EP0283334B1 - Armature tissée pour matériau composite - Google Patents

Armature tissée pour matériau composite Download PDF

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Publication number
EP0283334B1
EP0283334B1 EP88400279A EP88400279A EP0283334B1 EP 0283334 B1 EP0283334 B1 EP 0283334B1 EP 88400279 A EP88400279 A EP 88400279A EP 88400279 A EP88400279 A EP 88400279A EP 0283334 B1 EP0283334 B1 EP 0283334B1
Authority
EP
European Patent Office
Prior art keywords
threads
thread
weft
column
row
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.)
Expired - Lifetime
Application number
EP88400279A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0283334A1 (fr
Inventor
Georges Jean Joseph Cahuzac
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Priority to AT88400279T priority Critical patent/ATE58923T1/de
Publication of EP0283334A1 publication Critical patent/EP0283334A1/fr
Application granted granted Critical
Publication of EP0283334B1 publication Critical patent/EP0283334B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/40—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads
    • D03D15/44—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads with specific cross-section or surface shape
    • D03D15/46—Flat yarns, e.g. tapes or films
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D25/00—Woven fabrics not otherwise provided for
    • D03D25/005—Three-dimensional woven fabrics
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2403/00—Details of fabric structure established in the fabric forming process
    • D10B2403/02—Cross-sectional features
    • D10B2403/024—Fabric incorporating additional compounds
    • D10B2403/0241—Fabric incorporating additional compounds enhancing mechanical properties
    • D10B2403/02411—Fabric incorporating additional compounds enhancing mechanical properties with a single array of unbent yarn, e.g. unidirectional reinforcement fabrics
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2505/00—Industrial
    • D10B2505/02—Reinforcing materials; Prepregs

Definitions

  • the present invention relates to composite materials and it relates more particularly to a woven reinforcement having a new texture for the manufacture of parts with very high resistance.
  • the composite materials consist of a reinforcement and a binder.
  • the frame is essentially made from very resistant textile fibers (glass fibers, silica fibers, carbon fibers, silicon carbide fibers, alumina fibers, aromatic polyamide fibers, etc.) and the binder can be an organic resin. or a refractory product or a metal.
  • the present invention aims to achieve a new type of frame.
  • the frame is said to be woven.
  • woven reinforcement is meant an interlacing of textile fibers which stands by itself and has the dimensional characteristics of the part made of composite material.
  • the binder required to finish the structure can be deposited in the woven reinforcement, either by liquid or by gas.
  • the liquid route consists in making a liquid impregnate penetrate into the reinforcement which, by subsequent treatment, is transformed to such an extent that the structure thus made up has the required characteristics.
  • the gaseous route is meant a process such that the armature is placed in an enclosure at a fixed temperature and pressure and is subjected concomitantly to a gas flow, the molecules of which decompose in contact with the fibers constituting the armature (chemical deposition vapor phase). After a certain time, the reinforcement plus the binder have obtained the required characteristics.
  • random D - Reinforcements with fibrous reinforcement in random directions
  • Armatures of this type are most often used as by-products of armatures in more than one direction (with the exception of hazards D) or in the sports and leisure industry. They consist of long fibers (several meters) aligned parallel to each other.
  • the reinforcing fibers can be arranged either on the three axes of a normal trihedron (triorthogonal 3D) or in radial, circumferential and longitudinal directions of the axi-symmetrical pieces (polar 3D).
  • 3D reinforcement is that, as obtained by existing methods to date, the spacing between the layers of the wires is too large to meet the needs of thin structures, which can be of the order of 1 to 3 mm.
