WO2014009314A1 - Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe - Google Patents

Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe Download PDF

Info

Publication number
WO2014009314A1
WO2014009314A1 PCT/EP2013/064388 EP2013064388W WO2014009314A1 WO 2014009314 A1 WO2014009314 A1 WO 2014009314A1 EP 2013064388 W EP2013064388 W EP 2013064388W WO 2014009314 A1 WO2014009314 A1 WO 2014009314A1
Authority
WO
WIPO (PCT)
Prior art keywords
yarns
layers
layer
complex
angle
Prior art date
Application number
PCT/EP2013/064388
Other languages
English (en)
Inventor
Sung Kyu Ha
Philippe Sanial
Original Assignee
Compagnie Chomarat
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 Compagnie Chomarat filed Critical Compagnie Chomarat
Priority to EP13734770.4A priority Critical patent/EP2872685A1/fr
Publication of WO2014009314A1 publication Critical patent/WO2014009314A1/fr

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
    • B29C70/226—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 comprising mainly parallel filaments interconnected by a small number of cross threads
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04B—KNITTING
    • D04B21/00—Warp knitting processes for the production of fabrics or articles not dependent on the use of particular machines; Fabrics or articles defined by such processes
    • D04B21/14—Fabrics characterised by the incorporation by knitting, in one or more thread, fleece, or fabric layers, of reinforcing, binding, or decorative threads; Fabrics incorporating small auxiliary elements, e.g. for decorative purposes
    • D04B21/16—Fabrics characterised by the incorporation by knitting, in one or more thread, fleece, or fabric layers, of reinforcing, binding, or decorative threads; Fabrics incorporating small auxiliary elements, e.g. for decorative purposes incorporating synthetic threads
    • D04B21/165—Fabrics characterised by the incorporation by knitting, in one or more thread, fleece, or fabric layers, of reinforcing, binding, or decorative threads; Fabrics incorporating small auxiliary elements, e.g. for decorative purposes incorporating synthetic threads with yarns stitched through one or more layers or tows, e.g. stitch-bonded 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
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • B29L2031/085—Wind turbine blades
    • 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
    • D10B2403/02412—Fabric incorporating additional compounds enhancing mechanical properties including several arrays of unbent yarn, e.g. multiaxial 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the present disclosure relates to the field of technical textiles, and more specifically to textiles used to manufacture composite material, where the textile material is associated with a matrix, generally of thermosetting type.
  • a multiaxial reinforcing complex having a specific geometry enabling to optimize the mechanical properties of composite parts integrating it.
  • Such a textile complex may have multiple applications.
  • the aeronautical, automobile, or aerospace industry, the manufacturing of wind generators, and in particular of wind generator blades, or again of parts used in off-shore extraction installations should especially be mentioned, without this being a limitation.
  • textile reinforcing layers are intended to provide mechanical properties having a geometric definition directly depending on the direction of the yarns forming the textile reinforcing layer.
  • textile reinforcing layers may comprise one or several assemblies of high-tenacity yarns, following preferred directions.
  • the different yarns assemblies are distributed in an angularly balanced way.
  • a constant angular distribution may not be optimal in certain configurations, especially in composite parts which are strained by variable loads according to directions.
  • textile reinforcing structures capable of providing high mechanical properties may have various designs.
  • textile reinforcing layers based on woven yarns, where the yarns of different directions are interlaced are known.
  • NCF Non Crimp Fabric
  • the present invention thus relates to a reinforcing textile complex for composite parts, which comprises several layers of high-tenacity yarn.
  • the yarns are arranged in parallel fashion within each layer and with no crimp, and the layers are assembled together by any means, such as sawing, knitting, or gluing.
  • the complex comprises at least three different layers, that is:
  • a third layer having its yarns oriented along a direction forming a second angle with the reference direction, the first and the second angle being of opposite directions, and having an absolute value less than 60°.
  • the complex characterizes in that the second and the third layers differ by at least one parameter selected from the group comprising:
