+

WO2017046577A1 - Matériau composite - Google Patents

Matériau composite Download PDF

Info

Publication number
WO2017046577A1
WO2017046577A1 PCT/GB2016/052821 GB2016052821W WO2017046577A1 WO 2017046577 A1 WO2017046577 A1 WO 2017046577A1 GB 2016052821 W GB2016052821 W GB 2016052821W WO 2017046577 A1 WO2017046577 A1 WO 2017046577A1
Authority
WO
WIPO (PCT)
Prior art keywords
fibre
cuts
disconnected
composite material
alignment direction
Prior art date
Application number
PCT/GB2016/052821
Other languages
English (en)
Inventor
Roger Ford
Original Assignee
Integrated Materials Technology Ltd
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 Integrated Materials Technology Ltd filed Critical Integrated Materials Technology Ltd
Publication of WO2017046577A1 publication Critical patent/WO2017046577A1/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
    • B29C70/28—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
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
    • B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
    • 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
    • B29C70/12—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of short length, e.g. in the form of a mat
    • B29C70/14—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of short length, e.g. in the form of a mat oriented
    • 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
    • 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
    • B29C2793/00—Shaping techniques involving a cutting or machining operation
    • B29C2793/0081—Shaping techniques involving a cutting or machining operation before shaping

Definitions

  • This invention relates to composite materials comprising a structure of discrete fibre domains comprising discontinuous fibres, wherein a said discontinuous fibre does not extend beyond a fibre domain, and to apparatus and methods for preparing such composite materials.
  • a method for preparing a composite material layer comprising discrete fibre domains comprising discontinuous fibres, wherein a said discontinuous fibre does not extend beyond a said fibre domain, the method comprising: providing a continuous pre-preg layer comprising reinforcing fibres dispersed in a matrix, wherein said reinforcing fibres are generally aligned in a fibre alignment direction; making a plurality of first disconnected cuts through an entire thickness of said pre-preg layer, wherein said first disconnected cuts are separated in said fibre alignment direction, and wherein said first disconnected cuts have a component perpendicular to said fibre alignment direction; and making one or more of second disconnected cuts through an entire thickness of said pre-preg layer, wherein a said second disconnected cut is made along a line which is generally parallel to said fibre alignment direction, and wherein a said line connects corresponding, respective end points of said first disconnected cuts.
  • composite materials which comprise discontinuous, aligned fibres in a matrix, whereby a fibre does not extend beyond a fibre domain, as described herein have a wider, specifiable envelope of mechanical properties than existing structural composites, and can therefore be provided in a wider range of specifiable product forms.
  • the inventors have found that it is crucial to the mechanical properties, in particular the ductile response, of composite materials in a continuous form to prepare elements with discrete fibre domains which are free of fibre bridging, i.e. fibres which span from one fibre domain to another. This has been found to be particularly important in order to decrease the peak yield stress occurring on deformation of the composite material.
  • a composite material layer comprising discrete fibre domains comprising discontinuous fibres allows for providing materials with a degree of ductile response which facilitates the detection of local damage and thereby improves safety in use of the composite material layer, reduces safety margins and the frequency of maintenance schedules.
  • fibre bridging occurs across the contiguous edges of adjacent fibre domains because of fibre misalignment in commercial pre-pregs. Fibre bridging does not occur between the in-plane faces of fibre domains because of the inter-ply matrix layer formed between plies during laminate consolidation.
  • Fibre bridging is avoided by preparing the pattern of first and second cuts into the pre-preg layer as described herein.
  • the discrete fibre domains of the composite material layer may be defined by the first and second disconnected cuts, whereby an intersection or link between a cut of the first disconnected cuts and a line along which a second disconnected cut is made may define a corner of a fibre domain.
  • a distance or average distance between one of the first cuts and a neighbouring, second one of the first cuts may thereby define a domain length of a fibre domain.
  • a distance or average distance between a line along which a second disconnected cut is prepared and a second, neighbouring line may define a domain width of a fibre domain.
  • the line along which the one or more second cuts is/are made may be at a certain distance from an edge of the pre-preg layer.
  • the width of a fibre domain is determined by the distance between the edge of the pre-preg layer and the line along which the one or more second cuts is/are made.
  • first cut and a single second cut may be made into the pre- preg layer. Two adjacent corners may then be used to define the fibre domain together with the first and second cuts. This process may then be repeated and the resulting pre-preg material may subsequently be assembled.
  • the first disconnected cuts may have a finite length L and may be made into the pre-preg layer normal to or at an angle ⁇ to the fibre alignment direction.
  • the distance (or average distance in case the first cuts are not made normal to the fibre alignment direction) along the fibre alignment direction between successive cuts of the first cuts defines the fibre domain length.
  • Methods of preparing such composite materials as described herein allow for preparing such continuous composite material layers which do not contain fibres which span from one fibre domain to a neighbouring fibre domain.
  • fibre bridging may be prevented by making the first and second cuts into the pre-preg layer.
  • the second cuts may consist of a line of disconnected cuts having a straight, elongated shape.
  • the gaps between neighbouring cuts of the second disconnected cuts are as small as required (for example a few tens of micrometres, or a few micrometres, or less), to prevent fibres from spanning from one fibre domain via such a gap into another, neighbouring fibre domain.
  • the second disconnected cuts may define perforations, holes, or other shapes.
  • Connections between the corresponding, respective end points of the cuts may be aligned substantially parallel to the fibre alignment direction.
  • the probability of fibre bridging between neighbouring fibre domains may thereby be reduced significantly. It is to be noted that the majority of fibres are parallel to the general fibre alignment direction. However, a small fraction of fibres may form a small angle of, for example, 5 degrees or less with the fibre alignment direction.
  • the angle between a fibre and the general fibre alignment direction may follow a certain distribution, for example a Gaussian distribution.
  • the angle of maximum fibre misalignment may vary between different pre-preg materials. The embodiments of the methods described herein allow for preventing fibre bridging in such cases.
  • uni-directional pre-preg layers include a significant percentage of misaligned fibres normally accepted to fall within a range of +/- 5% of the general fibre alignment direction.
  • Such fibre misalignment may facilitate the coupling of the contiguous edges of adjacent fibre domains and may activate an element of intra-ply shear within the fibre domains during axial deformation.
  • a spacing p between a said second disconnected cut and a neighbouring said second disconnected cut on a same said line is equal to or less than x / tan ⁇ , where x is a width of a said second disconnected cut and ⁇ is a threshold angle between a said fibre of said pre-preg layer and said fibre alignment direction.
  • the threshold angle may be the maximum angle of misalignment of fibres in the pre-preg layer.
  • the threshold angle ⁇ may be, for example, 5 degrees, 4.5 degrees, 4 degrees, or less than 4 degrees. This may ensure that all fibres which previously extended beyond a single fibre domain are cut off by making the second disconnected cuts into the pre- preg layer.
  • a said second disconnected cut is made such that there is substantially no fibre bridging between adjacent fibre domains.