  • the 3D due to its geometric construction, the 3D has large cavities. These most often complicate the operation of depositing the binder in a homogeneous manner, both liquid and gas.
  • the object of the invention is to provide a new armature which is particularly suitable for producing thin structures and in particular for elements for protecting spacecraft when they re-enter the atmosphere, or other applications, having very good mechanical characteristics.
  • in the direction of the reinforcements equivalent to a stack of 2D, indelaminable like a 3D, but without fibers perpendicular to the wall, that is to say an intermediate reinforcement between 2D and 3D.
  • the subject of the invention is for this purpose a frame of woven threads or fibers formed of weft threads and warp threads, characterized in that its texture is formed by a basic pattern constituted by fifteen weft threads R arranged in staggered rows. forming six vertical columns 1 to 6 of two and three wires alternately and at least five horizontal lines 1 to 5 of three wires each, and by six overlapping layers C1 to C6 of at least two parallel wires or at least twelve wires a, b , c ...
  • this pattern being enlargeable according to the thickness of the material to be produced, with an odd number of lines.
  • FIG. 4 is an example of enlarging the basic pattern, comprising seven lines and three-wire plies.
  • the principle of the 2,5D reinforcement consists in interlacing the warp and weft threads in order to obtain an indelaminable material, without thread perpendicular to the wall.
  • Figures 1 to 3 show how the warp threads are arranged in relation to "circles” which correspond to the location of the weft threads. It will be noted that these weft threads, or these "circles” are arranged in staggered rows, forming alignments in rows and columns of which one intersection in two comprises a "circle” if each "circle” is given a line number and a column number: R2 indicates the "circle” of the 2nd column and the 3rd row. Note that the total number of lines depends on the thickness of the material to be produced and that it is odd (here 5) while the number of columns is multiple of 6, because the rest of the reinforcement is obtained by repeating the previous pattern.
  • a set of pairs of parallel wires will be called "tablecloth".
  • a complete pattern consists of 6 layers of warp threads, parallel two by two.
  • FIG. 1 shows the path of the layers C1, C2 and C3
  • FIG. 2 shows the path of the layers C4, C5 and C6.
  • the first wire turns around R 2 1 then R2. It therefore connects one in three of the wires in line 2.
  • the second wire turns around R 2 3 then R2. It therefore connects one in three of the weft yarns in line 3 to one in three of the weft yarns in line 4.
  • weft threads of line 1 are connected to those of line 2 and the weft threads of line 3 to those of line 4.
  • the layers C4, C5 and C6 (FIG. 2) connect the weft threads of line 2 to those of line 3 and the weft threads of line 4 to those of line 5.
  • the path of C4 is deduced from that of the web C1 by adding 1 to the line number and 1 to the column number of the weft threads.
  • the pattern constituting this reinforcement is the simplest and most logical to obtain a material with interlaced layers.
  • Each warp thread connects two rows of adjacent wefts.
  • the arrangement of the weft threads (R) in staggered rows is required to avoid a vacuum between the warp threads and minimize the undulations of the warp threads.
  • the reinforcements according to the invention can be produced with fibers or threads of any kind (carbon, Kevlar, silica, silicon carbide, Nextel, etc.).
  • These reinforcements are either made with fibers, or of the same kind, or else by a combination of fibers or threads of different natures.
  • the sections of the fibers or threads can be identical or of different dimensions and shapes.
  • the mesh of the frame can be adapted to the request by provision provided in advance of the "circles" corresponding to the weft threads.
  • the reinforcement according to the invention can be produced in the form of a plate.
  • most of this type of product relates to circular parts of variable shape, and is particularly suitable for thin structures.

