 2004-01-13 | Albany International Corp. | Spiral formed flexible fluid containment vessel |
| US6860218B2 (en) | 2001-04-11 | 2005-03-01 | Albany International Corp. | Flexible fluid containment vessel |
| US7107921B2 (en) | 2001-10-30 | 2006-09-19 | Albany International Corp. | End portion for a flexible fluid containment vessel and a method of making the same |
| US7775171B2 (en) | 2003-01-21 | 2010-08-17 | Albany International Corp. | Flexible fluid containment vessel featuring a keel-like seam |
| WO2013096202A1 (en) * | 2011-12-21 | 2013-06-27 | GKN Aerospace Services Structures, Corp. | Bias fiber control during wrapping of a fabric preform for a composite component |
| US8900392B2 (en) | 2011-12-21 | 2014-12-02 | GKN Aerospace Services Structures, Corp. | Bias fiber control during wrapping of a fabric preform for a composite component |
| US9869036B2 (en) | 2015-04-13 | 2018-01-16 | Gkn Aerospace Services Structures Corporation | Apparatus and method for controlling fabric web |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2595621B1 (en) | 1988-11-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| FR2595621A1 (en) | Process for manufacturing a reinforcing structure for a component made from a composite material | |
| EP0864008B1 (en) | Method for making fibrous preforms for producing annular parts from a composite material | |
| EP0611741B1 (en) | Process for the production of a workpiece made of composite material, especially a sandwich panel, from several preforms assembled together | |
| EP2512782B1 (en) | Method for manufacturing a part made of a composite material obtained by depositing layers of reinforcing fibers urged onto a mandrel | |
| EP0767146B1 (en) | Liner for tools in contact with hot glass | |
| EP1951945B1 (en) | Method for making three-dimensional fibrous annular structures | |
| EP0970271A1 (en) | Method for producing ring-shaped fibrous structures, in particular for making parts in composite material | |
| EP0573353A1 (en) | High temperature composite material having honeycomb structure and process for its preparation | |
| EP0198776A1 (en) | Textile reinforcing layer useful in the manufacture of laminated articles, and laminated articles containing such a reinforcing layer | |
| FR2968679A1 (en) | FIBROUS STRUCTURE FOR A PIECE OF COMPOSITE MATERIAL HAVING ONE OR MORE ARCHEME-SHAPED PARTS | |
| FR2584107A1 (en) | METHOD FOR MANUFACTURING THREE-DIMENSIONAL REVOLUTION STRUCTURES BY NEEDLEING LAYERS OF FIBROUS MATERIAL AND MATERIAL USED FOR THE IMPLEMENTATION OF THE PROCESS | |
| FR2607069A1 (en) | LIGHTWEIGHT PANEL, ESPECIALLY FOR AIRCRAFT, AND METHOD OF MANUFACTURING THE SAME | |
| WO2015049449A1 (en) | Fibrous structure with grouping of floats | |
| FR2718802A1 (en) | Composite connecting rod and method for its manufacture | |
| WO2016038301A1 (en) | Preform for a curved composite stiffener for an axisymmetric part such as a collar | |
| FR2713663A1 (en) | Fabrication of axisymmetrical composite components | |
| EP3843965B1 (en) | Method for producing a composite preform for producing a composite panel with double curvature geometry | |
| EP0436419B1 (en) | Textile core, method for its manufacture and layered product obtained from such textile core | |
| FR2677442A1 (en) | CANON TUBE SHIRT OF COMPOSITE MATERIAL, MANUFACTURING METHOD THEREOF, AND CANON TUBE PROVIDED WITH SUCH A SHIRT. | |
| EP0452199B1 (en) | Method of strengthening preforms for the fabrication of heat resistant composite material parts, in particular parts in the shape of sails or panels | |
| EP0449695B1 (en) | Method of strengthening a fibrous reinforcing texture for the fabrication of a composite material part | |
| EP0931638B1 (en) | Method and apparatus for winding simultaneously several fiber strands on a support and composite structures thus produced | |
| FR2669854A1 (en) | PROCESS FOR THE PREPARATION OF A FIBROUS PREFORM OF EVOLUTIVE THICKNESS FOR MANUFACTURING A PART IN COMPOSITE MATERIAL OF THE CARBON OR CERAMIC MATRIX TYPE. | |
| FR2772748A1 (en) | METHOD FOR MANUFACTURING A SPRING OF THERMOSTRUCTURAL COMPOSITE MATERIAL | |
| EP0447317B1 (en) | Method of forming a fold or separation line during the fabrication of a composite material part |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| TP | Transmission of property | ||
| CD | Change of name or company name | ||
| TP | Transmission of property | ||
| ST | Notification of lapse |
Effective date: 20051130 |