  • the said second cut connects, in this embodiment, with the corresponding, respective ends of the first cuts, a complete severing of all the fibres which bridge the contiguous, in-plane edges of adjacent fibre domains may be ensured.
  • a method for preparing a composite material layer comprising discrete fibre domains comprising discontinuous fibres, wherein a said discontinuous fibre does not extend beyond a said fibre domain, the method comprising: providing a continuous pre-preg layer comprising reinforcing fibres dispersed in a matrix, wherein the reinforcing fibres are generally aligned in a fibre alignment direction; making a plurality of first disconnected cuts through an entire thickness of the pre-preg layer, wherein the first disconnected cuts are separated in the fibre alignment direction, and wherein the first disconnected cuts have a component perpendicular to the fibre alignment direction; and making one or more of second cuts through an entire thickness of the pre-preg layer, wherein a said second cut is made substantially continuously along a line which is generally parallel to the fibre alignment direction, and wherein a said line connects corresponding, respective end points of the first disconnected cuts.
  • making the first disconnected cuts comprises making a first row of the first cuts, and making a second row of the first cuts, wherein a said cut of the first row and a said cut of the second row are disconnected and offset in the fibre alignment direction, and wherein a said line connects the corresponding, respective end points of the first cuts of the first row and simultaneously connects the corresponding, respective end points of the first cuts of the second row.
  • a line along which the one or more second disconnected cuts are made may connect corresponding, respective end points of cuts of different, neighbouring rows simultaneously, the manufacturing process may be simplified and/or accelerated.
  • the method further comprises applying a coating to a surface of the pre-preg layer prior to making the one or more second disconnected cuts, wherein the coating is compatible with the matrix.
  • the coating (which may be, for example, a polymer coating) is considered compatible with the matrix if the coating fuses with the matrix to form a single phase.
  • the coating may wholly or partly penetrate the pre-preg layer to hold the composite layer together during and after preparing the one or more second disconnected cuts. This may be particularly important if a cut of the second disconnected cuts connects corresponding, respective end points of multiple cuts of the first disconnected cuts while spanning over an entire length of the pre-preg layer.
  • the pre-preg layer may in a case when a cut of the second cuts spans over an entire length of the pre-preg layer fall apart into two or more pieces or strips, which may in some instances be undesired.
  • this coating may be chosen to improve the mechanical properties of the resulting composite material layer. It will be appreciated that the coating may thereby be chosen dependent on the subsequent use of the composite material layer.
  • the plurality of first disconnected cuts and the one or more second cuts are made substantially simultaneously, for example prior to collecting the processed material on a single reel.
  • This embodiment may be particularly useful for laminate sheet production as a wider sheet material may be employed.
  • a coating for example a polymer coating, may in this embodiment be applied to the pre-preg layer after making the first and second cuts into the pre-preg layer, which may improve the mechanical properties of the resulting composite material layer, as outlined above.
  • the order in which the first and second cuts are made into the pre-preg layer may be changed.
  • the first disconnected cuts are made into the pre-preg layer prior to making the one or more second cuts.
  • the one or more second cuts may be made prior to the plurality of first disconnected cuts.
  • the method may further comprising applying a coating to a surface of the pre-preg layer prior to making the plurality of first disconnected cuts.
  • the coating may not fuse with the matrix such that the coating encapsulates the matrix.
  • the coating comprises a polymer coating.
  • a polymer coating may be prepared, for example from a solution and may be deposited by comparatively inexpensive deposition techniques.
  • Coating means include, but are not limited to, dipping techniques, knife coating, die extrusion, roller systems, powder coating and others. A specific coating may be preferred depending on the pre-preg type and/or coating to be applied.
  • the coating may be applied to one or both surfaces of the pre-preg layer. Coating the pre-preg layer on both surfaces may be preferable to increase strength of cohesion between adjacent fibre domains, in particular since the coating may in this way fuse with a larger volume of the matrix to form a single phase compared to applying the coating on one side of the pre-preg layer only. Whether it is preferable to apply the coating to a single side of the pre-preg layer or to both sides of the pre-preg layer may depend on the use to which the resulting composite material layer may be applied.
  • the narrow tapes or strips comprising a sequence of individual discrete fibre domains may be obtained, which, in some embodiments, are linked via the coating.
  • the tapes or strips may be collected on a set of reels by means known in the art.
  • the pre-preg layer may, in some embodiments, be covered on one side by a backing paper.
  • a backing paper This may be particularly useful in embodiments in which the matrix comprises a thermoset matrix, as the backing paper provides for an enhanced cohesion between neighbouring fibre domains.
  • the composite materials described herein may have different shapes. The shape and size of a composite material strip or layer prepared according to embodiments of the methods described herein may be controlled by the shape, and/or length, and/or distribution of cuts.
  • the pattern of cuts defining the shape may have two-dimensional translational symmetry.
  • this restriction methods described herein may provide for making materials which may comprise more than one size or shape of discrete fibre domains, which may be distributed transversely or longitudinally with respect to the fibre alignment direction and have a regular, or irregular distribution depending on the use to which the material will be applied. In this case the choice of design for the pattern of cuts may depend on the shape into which the material will be formed.
  • a hexagonal symmetry may be employed as the composite material layer may then have shearing properties which may be the same in all directions (in the plane).
  • a fibre domain has a width of approximately 4 - 60 mm and a length of approximately 50 - 150 mm.
  • these parameters may be adjusted according to specific application of the composite material layer.
  • the cuts may be made into the pre-preg layer such that the resulting fibre domains may have a rectangular, trapezoidal, rhomboidal or other shape.
  • the first disconnected cuts are substantially parallel.
  • the cuts may not be parallel to each other, or only some of the cuts may be parallel to each other. Preparing cuts which are substantially parallel may simplify the manufacturing process.
  • an angle between a said first disconnected cut and a said line along which the one or more second cuts are made is substantially 90 degrees.
  • a composite material layer may be prepared whereby the shape of a fibre domain is substantially rectangular or trapezoidal.
  • the shape of a domain may be rhomboidal. Therefore, in a preferred embodiment of the method, an angle between one or more of the first cuts and a said line is less than 90 degrees. It will be appreciated that a combination of rectangular-shaped fibre domains, rhombus-shaped, trapezoidal-shaped, or otherwise shaped fibre domains may be prepared in a composite material strip, as required.
  • fibre domains with different lateral dimensions.
  • “Lateral” refers here to a plane of the pre-preg layer.
  • two or more of the fibre domains each have different domain lengths and/or different domain widths and/or different domain shapes. This may be preferable depending on, for example, a specific shape of an object the composite material layer may be applied to. This may be achieved by varying the length of some of the cuts, or, equivalently, by varying the distance between some of the lines along which the second cuts are made.
  • the order in which the cuts are prepared may vary.
  • a first set of (first or second) disconnected cuts is prepared across the width of the pre-preg layer, one cut for each row of cuts.