  • the present invention comprises combining several NCF-type layers by selecting parameters in relation with the geometry of the elementary layers, that is, their orientation, their mass, or their intrinsic properties by the selection of the material, to obtain a generally anisotropic material.
  • angles of the yarns of the second and third layers are different, and in particular different in absolute value by more than 5°, to obtain a measurable effect.
  • the reinforcing complex thus has an anisotropic structure, or more generally properties that cannot be deduced by symmetry around a median plane including the reference direction, since the different layers forming it are arranged with clearly different angles between one another.
  • Such a complex being anisotropic can be refered as an "unbalanced" complex.
  • the mechanical properties of composite parts integrating such reinforcing complexes can be optimized.
  • the Applicants have found that due to the difference between the angles formed by the yarns of the oriented layers and the reference direction, advantage is taken from a coupling effect between bending and twisting deformations around the reference direction, while keeping good mechanical properties.
  • the use of the third layer, arranged with an opposite orientation, contributes to increasing the torsion or flexion resistance, while keeping, due to the difference between the absolute values of the two angles, a coupling phenomenon between bend and twist phenomena.
  • such a coupling may advantageously used in elongated structures used in a fluid medium and submitted to variable loads, such as wind generators.
  • the coupling for example enables to modify the pitch angle of a wind generator blade, without requiring an active system and/or a complex mechanical connection, since the structure passively deforms according to the applied load.
  • the used high-tenacity yarns may be formed of different materials, and in particular, without this being a limitation, carbon, glass, aramide, basalt, or even natural fibers such as linen.
  • reinforcing layers having their different elementary layers or folds formed of yarns which are either identical or different, with all possible combinations between layers.
  • the complex may be used either alone, or in combination with other identical or different complexes, to form stacks.
  • a stack In the case of a stack of at least two identical complexes, solutions where all the stacked complexes have reference directions oriented in the same direction will be preferred. In other words, a stack will be formed by aligning the 0° directions of the different superposed layers.
  • association modes can be envisaged, and in particular so-called "symmetrical" stacks, where the layers in contact, from one elementary complex to the other, have the same orientation.
  • the stacking of the different complexes is performed by flipping every other complex, to have a stack symmetrical with respect to a mid-thickness plane.
  • FIG. 1 is a simplified perspective view of a textile complex according to a first embodiment of the present invention.
  • FIG. 1 is a simplified perspective view of an installation enabling to manufacture the complex of Figure 1.
  • FIG. 3 is an exploded simplified perspective view of a stack of several complexes of Figure 1.
  • FIG. 4 is a flowchart illustrating the different calculations enabling to assess the mechanical properties of composites incorporating complexes according to the present invention.
  • FIGS. 5A to 5F are graphs where the abscissas and ordinates correspond to values of orientation angles of the yarns of the second and third layers, and which have iso-level curves for the values of the following mechanical parameters:
  • FIG. 6A to 6L, 7A to 7D, 8A to 8E, 9A to 9E, 10A to 10F are Kiviat diagrams showing for five series of examples the values of different mechanical parameters compared with values of a reference example.
  • the present invention relates to a textile reinforcing complex, an example of which is schematically illustrated in Figure 1.
  • complex 1 comprises three different layers 2, 3, 4, assembled to form an element that can be individually handled, for its drape molding in a composite part manufacturing mold, alone or in association with one or other identical or different reinforcing layers.
  • reinforcing layer 1 comprises a first layer 2 illustrated as the top layer, and formed of torsion- free high-tenacity yarns 6 possibly transversely spread in the case of thin reinforcing layers, in particular based on carbon.
  • the yarns are arranged in parallel fashion in the form of sheets, while being as rectilinear as possible and with no crimp due to perpendicular weft yarns.
  • Such yarns may in particular be glass or carbon yarns, having properties selected in relation with the desired mechanical performance and for economical reasons.