Landscapes

  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Woven Fabrics (AREA)
  • Wrappers (AREA)
  • Agricultural Chemicals And Associated Chemicals (AREA)
  • Building Environments (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)
EP88400279A 1987-02-17 1988-02-08 Armature tissée pour matériau composite Expired - Lifetime EP0283334B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT88400279T ATE58923T1 (de) 1987-02-17 1988-02-08 Gewebte armierung fuer zusammengestelltes baumaterial.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8702012 1987-02-17
FR8702012A FR2610951B1 (fr) 1987-02-17 1987-02-17 Armature tissee pour materiau composite

Publications (2)

Publication Number Publication Date
EP0283334A1 EP0283334A1 (fr) 1988-09-21
EP0283334B1 true EP0283334B1 (fr) 1990-12-05

Family

ID=9348001

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88400279A Expired - Lifetime EP0283334B1 (fr) 1987-02-17 1988-02-08 Armature tissée pour matériau composite

Country Status (11)

Country Link
US (1) US4848414A (cs)
EP (1) EP0283334B1 (cs)
JP (1) JPS63295740A (cs)
AT (1) ATE58923T1 (cs)
CA (1) CA1301593C (cs)
DE (1) DE3861199D1 (cs)
DK (1) DK164821C (cs)
ES (1) ES2018880B3 (cs)
FR (1) FR2610951B1 (cs)
IE (1) IE60050B1 (cs)
NO (1) NO163457C (cs)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2653141B1 (fr) * 1989-10-16 1992-04-17 Chaignaud Ind Materiau composite et son procede de realisation.
FR2671111B1 (fr) * 1990-12-28 1993-03-19 Chaignaud Silac Ets L A Structure textile multichaines tissee en trois dimensions et son procede de fabrication.
FR2686336B1 (fr) * 1992-01-20 1995-01-13 Aerospatiale Piece en materiau composite carbone-carbone a matrice dopee sic, resistant a l'oxydation et son procede de fabrication.
FR2691174B1 (fr) * 1992-05-15 1994-07-29 Aerospatiale Procede de tissage d'armature epaisse a couches multiples indelaminables pour materiaux composites et machine a tisser pour sa mise en óoeuvre.
FR2702222B1 (fr) * 1993-03-03 1995-05-05 Cotton Freres Cie Tissu tridimensionnel multiaxial et son procédé de fabrication.
US5616175A (en) * 1994-07-22 1997-04-01 Herecules Incorporated 3-D carbon-carbon composites for crystal pulling furnace hardware
FR2732406B1 (fr) * 1995-03-29 1997-08-29 Snecma Aube de turbomachine en materiau composite
FR2750170B1 (fr) * 1996-06-24 1998-08-21 Aerospatiale Mat d'injection de combustible pour statoreacteur fonctionnant a un nombre de mach eleve
FR2753993B1 (fr) 1996-10-01 1998-11-27 Aerospatiale Structure tubulaire tressee pour piece composite, sa realisation et ses applications
FR2759096B1 (fr) * 1997-02-04 1999-02-26 Snecma Texture multicouche liee pour materiaux composites structuraux
SE9901572D0 (sv) * 1999-05-03 1999-05-03 Astra Ab New compounds
GB2362388B (en) * 2000-05-15 2004-09-29 Smith International Woven and packed composite constructions
FR2819804B1 (fr) * 2001-01-24 2003-04-25 Eads Launch Vehicles Procede de fabrication d'une piece en carbone/carbone
FR2825699A1 (fr) 2001-06-12 2002-12-13 Eads Launch Vehicles Procede de densification et de traitement anticorrosion d'un materiau composite thermostructural
FR2861143B1 (fr) 2003-10-20 2006-01-20 Snecma Moteurs Aube de turbomachine, notamment aube de soufflante et son procede de fabrication
FR2876946B1 (fr) 2004-10-27 2007-02-02 Eads Space Transp Sas Soc Par Insert en materiau composite et son procede de fabrication, et procede de realisation d'une structure sandwich comportant un tel insert
FR2902803B1 (fr) * 2006-06-21 2008-11-14 Snecma Propulsion Solide Sa Structure fibreuse de renfort pour piece en materiau composite et piece la comportant
FR2907475B1 (fr) * 2006-10-18 2008-12-05 Messier Dowty Sa Sa Tissu composite 3d
FR2917099B1 (fr) 2007-06-06 2010-03-19 Ensait Procede de fabrication d'un materiau composite, notamment pour la protection balistique, et materiau composite obtenu.
JP2009203092A (ja) 2008-02-26 2009-09-10 Ibiden Co Ltd 容器保持部材
US7963747B2 (en) * 2009-04-02 2011-06-21 General Electric Company Braided wind turbine blades and method of making same
US9181642B2 (en) * 2012-12-07 2015-11-10 Vostech B.V. Triaxial textile armature, process for producing triaxial textile armatures and composite material part
CN104802982B (zh) * 2015-04-22 2016-10-12 北京航空航天大学 三维编织复合材料整体成型旋翼桨叶及其制作方法
FR3098544B1 (fr) 2019-07-11 2021-06-25 Safran Aircraft Engines Aube de soufflante

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2866483A (en) * 1954-06-01 1958-12-30 Fenner Co Ltd J H Textile materials for power transmission and conveyor belting
FR2395340A1 (fr) * 1977-06-20 1979-01-19 Aerospatiale Procede et machine de tissage tridimensionnel pour la realisation d'armatures tissees de revolutions creuses
US4174739A (en) * 1978-02-21 1979-11-20 Fenner America Ltd. Tubular fabric
US4312913A (en) * 1980-05-12 1982-01-26 Textile Products Incorporated Heat conductive fabric
FR2531459A1 (fr) * 1982-08-09 1984-02-10 Aerospatiale Procede et machine de realisation de pieces complexes par tissage multidirectionnel
DE3434115A1 (de) * 1984-09-17 1986-04-03 Clouth Gummiwerke AG, 5000 Köln Foerdergurt

Also Published As

Publication number Publication date
ES2018880B3 (es) 1991-05-16
DK75888D0 (da) 1988-02-15
EP0283334A1 (fr) 1988-09-21
DK164821B (da) 1992-08-24
FR2610951A1 (fr) 1988-08-19
CA1301593C (fr) 1992-05-26
FR2610951B1 (fr) 1989-05-05
IE880366L (en) 1988-08-17
DK164821C (da) 1993-01-11
DE3861199D1 (de) 1991-01-17
ATE58923T1 (de) 1990-12-15
NO880680D0 (no) 1988-02-16
IE60050B1 (en) 1994-05-18
JPS63295740A (ja) 1988-12-02
NO163457B (no) 1990-02-19
JPH0359175B2 (cs) 1991-09-09
US4848414A (en) 1989-07-18
NO163457C (no) 1990-05-30
DK75888A (da) 1988-08-18
NO880680L (no) 1988-08-18

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