WO2003068472A1 - Préformes fibreuses et leur procédé de fabrication - Google Patents
Préformes fibreuses et leur procédé de fabrication Download PDFInfo
- Publication number
- WO2003068472A1 WO2003068472A1 PCT/FR2003/000468 FR0300468W WO03068472A1 WO 2003068472 A1 WO2003068472 A1 WO 2003068472A1 FR 0300468 W FR0300468 W FR 0300468W WO 03068472 A1 WO03068472 A1 WO 03068472A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- layers
- threads
- binder
- wires
- son
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
-
- 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
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H13/00—Other non-woven fabrics
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
- D04H3/002—Inorganic yarns or filaments
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
- D04H3/02—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
- D04H3/02—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments
- D04H3/04—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments in rectilinear paths, e.g. crossing at right angles
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
- D04H3/08—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating
- D04H3/12—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with filaments or yarns secured together by chemical or thermo-activatable bonding agents, e.g. adhesives, applied or incorporated in liquid or solid form
Definitions
- the present invention relates to the production of fibrous preforms, called “dry” preforms, intended to be associated with resins for the purpose of constituting parts made of composite materials, preferably structural parts, usable in various industries and in particular in aeronautics and space industry.
- RTM resin infusion
- RI resin infusion
- Simple structures such as parts of section in i, H, T, D or u, as well as more complex structures obtained by the assembly of such elementary structures, are concerned with the present invention, and can be obtained by the resin transfer molding process.
- the raw fibrous preforms also called “dry” preforms, used in this context, must meet a certain number of criteria: - Use of continuous high performance fibers, of carbon type HR (high resistance), HM (high modulus), IM (intermediate module),
- the present invention aims to remedy these drawbacks, by providing a different production technique for such preforms, allowing optimum mechanical characteristics to be obtained while reducing costs.
- the invention essentially relates to a fibrous preform, of the type here concerned, which comprises a plurality of superimposed layers of threads, with in each layer of threads parallel to each other, the successive layers of threads being assembled together by a binder, and the threads of a layer having a direction different from that of the threads of at least one other layer.
- the threads are arranged parallel to each other in a layer, and they are deposited in successive layers allowing an appropriate alternation of the angles defining the directions of these threads, with respect for the layup. Whatever their number, the layers of threads are joined together by an appropriate binder.
- the invention therefore allows the constitution of "dry" preforms without any mechanical or textile bonding, but only by physicochemical means.
- the manufacturing costs of these preforms are thereby significantly reduced, by eliminating a textile or similar operation, such as weaving, knitting, sewing, studding or stapling, by allowing optimum mechanical characteristics to be obtained due to the non -deterioration of the threads (there are no longer any cut filaments) and respect for the linearity of these threads.
- the linearity that is to say the absence of undulation of the wires, provides better rigidity of the final composite part, and it confers, as an additional property, on the preform, a natural expansion of this preform which is lower or equal to 5%, and makes it possible to reduce the concentration of stresses when closing the mold used in the resin transfer molding process; it also allows the realization of complex shapes, without any restriction.
- binding agents or preforming binders are known, which make it possible, for example, to stiffen unidirectional woven structures.
- binders have been made on unbound textured yarns, and there have been no elements allowing to prove the permanence of multilayer structures, of simple or complex shapes, assembled by means of such binders.
- the binder which can be used for the constitution of the fibrous preforms according to the invention is, advantageously, a single-component formula based on TGMDA epoxy with a hardener based on an amine of aromatic type, for example M-CDEA, all in a methyl acetate solvent. in order to give it the appropriate viscosity during its use.
- a binder has the advantage of being fully compatible with the new "high performance" structural injection resins used in the resin transfer molding process, and of having proven itself on conventional unidirectional or two-dimensional, or more recently on multiaxial fabrics.
- the level of binder is less than 15% of the total mass of the preform.
- binders of the family indicated above makes it possible to assemble successive layers of wire, to form structures of section in i, u, T, D, etc. of variable thickness and width.
- An assembly of such elementary structures between them by the use of the same type of binder as that assembling the layers of wires of each elementary structure, allows the production of preforms of more complex geometry: bilobe shape, ladder, panel autoraidi, box, etc.
- the invention it is possible to obtain preforms of lengths greater than 5 meters and masses greater than 20 kilograms, without degrading the preforms and respecting their geometry, such preforms can be handled manually without problems.
- the invention makes it possible to directly obtain preforms with nominal dimensions, thus avoiding any retouching or other finishing operations, which also contributes to reducing costs.