  • Glass may be mentioned as an example, and especially that sold by 3B-The Fiberglass under reference SE1500, or again carbon yarns sold under trade name T700 by TORAY.
  • yarns 6 of first layer 2 are oriented along a so-called reference direction 7, which, by convention, is angle 0° for the calculation of the orientations of the other layers.
  • Complex 1 also comprises a second layer 3 formed with yarns 8 also of same tenacity, which may be identical to or different from those 6 of first layer 2.
  • Yarns 8 are oriented along a direction 9 which forms an angle ⁇ with reference direction 7.
  • Angle ⁇ is selected to be relatively small, that is, between 10° and 35°, as compared with the angles generally observed in multiaxial reinforcing layers.
  • Third layer 4 of complex 1 of Figure 1 is also formed of high-tenacity yarns 10, which may also be similar to or different from yarns 6, 8 of the two other layers.
  • the yarns are oriented along a direction 11 which forms an angle ⁇ 2 with respect to reference direction 7.
  • the direction of angle ⁇ 2 is opposite to that of angle ⁇ , so that directions 8, 11 of the second and of the third layers 3, 4 are on either side of reference direction 7.
  • angle ⁇ 2 formed by the yarns of the third layer differs, in absolute value, from angle ⁇ , and is greater, typically ranging between 25° and 60°. The influence of the different angles will be detailed hereinafter.
  • the different layers of the complex may be associated in various ways, and in particular as illustrated in Figure 1 by sawing yarns 13 according to a conventional MALIMO- type technique.
  • Other means for assembling the different layers may be used, and especially techniques using adhesive materials capable of being deposited on a fraction of the surface of the different layers.
  • melt able materials are deposited between layers before being exposed to temperature and/or pressure conditions causing their melting, and accordingly the bonding of the stacked layers with one another, may also be used.
  • such a complex may be formed on installation 30 illustrated in Figure 2.
  • Such an installation 30 comprises a conveyor 31 having the different layers deposited thereon from four successive stations 40, 50, 60, 70.
  • first station 40 delivers from a creel 41 high-tenacity yarns 42 to form the third layer of the complex of Figure 1.
  • the different yarns are conventionally brought close to the conveyor via wefting device 44 which enables to deposit successive strips 45 of parallel yarns, with orientation ⁇ 2.
  • a similar second station 50 enables to deposit sheets of yarns 55 with an orientation ⁇ corresponding to the second layer of the complex of Figure 1.
  • angle ⁇ is selected to be different from angle ⁇ 2.
  • the two oriented layers may be directed symmetrically with respect to the reference direction, in which case the two angles ⁇ 2 and ⁇ are selected to be identical.
  • the two layers are conveyed forward by conveyor 31 and reach third station 60, where they are then covered with the first layer, having its yarns delivered from third canter 61, and which are oriented along the reference direction, that is, the forward direction of conveyor 31.
  • the different superposed sheets then arrive at the level of a sawing station 70 which enables to assemble the different layers, to make the complex easier to handle on manufacturing of the composite parts that it integrates.
  • the order in which the layers are superposed within the complex may be different from that shown in Figure 2, since it may in particular be influenced by the way in which the different layers are united. Indeed, in the case of an association by sawing, according to the used sawing head, it may be more convenient for the layer having yarns along the reference direction not to be under the stack. Apart from this constraint, the different layers may be indifferently arranged. The type of sawing, the stitch and the space between stitches are selected to provide an optimal cohesion between the assembled layers.
  • mass per unit area of each of the layers may be variable, to favor the contribution of one or several layers within the complex, as will be shown by the detailed examples described hereinafter.
  • the complex according to the present invention may be used in different ways, that is, alone or in combination with other identical or different complexes.
  • complex 101 formed of three elementary layers may be superposed in several layers.
  • stack 100 is formed "symmetrically", that is, opposite layers 105, 106; 107, 108; 109, 110 from one complex to the other have the same orientation, so that stack 100 is symmetrical with respect to its plane located at mid-thickness.