  • a second set of cuts may then be prepared across the width of the pre-preg at a different position, one further cut for each row or a separate row.
  • cuts may be prepared for one entire row before preparing cuts for one or more other rows.
  • alternative sequences for preparing cuts in the pre-preg layer may be used.
  • the coating comprises a polymer coating.
  • the polymer coating may be compatible with the matrix, i.e. it may fuse with the matrix to form a single phase.
  • Coating techniques include, but are not limited to, dipping techniques, knife coating technologies, slot die technologies, roller systems, powder scattering, hot-melt technologies, and others. It will be appreciated that a specific coating technique may be preferred depending on the type of pre-preg and/or coating to be applied to the pre-preg.
  • the matrix comprises a thermoplastic matrix or a thermoset matrix.
  • the thermoplastic matrix may comprise a thermoplastic polymer, such as, for example, a polyamide (PA), polyether ether ketone (PEEK), poly ether ketone ketone (PEKK), polyaryletherketone (PAEK), polyethersulfone (PES), polyphenylene sulphide (PPS), polyethylene terephthalate (PET), polybutylene terephthalate (PBT), polyvinyl chloride (PVC), polystyrene (PS), ethylene vinyl acetate (EVA), poly(methyl methacrylate) (PMMA), acrylonitrile butadiene styrene (ABS), polylactic acid (PLA), polybenzimidazole (PBI), polycarbonate (PC), polyethylene (PE), polypropylene (PP), polytetrafluoroethylene (PTFE), and others.
  • the thermoset matrix may comprise, for example, epoxy,
  • the reinforcing fibres may be, but are not limited to, glass fibres, carbon fibres, cellulose fibres, high strength polymeric fibres such as aramid or ultra-high molecular weight (UHMW) polyethylene and cellulose fibres, and other fibres.
  • the composite layer may be comprised of a matrix with a combination of fibre types.
  • the first disconnected cuts are substantially perpendicular to the alignment direction of the reinforcing fibres.
  • corresponding, respective end points of the first disconnected cuts are aligned in the fibre alignment direction such that the second cuts are prepared in the fibre alignment direction to thereby minimise the probability of fibre bridging between adjacent fibre domains.
  • fibre bridging is prevented where the second cuts are prepared continuously along the entire length of the pre-preg layer.
  • the continuous pre-preg layer comprises one or more plies each comprising reinforcing fibres dispersed in a matrix. This may advantageously allow for a rapid way of producing a composite material layer as described herein, which is more balanced with regard to its mechanical properties.
  • a first said fibre alignment direction of fibres in a first said ply has a component which is perpendicular to a second said fibre alignment direction of fibres in a second said ply, in particular wherein the first and second fibre alignment directions of the first and second plies, respectively, are perpendicular to each other.
  • This may advantageously allow for a rapid way of producing a composite material layer as described herein, which is even more balanced with regard to its mechanical properties.
  • the second cuts may be advantageous to make the second cuts continuously into the pre-preg layer in order to avoid fibre bridging in all plies, in particular as the general fibre alignment directions in the different plies may not be parallel to each other. If in these embodiments the second cuts were made discontinuously into the pre- preg layer, the second cuts may allow for avoiding fibre bridging in one or more plies, but not necessarily all plies if the general fibre alignment directions are not parallel to each other in all plies.
  • the plies may have a hybridised composition involving more than one fibre type.
  • the combination of types of fibres and matrices for each of the plies, and the combination of respective plies may be determined by the specific requirements of the composite material.
  • a single ply has a thickness of about 0.1 - 0.3 mm. But plies with other thicknesses may be provided depending on the subsequent use of the composite material layer.
  • the composite material layer comprises one or more fibre types which are hybridised. If a combination of fibres with different mechanical properties is used (for example, relatively softer and stronger fibres and/or more or less extensible fibres), the property (or properties) of one of the fibre types may override that of the others such that a single (or a few) fibre types may dominate the mechanical properties of the composite material layer when the fibre are provided in a continuous form (i.e. bridge from one fibre domain to one or more other fibre domains). For example, in a composite material layer with continuous fibres, the fibre type with the lowest extension capability dominates the extension capability of the whole composite material layer.
  • the composite material layer exhibits a blend of properties derived from each of the fibre types used.
  • Embodiments described herein therefore allow for obtaining a larger variety of composite material layer exhibiting different, tuneable mechanical properties.
  • the cuts may be prepared in the pre-preg layer using laser light.
  • this may be the preferred technique due to being a non-contact technique, its reliability and/or the short time in which cuts may be prepared in the pre-preg layer, other techniques may be exploited, and the preferred technique may depend on the type of pre-preg to be cut. Therefore, in a preferred embodiment of the method, the first and/or second cuts are made using rotary die cutting, flat die cutting, shear cutting, crush slitting, mechanical fracture by controlled flexing or impact or, preferably, laser-cutting.
  • Composite materials layers comprising discrete fibre domains prepared with any of the above methods may in some embodiments subsequently be assembled as required before being heated and/or consolidated to produce semi-finished materials of various forms, such as, for example, a sheet, profile, rod or tube.
  • a composite material layer comprising a plurality of discrete fibre domains comprising discontinuous, reinforcing fibres dispersed in a matrix, wherein a said discontinuous, reinforcing fibre does not extend beyond a said fibre domain, wherein a plurality of first disconnected cuts and one or more second disconnected or continuous cuts in said composite material layer define said fibre domains, wherein said first cuts are separated in a fibre alignment direction of said composite material layer, wherein said first cuts have a component perpendicular to said fibre alignment direction, wherein a said second cut is provided along a line which is substantially parallel to said fibre alignment direction, and wherein a said line connects corresponding, respective end points of said first cuts.
  • discrete fibre domains of the composite material layer may be defined by the first and second cuts, whereby intersections or links between the first cuts and a said line along which a said second cut is made may define corners of the fibre domains.
  • a fibre domain may be defined by the first cuts, the second cut as well as the edge of the composite material layer.
  • a distance or average distance between a cut of the first cuts and a neighbouring cut of the first cuts may thereby define a domain length of a fibre domain.
  • a distance or average distance between a line along which a second cut is prepared and a second, neighbouring line may define a domain width of a fibre domain.
  • the domain width may be defined by a distance or average distance between the second cut and an edge of the composite material layer.
  • Such a composite material layer may be free from fibre bridging between adjacent fibre domains, resulting in advantageous properties of the composite material layer, as outlined above.
  • a composite material layer comprising: a plurality of discrete fibre domains comprising discontinuous, reinforcing fibres dispersed in a matrix, in particular a thermoplastic or thermoset matrix, wherein a said discontinuous fibre does not extend beyond a said fibre domain; and a coating, in particular a polymer coating, on at least a first surface of the fibre domains configured to fuse with said matrix to connect the fibre domains to each other to form the composite material layer.
  • the coating may thereby improve the mechanical properties of the pre-preg layer, e.g. by strengthening the structure.
  • a composite material layer comprising: a plurality of discrete fibre domains comprising discontinuous, reinforcing fibres dispersed in a matrix, in particular a thermoplastic or thermoset matrix, wherein a said discontinuous fibre does not extend beyond a said fibre domain; and a coating, in particular a polymer coating, which encapsulates said matrix.
  • the coating may hereby not fuse with the matrix to form a single phase such that the coating encapsulates the matrix.
  • Figure 1 shows a schematic top-view of a composite material layer according to a first embodiment of the present invention
  • Figure 2 shows a schematic top-view of a composite material layer according to a second embodiment of the present invention
  • Figure 3 shows a schematic top-view of a composite material layer according to a third embodiment of the present invention.
  • Figure 4 shows a schematic cross-sectional side view of a composite material layer according to a fourth embodiment of the present invention
  • Figure 5 shows a schematic top-view of a composite material layer according to a fifth embodiment of the present invention.
  • Figures 6a - c show schematic top-views of composite material layers according to a sixth embodiment of the present invention.
  • Figures 7a - c show distribution of fibres along the fibre alignment direction in a pre-preg layer and the relation between the spacing, p, between adjacent disconnected cuts in the line of cuts comprising a second cut and the width of such cuts according to embodiments of the present invention
  • Figure 8 shows a schematic cross-sectional side-view of a composite material layer according to embodiments of the present invention.
  • Figures 9a and 9b show a flowchart of a method and a schematic of an apparatus, respectively, for preparing a composite material layer according to a first preferred embodiment of the present invention
  • Figures 10a, 10b and 10c show a flowchart of a method for preparing a composite material layer, a schematic cross-sectional side view of the resulting composite material layer and an apparatus for preparing a composite material layer according to a second preferred embodiment of the present invention
  • Figures 11 a and 1 1 b show a flowchart of a method and an apparatus, respectively, for preparing a composite material layer according to a third preferred embodiment of the present invention.
  • Figure 12 shows a schematic cross-sectional side view of a composite material layer prepared according to the third preferred embodiment of the present invention.
  • embodiments of the present invention aim to provide aligned discontinuous fibre materials which offer the needed balance of mechanical and deformation properties required for commercially acceptable structural applications.
  • a method comprising: providing a continuous pre-preg layer comprising reinforcing fibres dispersed in a matrix, where the reinforcing fibres are generally aligned in a fibre alignment direction; and making a plurality of sets of disconnected T cuts through an entire thickness of the pre-preg layer. Successive sets of disconnected T cuts are separated in said fibre alignment direction, and the disconnected T cuts have a component perpendicular to the fibre alignment direction.
  • the method preferably also involves making one or more continuous P cuts through an entire thickness of said pre-preg layer. A continuous P cut is made along a line which is generally parallel to the fibre alignment direction, and a continuous P cut connects corresponding, respective end points of the sets of disconnected T cuts.
  • Methods of preparing such composite materials as described herein allow for preparing such continuous composite material layers which do not contain fibres which span from one fibre domain to a neighbouring fibre domain.
  • P cuts into the pre-preg layer along lines which are generally parallel to the fibre alignment direction the probability of fibres spanning from one fibre domain to a neighbouring fibre domain is removed.
  • the discrete fibre domains of the composite material layer may then be defined by the sets of disconnected T cuts and continuous P cuts, whereby an intersection or link between a T cut and a P cut defines a corner of a fibre domain.
  • a distance or average distance between one set of T cuts and a neighbouring, set of T cuts thereby defines a domain length of a fibre domain.
  • a distance between a continuous P cut and a neighbouring continuous P cut thereby defines a domain width of a fibre domain.
  • the line along which the one or more continuous P cuts is/are made may be at a certain distance from an edge of the pre-preg layer.
  • the width of a fibre domain is determined by the distance between the edge of the pre-preg layer and the line along which the one or more P cuts is/are made.
  • the T cuts may not be made normal to the fibre alignment axis, but at an angle ⁇ to the fibre alignment direction.
  • the disconnected T cuts may be substantially parallel.
  • the cuts may not be parallel to each other, or only some of the cuts may be parallel to each other.
  • These effectively continuous P cuts may take the form of slots, perforations or holes of varied shape.
  • T cuts may precede P cuts and visa-versa depending on the application for which the material is intended. If narrow tape material is required for winding operations, P cuts may precede or follow T cuts whilst P and T cuts may be introduced simultaneously if wide width material is required for sheet or panel applications.
  • the P and T cuts will be the origin of voids in the pre-preg layer, which should be minimised and generally not exceed 0.5% of the pre-preg volume if laminate or shaped part quality is to be retained.
  • Calculations of the potential void levels created by the required sets of T and P cuts are laid out in Tables 1 and 2 below. These calculations are based on laser cuts having a specific width in these examples of 0.01 mm, 0.03mm, 0.05mm, 0.07mm and 0.09mm. In these examples, the fibre domains have a length which varies from 10mm to 160mm. It will be understood that these values are only examples.
  • Table 2 Calculated % voids associated with sets of P cuts comprising lines of linear cuts which effectively remove fibre bridging between adjacent fibre domains for the case where misalignment within the fibres of the composite pre-preg layer does not exceed 5 degrees.
  • Table 3 calculated % voids associated with embodiments of the method in which the second cuts are made discontinuously along a line into the pre-preg layer.
  • the total level of voids created using embodiments of the method in which the P cuts are genuinely continuous is that laid out in Table 1 , because here the set of P cuts separates the pre-preg layer into a set of individual discrete fibre domains linked through an applied coating.
  • the method of severing the fibres within the pre-preg layer may include, but is not limited to, rotary or flat die cutting, ultrasonic assisted blade cutting, crush slitting or a highly focused beam of high energy radiation.
  • mechanical means including, but not limited to controlled flexing or impact may be used to fracture the fibres.
  • the cuts may be prepared in the pre-preg layer using pulsed laser radiation, a non- contact technique that offers the long term reliability desirable for a continuous manufacturing process, but other techniques may be employed, the preference depending on the type of pre- preg to be processed.
  • the reinforcing fibres of the composite layer may be, but are not limited to, glass fibres, carbon fibres, cellulose fibres, high strength polymeric fibres such as aramid or ultra-high molecular weight (UHMW) polyethylene and cellulose fibres, and other fibres.
  • the composite layer may also have a hybridised composition involving more than one fibre type. The combination of types of fibres and matrices for each of the plies, and the combination of respective plies may be determined by the specific manner in which the composite material will be used.
  • the matrix may comprise a thermoplastic matrix or a thermoset matrix.
  • the thermoplastic matrix may comprise any of the polymers listed in the Summary of the Invention.
  • the material comprises a plurality of plies.
  • the composite material layer may comprises two or more plies, each comprising reinforcing fibres dispersed in a matrix with the sequence of the fibre alignment directions in the stacked plies being determined by the mechanical performance required of the resulting material.
  • the embodiment of the method will be restricted to the use of genuinely continuous P cuts with the T cuts.
  • a coating is applied to a surface of the pre-preg layer wherein the coating is compatible with the matrix.
  • the coating for example a polymer, is considered compatible with the matrix if the coating can fuse with the matrix to form a continuous phase.