- the invention will be better understood with the aid of the description which follows, with reference to the appended schematic drawing representing, by way of example, an embodiment of such a fibrous preform:
- Figure 1 is a perspective view of a section of an i-structure produced in accordance with the invention, with indication of the orientations of the wires in the different parts of the structure, and of the proportions of these wires;
- Figure 2 is a very schematic sectional view of the structure of Figure 1, with indication of the various layers of son.
- the example illustrated is a preform 1 of section in "i", with a lower sole 2 and an upper sole 3, connected by a core 4.
- the longitudinal direction is considered as 0 ° direction X of the preform 1.
- These threads are, for example, high strength carbon threads, such as of the "12000 filaments" type.
- each sole 2 or 3 there are provided layers of wires oriented at 0 °, layers of wires oriented at 90 °, layers of wires oriented at + 45 ° and layers of wires oriented at - 45 °, all the wires being parallel to the plane of the sole 2 or 3.
- the wires oriented at 0 ° represent, for example, about 43% of the total mass of the wires.
- the wires oriented at 90 °, + 45 ° and - 45 ° represent, respectively, about 19% of the total mass of the wires.
- the core 4 there are provided layers of wires oriented at 0 °, layers of wires oriented at 90 °, layers of wires oriented at + 45 ° and layers of wires oriented at - 45 °, all the wires being parallel to the plane of the core 4.
- the wires oriented in these four directions represent, respectively, 25% of the total mass of the wires.
- layers of wires belonging directly to the lower sole 2 layers of wires forming the upper part of the lower sole 2 and extending in the core 4
- layers of wires belonging specifically to the upper sole 3 layers of wires form the lower part of the upper sole 3 which come from the core 4.
- the dotted lines in FIG. 2 symbolize the layers of wires 5 oriented at 0 °.
- the solid lines 6 symbolize "blocks" each grouping a layer of wires oriented at 0 °, a layer of wires oriented at 90 °, a layer of wires oriented at + 45 ° and a layer of wires oriented at - 45 °, these four successive layers in the following order: + 45 °, 0 °, - 45 °, 90 °.
- the various superposed layers are assembled by a binder, such as that sold by the company STRUCTIL under the reference ST 1153, the binder being able to represent approximately 15% of the total mass of the preform l.
- the process implemented consists in depositing the wires parallel to one another and in successive layers, with appropriate alternation of the orientations of these wires, by bringing and depositing the binder between the layers of successive wires 5.
- the binder can be brought in and removed either by spraying or by wet transfer, in particular of the coating or licking or full bath type.
Landscapes
- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Inorganic Chemistry (AREA)
- Composite Materials (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03720611A EP1474274A1 (fr) | 2002-02-14 | 2003-02-13 | Preformes fibreuses et leur procede de fabrication |
AU2003224192A AU2003224192A1 (en) | 2002-02-14 | 2003-02-13 | Pre-formed fibres and method for production thereof |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0201860A FR2835854B1 (fr) | 2002-02-14 | 2002-02-14 | Preformes fibreuses et leur procede de fabrication |
FR02/01860 | 2002-02-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2003068472A1 true WO2003068472A1 (fr) | 2003-08-21 |
Family
ID=27620222
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2003/000468 WO2003068472A1 (fr) | 2002-02-14 | 2003-02-13 | Préformes fibreuses et leur procédé de fabrication |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1474274A1 (fr) |
AU (1) | AU2003224192A1 (fr) |
FR (1) | FR2835854B1 (fr) |
WO (1) | WO2003068472A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011077337A1 (de) * | 2011-06-10 | 2012-12-13 | Zf Friedrichshafen Ag | Kunststoff-Bauteile mit komplexer, verzweigter Struktur |
CN110341211A (zh) * | 2019-07-30 | 2019-10-18 | 中南大学 | 一种热塑性复合材料工形加筋构件的模压成型模具组件 |
CN110341210A (zh) * | 2019-07-30 | 2019-10-18 | 中南大学 | 带工字形加强筋的热塑性复合材料构件的模压成型方法 |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0361796A2 (fr) * | 1988-09-26 | 1990-04-04 | Tech Textiles International Limited | Procédé pour la fabrication d'une matière composite moulable |