  • the number of elementary layers may be adapted according to the application and to the desired mechanical properties. It is also possible to integrate within the stack other types of complexes, which have properties similar to or different from those of the complex of Figure 1, according to the desired result.
  • the complex according to the present invention enables to form composite parts which have a better mechanical performance, for a smaller weight.
  • Such mechanical properties may be either directly measured on real parts, or again be estimated by simulations implementing mathematical calculations, or based on the intrinsic properties of the materials used and the different conventional theories in laminated structure calculation.
  • Figure 5 illustrates a simplified algorithm of the different steps enabling to calculating the main mechanical properties of a composite part integrating reinforcing layer complexes according to the present invention.
  • This calculation requires knowing the properties of each of the materials of the layers forming the complexes, and in particular the longitudinal and transverse elongation modules (E x , E y ) of the materials forming the high-tenacity yarns, as well as the shear modulus (E s ) and the Poisson's coefficient (v) of the same material.
  • a compliance matrix of each layer Based on these intrinsic data and on thickness e of each of the layers, it is possible to develop a compliance matrix of each layer at a first step 201. Then, inverting this matrix provides the stiffness matrix calculated along the yarn axis. In a subsequent step 202, based on this stiffness matrix along the yarn axis, the stiffness matrix along the reference direction is calculated by using the values of angles ⁇ and 0 2 formed by the yarns of the oriented layers with respect to the reference direction. At a subsequent step 203, based on the different thicknesses and thus on coordinates Zk of each of the elementary layers, a so-called "ABD" matrix providing the twist and bend stiffnesses of the stack is determined.
  • a critical buckling load P cr is calculated. This critical buckling load calculation takes into account the values of axial load i and shear load ⁇ assessed in the active configuration of the composite part. As an example, for an application to the forming of wind generator blades, it is assumed that axial load Ni is equal to approximately 10 times shear load ⁇ .
  • the calculations of the properties of the structure may also enable, in a complementary step 301, to measure the general deformation of the composite part, based on the axial load and shear load values Ni, applied to the structure. Based on these general values, it is possible, in a subsequent step 302, to determine the deformation values of each layer, along the direction of longitudinal load Ni, according to the coordinates of each elementary layer. At a subsequent step 303, the deformation values of each of the layers can then be deduced according to the orientation of the yarns of each layer, along the direction of the yarns of each layer. Then, at step 304, the strain applied at the level of each layer can be deduced.
  • the shear strength of each layer is determined by taking into account the layers for which the rupture criterion is the most critical.
  • the shearing strengths thus determined differ according to the shear direction.
  • the fatigue is assessed by considering the fatigue properties of the matrix and of the fibers. Such fatigue predictions are made according to standard GL (German Fischer Lloyd Industrial Services GmbH) methods. The results of this calculation method are a number corresponding in logarithmic scale to a number of cycles before failure.
  • Transverse elasticity module 19 GPa
  • the used matrix has the following properties:
  • Figures 5A to 5G have been plotted from simulations calculated for glass-based composites, comprising a first 0° layer, weighting twice as much as each of the inclined layers having variable parameters as orientation angles.
  • the angles are indicated in absolute value, it being understood that they are oriented in opposite directions, on either side of the reference direction.
  • Figure 5A thus shows that the axial stiffness is maximum when the oriented layers are closest in angle to the reference direction. Conversely, the axial stiffness decreases when the directions of the oriented layers form an angle approaching 90°.
  • Figure 5B shows that the shear stiffness is maximum for a configuration where the angles of the oriented layers are close to +45° and -45° respectively. It should also be noted that for a layer having an angle close to 25°, the shear stiffness is maximum when the angle of the other layer is close to 40°, measured in the opposite direction.
  • Figures 5C and 5D show that the positive or negative shear strength is maximum when one of the layers is oriented close to 20°, for a very small inclination of the other layer.