  • the coating may be applied to one or both surfaces of the pre-preg layer. Coating the composite material layer on both surfaces may be preferable to increase the cohesion between adjacent discrete fibre domains. Apart from ensuring cohesion between axially adjacent discrete fibre domains, it will be appreciated that the coating may also be chosen to modify the properties of the resulting composite material layer. The degree to which the fibre volume fraction of the composite layer will be reduced by coating will depend on the coating thickness. For materials employed in structural applications it is desirable that the fibre volume fraction should not fall below 0.55. The maximum permissible thickness of the coating will therefore depend on the fibre volume fraction of the uncoated composite material layer. Accordingly, it will be appreciated that the choice of coating may depend on the subsequent use of the composite material layer.
  • the coating may be applied to the pre-preg layer before or after the introduction of the sets of T and P cuts depending on the chosen embodiment of the method.
  • coating means may include, but are not limited to, dipping techniques, knife coating, die extrusion, roller systems, film lamination, powder coating and others. It will be appreciated that a specific coating technique may be preferred depending on the pre-preg type and/or the coating to be applied. Preferably, the coating is compatible with the composite matrix, effectively fusing with the matrix to form a continuous matrix phase.
  • composite materials described herein may comprise different shapes of discrete fibre domains which will be defined by the shape, and/or length, and/or distribution of the sets of T and P cuts. There may be reasons for adjusting the size and shape of discrete fibre domains to achieve the desired balance of the mechanical and deformation properties or situations where maximising material usage is important.
  • the pattern of cuts defining the shape of the discrete fibre domains must have two-dimensional translational symmetry.
  • the methods described herein may provide for making materials which may comprise more than one size or shape of discrete fibre domains, which may be distributed transversely or longitudinally with respect to the fibre alignment direction and have a regular, or irregular distribution depending on the use to which the material will be applied.
  • the choice of design for the pattern of cuts may depend on the shape into which the material will be formed.
  • the sets of discontinuous T* cuts and the set of effectively continuous P cuts, which connect with the ends of the said T cuts are simultaneously introduced into a wide tape of UD pre-preg material by means well known in the art, prior to collecting the processed material on a single reel, by means well known in the art.
  • This embodiment is particularly useful for laminate sheet production
  • the sets of discontinuous T cuts are introduced into a supply of UD pre-preg material by means well known in the art, after which the pre-preg material is coated with a compatible polymer by means well known in the art.
  • This coating may be applied to a single or both sides of the pre-preg, depending on the use to which the resulting material will be applied.
  • a set of continuous P cuts which connect with the ends of the sets of T' cuts, are made in the coated pre-preg, using means well known in the art, before collecting a set of narrow tapes, comprised of axially linked individual discrete fibre domains on a set of reels by means well known in the art.
  • These narrow tapes comprising a sequence of individual discrete fibre domains linked by the coating are particularly suitable for tape placement and winding operations.
  • a supply of UD pre-preg material is slit into a set of narrow tapes of the required fibre domain width by means well known in the art, after which an individual narrow tape is coated with a compatible polymer, which has a melt temperature somewhat lower than that of the pre-preg matrix, using means well known in the art.
  • the pre-preg tape is given a coated sleeve without fusion of the matrix and coating taking place his narrow coated tape is then subjected to periodic mechanical stress, which fractures the fibres, before the tape is collected on a reel by means well known in the art.
  • a composite material layer comprising a plurality of discrete fibre domains comprising discontinuous, reinforcing fibres dispersed in a matrix, wherein a said discontinuous, reinforcing fibre does not extend beyond a said fibre domain, wherein a plurality of disconnected T cuts and one or more continuous or effectively continuous P cuts in said composite material layer define said discrete fibre domains, wherein said T cuts are separated in a fibre alignment direction of said composite material layer, wherein said T cuts have a component perpendicular to said fibre alignment direction, wherein a said P cut is provided along a line which is substantially parallel to said fibre alignment direction, and wherein a said line connects corresponding, respective end points of said T cuts.
  • discrete fibre domains of the composite material layer may be defined by the T and P cuts, whereby intersections or links between the T cuts and a said line along which a said P cut is made may define corners of the fibre domains.
  • a fibre domain may be defined by the T cuts, and the P cut as well as the edge of the composite material layer.
  • a distance or average distance between a set of T cuts and a neighbouring set of T cuts may thereby define a domain length of a fibre domain.
  • a distance or average distance between a line along which a P cut is prepared and its neighbouring line may define a domain width of a fibre domain.
  • the domain width may be defined by a distance or average distance between the P cut and an edge of the composite material layer.
  • Such a composite material layer may be free from fibre bridging between adjacent fibre domains, resulting in advantageous properties of the composite material layer, as outlined above.
  • Composite materials layers comprising discrete fibre domains prepared with any of the above methods may in some embodiments subsequently be assembled as required before being heated and consolidated to produce materials of various forms, such as, for example, a sheet, profile, rod or tube.
  • a supply of 150mm width PEKK/AS4 carbon fibre pre-preg, 61 % fibre by volume was fed under controlled tension through a roller system consisting of rotating datum guides and a pair of parallel un-driven rollers, which define the focal plane of a high speed Cambridge Technology galvanometer scanner.
  • a SPI SP -200C 200W laser, wavelength 1075 nm, beam diameter 5+/-0.7mm and M 2 1.1 was then focussed via an 80mm f-theta lens to deliver a minimum focal spot of 0.032mm at the work piece to introduce the sets of T cuts into the pre-preg.
  • the resulting processed pre-preg was then drawn through a 150mm width heated extrusion die, supplied with PEEK resin by a co-rotating twin screw extruder, which could coat the pre-preg on one or both sides.
  • the set of continuous P cuts was introduced into the coated tape by a multiple shear slitting unit.
  • the resulting slit tapes consisting of a linked sequence of individual discrete fibre domains, were then collected on a set of driven reels with a minimum core size of 100mm. Integration of the laser power, the galvanometer scanner movement, the polymer extrusion rate and the line speed was provided by a CNC system.
  • this shows a schematic top-view of a processed composite material layer [100] comprising a sequence of rectangular discrete fibre domains [102], where A is the fibre alignment direction, L is the length and W the width of an individual domain.
  • Figure 2 shows a schematic top-view of a processed composite material layer [200] comprising a sequence of rectangular discrete fibre domains of different domain lengths [201 & 204], where A is the fibre alignment direction.
  • Figure 3 shows a schematic top-view of a processed composite material layer [300] comprising a sequence of rhombic discrete fibre domains [302], where A is the fibre alignment direction.
  • Figure 4 shows a schematic longitudinal cross-sectional view of stacked, processed composite material layers [400] comprising discrete fibre domains [402] where A is the fibre alignment direction.
  • Figure 5 shows a schematic top-view of a processed composite material layer [500] comprising domains [502, 504] with different shapes.
  • some domains have a rectangular shape [504]
  • some domains have a rhombic (trapezoidal) shape [502].
  • many other shapes and/or combination of shapes may be desirable, depending on the specific application in which the composite material layer is used.
  • FIGS 6a to 6c show schematic top-views [600] of processed composite material layers illustrating the T cuts 602 and P cuts 604 used to create discrete fibre domains, where A is the fibre alignment direction. Whilst T cuts 602 are always continuous, P cuts may in some cases be discontinuous where the spacing between individual component cuts of the P cut is sufficiently small to ensure that no fibre bridging between adjacent fibre domains occurs.
  • Figures 7a shows an example of the general distribution of misaligned fibres about the fibre alignment direction in a commercial pre-preg layer, where a is the angle of fibre misalignment.
  • Figure 7b illustrates the spacing required between component cuts of effectively continuous P cuts [702] where x is the width of the component cuts and p is the desired spacing.
  • Figure 7c illustrates the relationship between the required spacing between component cuts of effectively continuous P cuts and the width of the component cuts for the case where misalignment within the fibres of the composite pre-preg layer does not exceed 5 degrees.
  • Figure 8 shows a composite material layer [800] which comprises a first ply [802] and a second ply [804].
  • A indicates the general fibre alignment direction in each of the plies [802 & 804].
  • the fibre alignment directions of the plies [802 & 804] are perpendicular to each other.
  • the composite material layer which may be prepared this way allows for a more rapid manufacture for producing a material with more balanced mechanical properties.
  • Figure 9a shows a flowchart according to the first preferred embodiment of the method of the present invention.
  • the pre-preg layer is unwounded at step [902].
  • T and P cuts are inserted into the pre-preg layer at step [904].
  • the pre-preg is then rewound at step [906].
  • Figure 9b is a schematic diagram of the apparatus [910] required for processing a composite material layer according to the first preferred embodiment of the method of the present invention where a winding unit [912] is loaded with a package of the composite material layer [914] that is fed through a roller system [916] which positions it precisely under a galvo-scanner [920] which delivers appropriately pulsed radiation from a laser [918] to sever the fibres of the composite layer before collecting a sheet of processed material [922] on a further winding unit [912].
  • B is the machine direction.
  • Figure 10a shows a flowchart according to the second preferred embodiment of the method of the present invention.
  • the pre-preg layer is unwounded at step [1002].
  • T cuts are then inserted into the pre-preg layer using a laser at step [1004].
  • the material is then coated with a coating at step [1006].
  • P cuts are then inserted by shear slitting at step [1008], before the material is rewound at step [1010].
  • Figure 10b is a schematic drawing of the cross section of an individual fibre domain [1012] according to the second preferred embodiment of the method of the present invention showing the composite layer [1016] and its coating [1014].
  • Figure 10c is a schematic diagram of the apparatus [1020] required for processing a composite material layer according to the second preferred embodiment of the method of the present invention.
  • a winding unit [1022] is loaded with a package of the composite material layer which is fed through a roller system [1024] which positions it under a galvo-scanner [1228] which delivers appropriately pulsed radiation from a laser [1226] to sever the fibres of the composite layer.
  • the material then passes through a coating unit [1030] which is fed by an extruder [1032].
  • the coated material then passes through a temperature controlled water bath [1034] and a slitting unit [1036] before being collected as sequences of individual discrete fibre domains [1038] on a further winding unit [1022].
  • B is the machine direction.
  • Figure 1 1 a shows a flowchart according to the third preferred embodiment of the method of the present invention.
  • the pre-preg layer is unwound at step [1 102].
  • P cuts are then inserted into the pre-preg layer, in this example, by shear slitting at step [1 104].
  • the material is then coated with a coating at step [1 106].
  • T cuts are then inserted, in this example, into the layer using a mechanical fracturing process at step [1 108].
  • the layer is then rewound at step [1 1 10].
  • Figure 1 1 b is a schematic diagram of the apparatus [1 120] required for processing a composite material layer according to the third preferred embodiment of the method of the present invention.
  • a winding unit [1 122] is loaded with a package of the composite material layer [1 124] which passes through a slitting unit [1 126].
  • the slit material is then fed through a coating unit [1 128] which is fed by an extruder [1 130].
  • the coated material is then passed through a temperature controlled water bath before entering mechanical fracturing units [1 134 & 1 138] and being collected as sequences of individual discrete fibre domains on a further winding unit [1 122].
  • B is the machine direction.
  • Figure 12 is a schematic drawing of the cross section of an individual fibre domain [1200] according to the third preferred embodiment of the method of the present invention showing the composite material layer [1204] and the encapsulating coating [1202]. Variants
  • One variant of the above described technique involves coating the pre-preg and impacting the coated pre-preg to prepare the composite material layer with discrete fibre domains.
  • a method of preparing discrete fibre domains comprising discontinuous fibres in a composite material strip (or layer), the method comprising: providing a continuous fibre reinforcement tow; impregnating said continuous fibre reinforcement tow with a matrix resin; and subjecting said impregnated continuous fibre reinforcement tow to an impact force which is controlled to fracture said fibres to obtain discrete fibre domains while preserving said matrix such that said discrete fibre domains are connected to each other via said matrix, wherein a said discontinuous fibre does not extend beyond a said fibre domain.
  • Fibre bridging may be prevented in this method due to the fracturing of the fibres in areas which define boarders of a fibre domain.
  • the continuous fibre reinforcement tow may be of a specific Tex which may be chosen dependent on the specific application of the composite material.
  • the continuous fibre reinforcement tow or pre-preg layer may be coated with a coating, for example a polymer coating.
  • the coating may not fuse with the matrix (or matrix resin) to form a single phase.
  • Precursor elements obtained by impregnating the continuous fibre reinforcement tow may be subjected to a period impact while the tow is moved under an impact unit.
  • the impactor may be moved over the impregnated elements to obtain the desired fibre domains at specific locations of the impregnated elements.
  • the fibres are thereby fractured whilst leaving the surrounding matrix intact, such that the matrix bonds the fibre domains to each other. It will be appreciated that the force of impacting the impregnated continuous fibre reinforcement tow to fracture fibres without fracturing the matrix should be adjusted depending on the specific material combination of fibres and matrix.
  • the method further comprises shaping the impregnated continuous fibre reinforcement tow prior to said fracturing, wherein the shaping comprises: feeding the impregnated continuous fibre reinforcement tow through a heated die having a cross-section, in particular a rectangular cross-section, which the impregnated continuous fibre reinforcement tow is to adapt; and cooling and straightening the impregnated continuous fibre reinforcement tow. Shaping the impregnated continuous fibre reinforcement tow may be preferably performed prior to the fracturing as the shaping may be easier on a pristine impregnated continuous fibre reinforcement tow.
  • Adequate residence time may be provided in an impregnation unit to ensure complete impregnation before the impregnated tow passes through the heated die and is then cooled and straightened.
  • the cooling comprises controlling a temperature in a water bath for cooling the impregnated continuous fibre reinforcement tow. This may be preferable as the cooling rate may be precisely controlled using the water bath.
  • the fibre domain size, and/or shape, and/or pattern prepared with the "impacting" method may be equivalent to those patterns which may be prepared using the "cutting" method outlined above.
  • Composite materials strips comprising discrete fibre domains prepared with any of the above methods may then be assembled as required before being heated and consolidated to produce semi-finished materials of various forms, such as, for example, a pre-preg, rod or tube.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

L'invention concerne un procédé pour préparer une couche (400, 500, 600) de matériau composite, ladite couche (400, 500, 600, 700, 800) de matériau composite comprenant des domaines discrets (402, 502, 602, 702) de fibres, comprenant des fibres discontinues, une dite fibre discontinue ne s'étendant pas au-delà d'un dit domaine de fibres, le procédé consistant à : prendre une couche continue de préimprégné comprenant des fibres de renforcement dispersées dans une matrice, lesdites fibres de renforcement étant généralement alignées dans une direction d'alignement de fibres ; réaliser une pluralité de premières découpes non reliées à travers l'épaisseur entière de ladite couche de préimprégné, lesdites premières découpes non reliées étant séparées dans ladite direction d'alignement de fibres et lesdites premières découpes non reliées présentant une composante perpendiculaire à ladite direction d'alignement de fibres ; et réaliser une ou plusieurs deuxièmes découpes non reliées à travers l'épaisseur entière de ladite couche de préimprégné, une deuxième découpe non reliée étant réalisée le long d'une ligne qui est généralement parallèle à ladite direction d'alignement de fibres et une dite ligne reliant des points d'extrémité correspondants respectifs desdites premières découpes non reliées.
PCT/GB2016/052821 2015-09-14 2016-09-13 Matériau composite WO2017046577A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1516245.6 2015-09-14
GBGB1516245.6A GB201516245D0 (en) 2015-09-14 2015-09-14 Composite material

Publications (1)

Publication Number Publication Date
WO2017046577A1 true WO2017046577A1 (fr) 2017-03-23

Family

ID=54363132

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2016/052821 WO2017046577A1 (fr) 2015-09-14 2016-09-13 Matériau composite

Country Status (2)

Country Link
GB (1) GB201516245D0 (fr)
WO (1) WO2017046577A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108846181A (zh) * 2018-05-31 2018-11-20 江苏理工学院 一种基于首层失效的复合材料层合板可靠性分析方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007038274A (ja) * 2005-08-04 2007-02-15 Kawamura Seiki Kk プリプレグの切断方法
WO2007135418A1 (fr) * 2006-05-22 2007-11-29 Advanced Composites Group Limited MatÉriaux de moulage
EP2127840A1 (fr) * 2007-02-02 2009-12-02 Toray Industries, Inc. Matériau de base préimprégné, matériau de base multicouche, matière plastique renforcée de fibres, procédé de fabrication d'un matériau de base préimprégné, et procédé de fabrication d'une matière plastique renforcée de
DE102013105080A1 (de) * 2013-05-17 2014-11-20 Thyssenkrupp Steel Europe Ag Verfahren zur Herstellung von Halbzeugen oder Bauteilen aus faserverstärktem thermoplastischen Kunststoff, nach dem Verfahren hergestelltes Halbzeug und daraus hergestelltes Bauteil
WO2015037570A1 (fr) * 2013-09-10 2015-03-19 三菱レイヨン株式会社 Pré-imprégné thermoplastique et stratifié

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007038274A (ja) * 2005-08-04 2007-02-15 Kawamura Seiki Kk プリプレグの切断方法
WO2007135418A1 (fr) * 2006-05-22 2007-11-29 Advanced Composites Group Limited MatÉriaux de moulage
EP2127840A1 (fr) * 2007-02-02 2009-12-02 Toray Industries, Inc. Matériau de base préimprégné, matériau de base multicouche, matière plastique renforcée de fibres, procédé de fabrication d'un matériau de base préimprégné, et procédé de fabrication d'une matière plastique renforcée de
DE102013105080A1 (de) * 2013-05-17 2014-11-20 Thyssenkrupp Steel Europe Ag Verfahren zur Herstellung von Halbzeugen oder Bauteilen aus faserverstärktem thermoplastischen Kunststoff, nach dem Verfahren hergestelltes Halbzeug und daraus hergestelltes Bauteil
WO2015037570A1 (fr) * 2013-09-10 2015-03-19 三菱レイヨン株式会社 Pré-imprégné thermoplastique et stratifié

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108846181A (zh) * 2018-05-31 2018-11-20 江苏理工学院 一种基于首层失效的复合材料层合板可靠性分析方法
CN108846181B (zh) * 2018-05-31 2022-07-08 江苏理工学院 一种基于首层失效的复合材料层合板可靠性分析方法

Also Published As

Publication number Publication date
GB201516245D0 (en) 2015-10-28

Similar Documents

Publication Publication Date Title
EP3928974B1 (fr) Matériau d'âme en nid d'abeille continu, panneau composite en sandwich à âme en nid d'abeille, procédé de préparation et dispositif associés à ce dernier
RU2715534C2 (ru) Композитные заготовочные полосы для использования в технологии аддитивного производства и способы их формирования
US10357924B2 (en) Composite feedstock strips for additive manufacturing and methods of forming thereof
EP2974842B1 (fr) Substrat stratifié et son procédé de fabrication
KR101787627B1 (ko) 열가소성 프리프레그 및 적층체
US8932422B2 (en) Sandwich structure with a high load-bearing capacity, as well as methods for the manufacture thereof
US9334039B2 (en) Composite laminate structure
EP3482923B1 (fr) Pâte de tissu unidirectionnelle gainée
JP6947034B2 (ja) 切込プリプレグ及び切込プリプレグの製造方法
CN112078056A (zh) 纤维增强树脂成型材料及其制造方法、连续碳纤维束及其分纤方法
US20190061279A1 (en) Thermoplastic composite master sheets and tapes and method
US8986804B2 (en) Method for producing structural member and structural member
US9403340B2 (en) Method of manufacturing a composite load-bearing structure
EP3424696B1 (fr) Procédé de rétrécissement d'une bande composite renforcée par des fibres
WO2017046577A1 (fr) Matériau composite
EP3647036B1 (fr) Couche d'enroulement sans fin renforcée par des fibres unidirectionnelles
US11787093B2 (en) Process and tool for continuous production of fiber-reinforced foams
US20200061938A1 (en) Additive manufacturing of continuous fiber thermoplastic composites
US11331890B1 (en) Polymeric sandwich structure having enhanced thermal conductivity and method of manufacturing the same
CN212242492U (zh) 一种多尺度纤维增强热塑性复合材料板
JP6702220B2 (ja) シートモールディングコンパウンドの製造方法
US9757906B2 (en) Methods of making composite charges
CN112874079A (zh) 一种多尺度纤维增强热塑性复合材料板及其制作方法

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: 16770297

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16770297

Country of ref document: EP

Kind code of ref document: A1

点击 这是indexloc提供的php浏览器服务，不要输入任何密码和下载