WO1993004224A1 (fr) * | 1991-08-19 | 1993-03-04 | Cambridge Consultants Limited | Preforme fibreuse pour elements structuraux composites |
FR2718757A1 (fr) * | 1994-04-18 | 1995-10-20 | Aerospatiale | Procédé et machine pour la réalisation d'une armature en forme de plaque pour une pièce de matière composite. |
US5476704A (en) * | 1992-07-01 | 1995-12-19 | Hoac-Austria Flugzeugwerk Wr.Neustadt Gesellschaft M.B.H. | Plastic-composite profiled girder, in particular a wing spar for aircraft and for wind-turbine rotors |
EP0749825A2 (fr) * | 1995-06-21 | 1996-12-27 | Fuji Jukogyo Kabushiki Kaisha | Elément de structure renforcé de fibres et procédé de sa fabrication |
FR2753978A1 (fr) * | 1996-09-30 | 1998-04-03 | Inst Francais Du Petrole | Composition thermodurcissable, ses utilisations et preforme souple depliable comprenant cette composition |
WO1998034979A1 (fr) * | 1997-02-06 | 1998-08-13 | Cytec Technology Corp. | Materiau fibreux partiellement impregne de resine |
WO1999044819A1 (fr) * | 1998-03-06 | 1999-09-10 | Southwall Technologies, Inc. | Couche antireflet absorbante multicouche |
WO2002002666A1 (fr) * | 2000-06-29 | 2002-01-10 | Cytec Technology Corp. | Systemes de resine epoxyde a faible absorption d'humidite |
WO2002016197A1 (fr) * | 2000-08-25 | 2002-02-28 | Lockheed Martin Corporation | Structures de support en materiau composite avec toiles sinusoidales et leur procede de fabrication |
-
2002
- 2002-02-14 FR FR0201860A patent/FR2835854B1/fr not_active Expired - Fee Related
-
2003
- 2003-02-13 AU AU2003224192A patent/AU2003224192A1/en not_active Abandoned
- 2003-02-13 EP EP03720611A patent/EP1474274A1/fr not_active Withdrawn
- 2003-02-13 WO PCT/FR2003/000468 patent/WO2003068472A1/fr not_active Application Discontinuation
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0361796A2 (fr) * | 1988-09-26 | 1990-04-04 | Tech Textiles International Limited | Procédé pour la fabrication d'une matière composite moulable |
WO1993004224A1 (fr) * | 1991-08-19 | 1993-03-04 | Cambridge Consultants Limited | Preforme fibreuse pour elements structuraux composites |
US5476704A (en) * | 1992-07-01 | 1995-12-19 | Hoac-Austria Flugzeugwerk Wr.Neustadt Gesellschaft M.B.H. | Plastic-composite profiled girder, in particular a wing spar for aircraft and for wind-turbine rotors |
FR2718757A1 (fr) * | 1994-04-18 | 1995-10-20 | Aerospatiale | Procédé et machine pour la réalisation d'une armature en forme de plaque pour une pièce de matière composite. |
EP0749825A2 (fr) * | 1995-06-21 | 1996-12-27 | Fuji Jukogyo Kabushiki Kaisha | Elément de structure renforcé de fibres et procédé de sa fabrication |
FR2753978A1 (fr) * | 1996-09-30 | 1998-04-03 | Inst Francais Du Petrole | Composition thermodurcissable, ses utilisations et preforme souple depliable comprenant cette composition |
WO1998034979A1 (fr) * | 1997-02-06 | 1998-08-13 | Cytec Technology Corp. | Materiau fibreux partiellement impregne de resine |
WO1999044819A1 (fr) * | 1998-03-06 | 1999-09-10 | Southwall Technologies, Inc. | Couche antireflet absorbante multicouche |
WO2002002666A1 (fr) * | 2000-06-29 | 2002-01-10 | Cytec Technology Corp. | Systemes de resine epoxyde a faible absorption d'humidite |
WO2002016197A1 (fr) * | 2000-08-25 | 2002-02-28 | Lockheed Martin Corporation | Structures de support en materiau composite avec toiles sinusoidales et leur procede de fabrication |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011077337A1 (de) * | 2011-06-10 | 2012-12-13 | Zf Friedrichshafen Ag | Kunststoff-Bauteile mit komplexer, verzweigter Struktur |
US9011748B2 (en) | 2011-06-10 | 2015-04-21 | Zf Friedrichshafen Ag | Plastic component with a complex and bifurcated structure |
US9694557B2 (en) | 2011-06-10 | 2017-07-04 | Zf Friedrichshafen Ag | Plastic component with a complex and bifurcated structure |
CN110341211A (zh) * | 2019-07-30 | 2019-10-18 | 中南大学 | 一种热塑性复合材料工形加筋构件的模压成型模具组件 |
CN110341210A (zh) * | 2019-07-30 | 2019-10-18 | 中南大学 | 带工字形加强筋的热塑性复合材料构件的模压成型方法 |
CN110341211B (zh) * | 2019-07-30 | 2020-04-24 | 中南大学 | 一种热塑性复合材料工形加筋构件的模压成型模具组件 |
Also Published As
Publication number | Publication date |
---|---|
FR2835854B1 (fr) | 2005-12-30 |
AU2003224192A1 (en) | 2003-09-04 |
FR2835854A1 (fr) | 2003-08-15 |
EP1474274A1 (fr) | 2004-11-10 |
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