  • Figure 5E shows that the coupling coefficient between bending and twisting is zero for angles symmetrical with respect to the reference direction. It should also be noted that for a layer which has an orientation on the order of 25°, the coupling coefficient is all the larger as the other layer is oriented with a large angle with respect to the reference direction.
  • Figure 5G shows that the fatigue criterion is maximum when the angles of the oriented layers are small.
  • the following table provides the values of the different simulated parameters for 12 examples of composite parts where the angles of the different layers are variable.
  • the mass per unit area of the layer oriented along the reference direction is twice the mass of each of the layers having non-zero orientations.
  • the last column of this table indicates a way to describe such a complex, by listing the angles formed by each of the layers, it being specified that the indexes indicate the relative weight of the concerned layer.
  • the material of the concerned layer is glass by convention.
  • the use of carbon in one of the layers is indicated by letter C following the angle of the concerned layer.
  • the following table indicates the values of d ihh D N ttt :eg av e s ea r sre n g ifferent mechanical parameters for a sandwich structure comprising two textile comp ()P alexes defined by the above table, between which a core layer having an 8-millimeter thickness is interposed.
  • Figures 6A to 6L are 12 diagrams where each of the criteria of the above table are listed for each concerned example, after having been normalized with respect to the values assessed on a conventional structure.
  • This structure is obtained from glass yarns and comprises oriented layers forming angles of +45° and -45°, and a layer at 0° which weighs twice as much as each of the oriented layers.
  • the diagrams also comprise a plot for this conventional structure, to make the comparison easier.
  • the criteria for this conventional structure are listed in the following table.
  • Figures 7A to 7D are 4 diagrams where each of the criteria of the above table are shown for each concerned example, after having been normalized in the same way as for examples 1 to 12.
  • each of the layers is formed of glass yarns, for pairs of identical angles ⁇ ⁇ 2, of +20° for the second layer and -30° for the third layer, for which the masses per unit area of each of the layers are variable.
  • the masses of the different layers are given in multiples of elementary masses per unit area for layers of a 0.125-mm thickness.
  • Figures 8A to 8E are 5 diagrams where each of the criteria of the above table are shown for each concerned example, after having been normalized in the same way as for examples 1 to 12.
  • each of the layers is formed of glass fibers, for pairs of identical angles ⁇ ⁇ ⁇ for the second layer and for the third layer, for which the materials of each of the layers are variable.
  • Figures 9A to 9E are 5 diagrams in which each of the criteria of the above table are shown for each concerned example, after having been normalized in the same way as for examples 1 to 12.
  • each of the layers is formed of glass yarns, for pairs of identical angles ⁇ ⁇ 2 of +20° or +30° for the oriented layers, for which the masses per unit area of each of the layers are variable.
  • the masses of the different layers are given in multiples of elementary masses per unit area, for a layer of a 0.125-mm thickness.
  • Figures 10A to 10F are 6 diagrams in which each of the criteria of the above table are shown for each concerned example, after having been normalized in the same way as for examples 1 to 12.
  • the present invention finds multiples applications in the field of high-performance composite materials, and especially in aeronautics, wind generator construction, and automobile, without this being a limiting list. Due to the specific structure of the associated layers, the present invention enables to optimize various mechanical parameters of composite parts, by privileging certain critical factors for certain applications, while maintaining the other factors at satisfactory levels.
  • the shear stiffness also is an important factor for the construction of wind generator blades since the blades are submitted to twisting strain mainly caused by stress due to wind, as well as to the blade inclination which influences the pitch angle, as well as to the very weight of the blade.
  • Positive and negative strengths are also important for the design of a wind generator blade since it is a rotating structure, where the direction of the stress applied to a portion of the blade reverses according to the angular position of the helix.
  • wind generator blades are particularly elongated and flexible structures, so that it is useful for them to have a good resistance to buckling.

Landscapes

  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

L'invention porte sur un complexe textile renforçant pour une pièce composite, comprenant plusieurs couches de fils à haute ténacité, lesdits fils étant disposés en parallèle à l'intérieur de chaque couche, sans frisure, à savoir : une première couche ayant ses fils orientés le long d'une direction de référence ; une deuxième couche ayant ses fils orientés le long d'une direction formant un premier angle non nul avec la direction de référence ; une troisième couche ayant ses fils orientés le long d'une direction formant un second angle avec la direction de référence, lesdits premier et second angles étant dans des directions opposées, les couches étant assemblées par couture, tricotage ou collage, caractérisé en ce que les deuxième et troisième couches diffèrent en ce qui concerne au moins un paramètre choisi dans le groupe comprenant : la valeur absolue de l'angle de la direction des fils par rapport à la direction de référence, la masse par unité de surface et le matériau formant les fils desdites couches.
PCT/EP2013/064388 2012-07-12 2013-07-08 Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe WO2014009314A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13734770.4A EP2872685A1 (fr) 2012-07-12 2013-07-08 Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1256711A FR2993284B1 (fr) 2012-07-12 2012-07-12 Complexe textile de renforcement pour pieces composites, et pieces composites integrant un tel complexe
FR1256711 2012-07-12

Publications (1)

Publication Number Publication Date
WO2014009314A1 true WO2014009314A1 (fr) 2014-01-16

Family

ID=46785719

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2013/064388 WO2014009314A1 (fr) 2012-07-12 2013-07-08 Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe

Country Status (3)

Country Link
EP (1) EP2872685A1 (fr)
FR (1) FR2993284B1 (fr)
WO (1) WO2014009314A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077805A1 (fr) 2016-10-24 2018-05-03 Sceye Sàrl Structure de dirigeable et procédé dans lequel une structure de harnais est fixée autour d'une coque
JP2019116254A (ja) * 2017-12-27 2019-07-18 株式会社イノアックコーポレーション 回転翼及びそれを用いた無人航空機
US11285707B2 (en) 2016-10-24 2022-03-29 Sceye Sa Lighter-than-air vehicle with a hull, a laminate for such hull and a method of production of such laminate
US11346499B1 (en) 2021-06-01 2022-05-31 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
US11376812B2 (en) 2020-02-11 2022-07-05 Helicoid Industries Inc. Shock and impact resistant structures
US11753754B2 (en) 2018-08-21 2023-09-12 Owens Corning Intellectual Capital, Llc Multiaxial reinforcing fabric with a stitching yarn for improved fabric infusion
US11852297B2 (en) 2021-06-01 2023-12-26 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
US11913148B2 (en) 2018-08-21 2024-02-27 Owens Corning Intellectual Capital, Llc Hybrid reinforcement fabric
US11952103B2 (en) 2022-06-27 2024-04-09 Helicoid Industries Inc. High impact-resistant, reinforced fiber for leading edge protection of aerodynamic structures
WO2024190111A1 (fr) * 2023-03-13 2024-09-19 東レ株式会社 Pale d'éolienne

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4567738A (en) * 1980-11-26 1986-02-04 Knytex, Inc. Structural fabric and method for making same
WO1996010666A1 (fr) * 1994-09-30 1996-04-11 Lockheed Martin Corporation Materiau souple destine a etre utilise dans une structure gonflable
WO1998010128A1 (fr) * 1996-09-03 1998-03-12 Mcdonnell Douglas Corporation Tissu industriel tricot chaine perfectionne et a propriete structurelle renforcee
FR2890398A1 (fr) * 2005-09-07 2007-03-09 Saint Gobain Vetrotex Etoffe complexe pour moulage par infusion
WO2010014342A1 (fr) 2008-07-31 2010-02-04 General Electric Company Procédés destinés à améliorer l'adaptabilité d'un matériau composite tissé et de composants composites en forme fabriqués à l'aide de ces procédés

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4567738A (en) * 1980-11-26 1986-02-04 Knytex, Inc. Structural fabric and method for making same
US4567738B1 (fr) * 1980-11-26 1991-08-27 Hexcel Corp
WO1996010666A1 (fr) * 1994-09-30 1996-04-11 Lockheed Martin Corporation Materiau souple destine a etre utilise dans une structure gonflable
WO1998010128A1 (fr) * 1996-09-03 1998-03-12 Mcdonnell Douglas Corporation Tissu industriel tricot chaine perfectionne et a propriete structurelle renforcee
FR2890398A1 (fr) * 2005-09-07 2007-03-09 Saint Gobain Vetrotex Etoffe complexe pour moulage par infusion
WO2010014342A1 (fr) 2008-07-31 2010-02-04 General Electric Company Procédés destinés à améliorer l'adaptabilité d'un matériau composite tissé et de composants composites en forme fabriqués à l'aide de ces procédés

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077805A1 (fr) 2016-10-24 2018-05-03 Sceye Sàrl Structure de dirigeable et procédé dans lequel une structure de harnais est fixée autour d'une coque
US11285707B2 (en) 2016-10-24 2022-03-29 Sceye Sa Lighter-than-air vehicle with a hull, a laminate for such hull and a method of production of such laminate
JP2019116254A (ja) * 2017-12-27 2019-07-18 株式会社イノアックコーポレーション 回転翼及びそれを用いた無人航空機
US11753754B2 (en) 2018-08-21 2023-09-12 Owens Corning Intellectual Capital, Llc Multiaxial reinforcing fabric with a stitching yarn for improved fabric infusion
US11913148B2 (en) 2018-08-21 2024-02-27 Owens Corning Intellectual Capital, Llc Hybrid reinforcement fabric
US11376812B2 (en) 2020-02-11 2022-07-05 Helicoid Industries Inc. Shock and impact resistant structures
US11346499B1 (en) 2021-06-01 2022-05-31 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
US11852297B2 (en) 2021-06-01 2023-12-26 Helicoid Industries Inc. Containers and methods for protecting pressure vessels
US11952103B2 (en) 2022-06-27 2024-04-09 Helicoid Industries Inc. High impact-resistant, reinforced fiber for leading edge protection of aerodynamic structures
WO2024190111A1 (fr) * 2023-03-13 2024-09-19 東レ株式会社 Pale d'éolienne

Also Published As

Publication number Publication date
EP2872685A1 (fr) 2015-05-20
FR2993284A1 (fr) 2014-01-17
FR2993284B1 (fr) 2015-02-20

Similar Documents

Publication Publication Date Title
WO2014009314A1 (fr) Complexe textile renforçant pour pièces composites et pièces composites incorporant ledit complexe
Badie et al. An investigation into hybrid carbon/glass fiber reinforced epoxy composite automotive drive shaft
Camanho et al. Stress analysis and strength prediction of mechanically fastened joints in FRP: a review
Kretsis A review of the tensile, compressive, flexural and shear properties of hybrid fibre-reinforced plastics
Pingulkar et al. Free vibration analysis of laminated composite plates using finite element method
CA2581042C (fr) Lamines a plis minces
EP3018293A1 (fr) Composant en matière composite avec noyau renforcé en fibre
Kumar et al. Postbuckling strengths of composite laminate with various shaped cutouts under in-plane shear
BR112013017815B1 (pt) Estruturas de compósito laminado e métodos para fabricar e usar as mesmas
WO2005081995A2 (fr) Semelle de longeron pour pale d'eolienne
Khashaba et al. Effect of different loading conditions on the mechanical behavior of [0/±45/90] s woven composites
Akhavan et al. Non-linear forced periodic oscillations of laminates with curved fibres by the shooting method
Samborsky et al. The SNL/MSU/DOE fatigue of composite materials database: recent trends
EP2922696B1 (fr) Tissus multiaxiaux, stratifiés polymère-fibre et corps les incorporant pour des applications de connexion
CN112481773B (zh) 三维机织结构、三维织物复合材料及工艺方法
Antoniou et al. Mechanical behavior of glass/epoxy tubes under combined static loading. Part I: Experimental
Atlıhan Buckling analysis of delaminated composite beams
Lomov et al. Mechanical behaviour of non-crimp 3D woven carbon/epoxy composite under in-plane tensile loading
Khoshbakht et al. Failure of woven composites under combined tension-bending loading
Singh et al. Cutout shape and size effects on response of quasi-isotropic composite laminate under uni-axial compression
Swaminathan et al. RETRACTED: Material property characterization of glass and carbon/vinyl ester composites
Talib et al. Mechanical properties of interlaminer Kevlar 29 and Al2O3 powder/epoxy composite plates using an analytical approach
Cannon Stress concentrations around a square cutout in a composite plate
Bruffey et al. Predicting Flexural Strength of Composite Honeycomb Core Sandwich Panels Using Mechanical Models of Face Sheet Compressive Strength
Liu et al. Experimental study on the mechanical behavior of laminates made by fiber steering: influence of fiber angle and tow width

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13734770

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 2013734770

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE