A method of preparing a polymer powder composition suitable for selective laser sintering and a powder composition obtained from the same. The polymer composition comprising at least two polyetherketoneketone polymorphs, each of the polymorphs having a different melting peak in a melting temperature range. The polymer is heated at a temperature below the lowest of the polymorphs melting peaks thereby decreasing the melting temperature range of the polymer composition. The treatment is especially useful with Cake B PEKK powder, which is otherwise unusable in SLS. Parts built from the treated powder using SLS have reduced surface anomalies and are easier to remove from the Cake bed.
C08J 3/00 - Processes of treating or compounding macromolecular substances
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29K 71/00 - Use of polyethers as moulding material
2.
ANALYTICAL METHOD FOR PREPARING PEKK FOR SLS PROCESS
A method of preparing a polymer powder composition suitable for selective laser sintering and a powder composition obtained from the same. The polymer composition comprising at least two polyetherketoneketone polymorphs, each of the polymorphs having a different melting peak in a melting temperature range. The polymer is heated at a temperature below the lowest of the polymorphs melting peaks thereby decreasing the melting temperature range of the polymer composition. The treatment is especially useful with Cake B PEKK powder, which is otherwise unusable in SLS. Parts built from the treated powder using SLS have reduced surface anomalies and are easier to remove from the Cake bed.
There is provided a surfacing material comprising an ultraviolet (UV) resistant polymer layer, a thermocurable or thermoplastic resin layer and a fibrous support, wherein a first surface of the UV resistant polymer layer forms an outermost surface of the surfacing material and the second surface of the UV resistant polymer layer contacts a first surface of the thermocurable or thermoplastic resin layer, and the second surface of the thermocurable or thermoplastic resin layer contacts a first surface of the fibrous support. There is also provided methods of forming cured composite structures having an ultraviolet resistant outer surface utilising a surfacing material of the invention, and cured composite structures incorporating a UV resistant surfacing layer of the invention.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 15/02 - Layered products essentially comprising metal in a form other than a sheet, e.g. wire, particles
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
A prepreg comprising a structural layer of electrically conductive fibres having interstices therebetween, the structural layer having a first outer face and an essentially parallel second outer face, the faces each defining an x-y plane separated from each other by a distance equal to the thickness of the structural layer in a z-direction, orthogonal to the x-y plane; the electrically conductive fibres being parallel to the x-y planes; the prepreg comprising resin impregnated within the structural layer and present within the interstices between the fibres; and a first layer of resin in an x-y plane and in contact with the first outer face of the structural layer having a thickness in the z-direction; wherein a number of electrically conductive fibre ends deviate from being parallel to the x-y planes, extend out of the structural layer and into the z-direction, the deviating fibres entering and passing through essentially the entire thickness of the first layer of resin.
C08J 5/04 - Reinforcing macromolecular compounds with loose or coherent fibrous material
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
5.
THERMALLY CURABLE RESIN BLEND AND ITS USE IN COMPOSITE MATERIALS
A thermally curable resin blend, comprising a) from 50 to 90 wt% cycloaliphatic curable epoxy resin having an epoxy equivalent weight of greater than 350, b) from 2 to 25 wt% of a tri- or tetra- functional epoxy reactive diluent having an epoxy equivalent weight of less than 200, and c) a curing agent; a process of thermally curing such a resin blend, the cured resin, a prepreg impregnated with the curable resin blend, and a composite material obtainable by curing such a prepreg.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Combination of continuous or discontinuous reinforcement fibers in the form of tape, fabric, non-woven, mat, or rovings impregnated with a thermoset, thermoplastic or other matrix material for use as a composite material; preimpregnated reinforcement fiber fabrics comprised of carbon, glass and aramid for use in the aerospace, space and defense, energy, transportation, automotive, machinery, tooling, sports and athletics, building and construction, and marine industries
There is provided a surfacing material comprising: a) a fibrous support layer having a first surface and an opposing second surface, a first edge and an opposing second edge, and first and second ends; and5 b) a lightning strike protection (LSP) layer having a first surface and an opposing second surface, a first edge and an opposing second edge, and first and second ends; wherein the first surface of the LSP layer contacts the second surface of the fibrous support layer, and the first edge of the LSP layer extends beyond the 10 first edge of the fibrous support layer. There is also provided methods for manufacturing a cured composite structure using the materials of the invention.
B32B 3/02 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/04 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by a layer folded at the edge, e.g. over another layer
B32B 3/06 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers togetherLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/05 - Interconnection of layers the layers not being connected over the whole surface, e.g. discontinuous connection or patterned connection
B32B 15/02 - Layered products essentially comprising metal in a form other than a sheet, e.g. wire, particles
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
B32B 27/42 - Layered products essentially comprising synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
Woven fabrics and non-woven textile fabrics used to manufacture reinforcements for composite materials in aerospace, space and defense, recreation, electrical, architectural, transportation, marine and general industrial fields; Woven and non-woven textile fabrics comprised of glass, carbon and aramid used to manufacture reinforcements for composite materials in aerospace, space and defense, military, marine, tooling, recreation, athletic equipment, electrical, architectural, construction, building, transportation, automotive, marine and general industrial fields
9.
REINFORCING MATERIAL COMPRISING A POROUS LAYER MADE OF A REACTIVE THERMOPLASTIC POLYMER AND ASSOCIATED METHODS
The present invention concerns a reinforcing material comprising at least one fibrous reinforcement associated on at least one of its faces with a thermoplastic porous layer, said thermoplastic porous layer(s) representing at most 10% of the total mass of the reinforcing material, preferably from 0.5 to 10% of the total mass of the reinforcing material, and more preferably from 2 to 6% of the total mass of the reinforcing material, characterized in that said thermoplastic porous layer or each of said thermoplastic porous layers present comprises a so-called reactive thermoplastic polymer or consists of one or more reactive thermoplastic polymers, a reactive thermoplastic polymer carrying —NH2 functions in an amount greater than 0.15 meq/g of reactive thermoplastic polymer and/or carrying —COOH functions in an amount greater than 0.20 meq/g of reactive thermoplastic polymer.
The present invention concerns a reinforcing material comprising at least one fibrous reinforcement associated on at least one of its faces with a thermoplastic porous layer, said thermoplastic porous layer(s) representing at most 10% of the total mass of the reinforcing material, preferably from 0.5 to 10% of the total mass of the reinforcing material, and more preferably from 2 to 6% of the total mass of the reinforcing material, characterized in that said thermoplastic porous layer or each of said thermoplastic porous layers present comprises a so-called reactive thermoplastic polymer or consists of one or more reactive thermoplastic polymers, a reactive thermoplastic polymer carrying —NH2 functions in an amount greater than 0.15 meq/g of reactive thermoplastic polymer and/or carrying —COOH functions in an amount greater than 0.20 meq/g of reactive thermoplastic polymer.
The invention also concerns processes for manufacturing such reinforcement materials, preforms, processes for manufacturing composite parts and composite parts using such reinforcement materials.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 3/08 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
D04H 3/16 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between thermoplastic yarns or filaments produced by welding with bonds between thermoplastic filaments produced in association with filament formation, e.g. immediately following extrusion
10.
USE OF HYDROXY SUBSTITUTED URONES AS CURE ACCELERATORS
Urone compounds containing at least 2 orthohydroxyphenyl urea units where the units are coupled via a divalent or multivalent bridging group which may be heterointerrupted are used as cure accelerators for thermosetting resin systems particularly fibre filled epoxy resin.
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C08G 59/68 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the catalysts used
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
C08L 63/00 - Compositions of epoxy resinsCompositions of derivatives of epoxy resins
11.
CARBON FIBERS HAVING IMPROVED STRENGTH AND MODULUS AND AN ASSOCIATED METHOD AND APPARATUS FOR PREPARING SAME
The invention is directed to carbon fibers having high tensile strength. The invention also provides a method and apparatus for making the carbon fibers. The method comprises advancing a precursor fiber through a plurality of passes through an oxidation oven, where stretching during the initial passes is minimized or eliminated entirely, or made negative, followed by controlled stretching over a series of passes, using rollers of increasing speed.
D01F 9/20 - Carbon filamentsApparatus specially adapted for the manufacture thereof by decomposition of organic filaments from polyaddition, polycondensation or polymerisation products
D02J 1/22 - Stretching or tensioning, shrinking or relaxing, e.g. by use of overfeed and underfeed apparatus, or preventing stretch
D02J 13/00 - Heating or cooling the yarn, thread, cord, rope, or the like, not specific to any one of the processes provided for in this subclass
12.
Method Of Printing With Polymer Powder And Siloxane Additive
A powder composition suitable for use in selective laser sintering for printing an object. The powder composition includes a first fraction having a polyetherketoneketone (PEKK) powder having a plurality of particles. The powder composition includes a second fraction having a plurality of siloxane particles that is dry blended with the PEKK powder prior to selective laser sintering of the powder. In some embodiments, the powder composition includes a third fraction of carbon fiber. The powder composition when used in selective laser sintering results in parts with more consistent results and improves process economics.
C09D 11/102 - Printing inks based on artificial resins containing macromolecular compounds obtained by reactions other than those only involving unsaturated carbon-to-carbon bonds
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29C 64/20 - Apparatus for additive manufacturingDetails thereof or accessories therefor
B29K 71/00 - Use of polyethers as moulding material
Bisorthohydroxy aromatic urones and their use as curatives and cure accelerators in resin systems particularly epoxy resin systems provide formulations with good outlife, low curing temperatures and desirable glass transition temperatures after curing, they are particularly useful in prepregs used in the production of components for the aerospace and wind turbine industries.
C07C 275/40 - Derivatives of urea, i.e. compounds containing any of the groups the nitrogen atoms not being part of nitro or nitroso groups having nitrogen atoms of urea groups bound to carbon atoms of six-membered aromatic rings of a carbon skeleton being further substituted by nitrogen atoms not being part of nitro or nitroso groups
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
14.
REINFORCING MATERIAL COMPRISING TWISTED CARBON THREADS FOR THE MANUFACTURE OF COMPOSITE PARTS, AND CORRESPONDING METHODS AND USE
The invention relates to a reinforcing material (1) consisting of a unidirectional reinforcing web (2) formed of one or more carbon reinforcing yarns (3), associated on each of its faces with a veil of polymeric fibers (4, 5) chosen from among nonwoven materials, the polymeric portion of the reinforcing material representing from 0.5% to 10% of the total weight of the reinforcing material (1), and preferably from 2% to 6% of its total weight, said unidirectional reinforcing web (2) comprising one or a series of reinforcing yarns (3) individually twisted having a twist of 3 turns/m to 15 turns/m, preferably from 6 turns/m to 12 turns/m.
D02G 3/26 - Yarns or threads characterised by constructional features with characteristics dependent on the amount or direction of twist
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29K 105/10 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns oriented
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
D04H 3/04 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments in rectilinear paths, e.g. crossing at right angles
There is provided a resin composition for producing a composite part, comprising: a) from 30 to 90 wt % by weight of the composition of an epoxy resin component; and b) from 5 to 50 wt % by weight of the composition of a curative component; wherein the epoxy resin component comprises N,N,N′,N′-tetraglycidyl-4,4′-diamino-3,3′-dimethyldiphenylmethane (M-TGDDM) in an amount of at least 30 wt % by weight of the epoxy resin component; and further wherein the curative component comprises one or more of a diaminodiphenyl sulfone, a diaminobenzophenone, a fluorene diamine, a methylene bis aniline, including hybrid methylene bis anilines, or a substituted diamine toluene. There is also provided the use of N,N,N′,N′-tetraglycidyl-4,4′-diamino-3,3′-dimethyldiphenylmethane (M-TGDDM) as a compression performance improving additive in a resin composition for producing a composite part. There are also provided curable composite components, cured composite components produced therefrom and the use of such components as aircraft components.
C08L 87/00 - Compositions of unspecified macromolecular compounds, obtained otherwise than by polymerisation reactions only involving unsaturated carbon-to-carbon bonds
A process for forming a spliced prepreg tape by joining adjacent ends (22, 24) of a first and a second prepreg tape (2, 3, 4), each prepreg tape comprising a respective first and second prepreg layer (12, 18) comprising fibrous material and curable thermosetting resin, each prepreg tape further comprising a respective first and second releasable polymeric backing sheet (14), the process involving: peeling of the first polymeric backing sheet from the first prepreg layer, so as to provide a first peeled end region, and optionally peeling of the second polymeric backing sheet from the second prepreg layer, so as to provide a first peeled end region (30), and optionally a second peeled end region (32), over which peeled end region or regions the prepreg layer is separated from its respective polymeric backing sheet; overlapping the first and second prepreg tapes at the first peeled end region, and if present the second peeled end region, so as to form a preliminary spliced join (34, 38), the preliminary spliced join comprising first and second adjacent layers of prepreg and first and second adjacent layers of polymeric backing sheet; ultrasonically welding of the preliminary spliced join (36) to merge together the first and second adjacent layers of prepreg and to merge together the two adjacent layers of polymeric backing sheet to form the spliced prepreg tape.
Provided are sizing compositions, and more particularly, sizing compositions comprising an epoxy and a carboxylate salt of an amine compound for the treatment of carbon fiber. The structure of the amine used to make the carboxylate salts is RnXmQ, wherein Q is an amine-containing group, X is a polyether group, and R is an aryl or alkyl group, either linear or branched, saturated or unsaturated, or a combination thereof. m and n are integers greater than or equal to 0. The compositions reduce or eliminate sheen and luster on carbon fibers in finished goods. Carbon fiber-reinforced composite materials and carbon fibers incorporating said sizing compositions are also provided.
nmmQ, wherein Q is an amine-containing group, X is a polyether group, and R is an aryl or alkyl group, either linear or branched, saturated or unsaturated, or a combination thereof. m and n are integers greater than or equal to 0. The compositions reduce or eliminate sheen and luster on carbon fibers in finished goods. Carbon fiber-reinforced composite materials and carbon fibers incorporating said sizing compositions are also provided.
A curable prepreg comprising a structural layer of unidirectional electrically conductive fibres having interstices therebetween, having a first outer face and an essentially parallel second outer face, and comprising thermosetting resin impregnated within the structural layer and present within the interstices, and a first layer of thermosetting resin in contact with the first outer face of the structural layer, wherein the ratio of the electrical conductivity in the x-direction, parallel to the conductive fibres, to the electrical conductivity in the y-direction perpendicular to the conductive fibres, is less than 1000.
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
C08J 5/04 - Reinforcing macromolecular compounds with loose or coherent fibrous material
C08J 5/10 - Reinforcing macromolecular compounds with loose or coherent fibrous material characterised by the additives used in the polymer mixture
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
20.
NEW REINFORCING MATERIALS BASED ON S- AND Z-TWISTED YARNS FOR THE MANUFACTURE OF COMPOSITE PARTS, METHODS AND USE
The reinforcing material comprises a unidirectional reinforcing web (2) formed of one or a plurality of carbon yarns (3), associated on at least one of its faces, preferably on each of its faces, with a porous polymeric layer (4, 5), the polymeric portion of the reinforcing material representing from 0.5% to 10% of its total weight and preferably from 2% to 6% of its total weight, characterized in that said carbon yarns (3) are individually twisted having a twist from 3 turns/m to 15 turns/m, preferably from 6 turns/m to 12 turns/m, and comprise at least one S-twist yarn and at least one Z-twist yarn, from a selection according to claim 1.
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B32B 3/18 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an internal layer formed of separate pieces of material
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
D02G 3/02 - Yarns or threads characterised by the material or by the materials from which they are made
D02G 3/26 - Yarns or threads characterised by constructional features with characteristics dependent on the amount or direction of twist
D02G 3/44 - Yarns or threads characterised by the purpose for which they are designed
A resin layer, having a generally planar form and having a first outer face and an essentially parallel second outer face, and supported on its first outer face by a supporting structure, parallel to and in contact with the first outer face, wherein the layer comprises a skeletal structure embedded within the resin, the skeletal structure comprising: a plurality of studs distributed throughout the plane of the layer, each stud having a length in the direction perpendicular to the plane of the layer, and terminating in a first end and a second end, the studs having a length extending from at least the first face to at least the second face; and a framework of solid connections, connecting each solid stud to a plurality of adjacent studs, particularly for use as part of a prepreg.
B32B 3/10 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
22.
A PREPREG, A METHOD OF TESTING THEREOF AND A PROCESS FOR ITS MANUFACTURE
A prepreg comprising a structural layer comprising fibres having interstices therebetween, and comprising curable thermosetting resin impregnated within the structural layer and present within the interstices, wherein the prepreg comprises a test region that is free of curable thermosetting resin; a method of testing the pregreg, wherein the method comprises the steps of a) carrying out a measurement test on a test area of the test region, followed by b) inferring a property of the prepreg from the results of the measurement; and a process for the manufacture of the prepreg, the process comprising the steps of: providing a structural layer comprising fibres, having a first face and a second face, and a first impregnating layer comprising curable thermosetting resin; bringing the first face of the structural layer into contact with the first impregnating layer; compressing the structural layer and first impregnation layer together so that curable resin impregnates the fibrous layer so that it is present between the interstices between the fibres, thereby forming the prepreg; wherein the first impregnating layer comprises a region where no impregnation occurs, thereby producing the test region of the prepreg that is free of curable resin.
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
B32B 3/02 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
23.
REINFORCEMENT MATERIAL INCLUDING A POROUS LAYER MADE OF A PARTIALLY CROSS-LINKED THERMOPLASTIC POLYMER AND ASSOCIATED METHODS
The present invention relates to a reinforcement material including at least one fiber reinforcement associated on at least one of its faces with a porous layer, the porous layer(s) representing no more than 10% of the total weight of the reinforcement material, preferably from 0.5 to 10% of the total weight of the reinforcement material, and most preferably from 2 to 6% of the total weight of the reinforcement material, characterized in that the porous layer contains a partially cross-linked thermoplastic polymer. Another object of the invention is a precursor material of such a reinforcement material, as well as their preparation method and the methods for manufacturing a preform or a composite part from such materials.
The host compound in a clathrate is an amino or hydroxyl containing aromatic phosphorous compound, clathrates containing a resin curative and their use in curable resin compositions to produce moulded articles particularly fibre reinforced articles.
06 - Common metals and ores; objects made of metal
Goods & Services
Metallic cellular core material and metallic sandwich panels for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products; building materials, namely, metallic honeycomb and metallic sandwich panels.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Soundproofing materials for vehicles, vehicle engines, airplanes, and airplane engines in the nature of cellular core material with inserts for noise reduction
06 - Common metals and ores; objects made of metal
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Metallic cellular core material and metallic sandwich panels for use in manufacturing aerospace, space and defence, recreation, electrical, architectural, marine, transportation and general industrial products; Metallic honeycomb and metallic sandwich panels. Soundproofing materials for airplane engines and other portions of airplanes in the nature of cellular core material with inserts for noise reduction.
There is provided a surfacing material comprising an ultraviolet (UV) resistant polymer layer, a thermocurable or thermoplastic resin layer and a fibrous support, wherein a first surface of the UV resistant polymer layer forms an outermost surface of the surfacing material and the second surface of the UV resistant polymer layer contacts a first surface of the thermocurable or thermoplastic resin layer, and the second surface of the thermocurable or thermoplastic resin layer contacts a first surface of the fibrous support. There is also provided methods of forming cured composite structures having an ultraviolet resistant outer surface utilising a surfacing material of the invention, and cured composite structures incorporating a UV resistant surfacing layer of the invention.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
The invention is directed to carbon fibers having high tensile strength. The invention also provides a method and apparatus for making the carbon fibers. The method comprises advancing a precursor fiber through a plurality of passes through an oxidation oven, where stretching during the initial passes is minimized or eliminated entirely, or made negative, followed by controlled stretching over a series of passes, using rollers of increasing speed.
The present invention is concerned with a moulding material comprising: a) A primary non-woven fibre layer; b) A secondary non-woven fibre layer, and c) A resin layer; wherein the resin layer bonds the secondary non-woven fibre layer to a first surface of the primary non-woven fibre layer, and the resin layer is exposed on the second surface of the primary non-woven layer.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/08 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments the fibres or filaments of a layer being specially arranged or being of different substances
B32B 5/10 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer reinforced with filaments
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
31.
Reinforcement material comprising a porous layer made of partially cross-linked thermoplastic polymer and associated methods
The present invention relates to a reinforcement material including at least one fiber reinforcement associated on at least one of its faces with a porous layer, the porous layer(s) representing no more than 10% of the total weight of the reinforcement material, preferably from 0.5 to 10% of the total weight of the reinforcement material, and most preferably from 2 to 6% of the total weight of the reinforcement material, characterized in that the porous layer contains a partially cross-linked thermoplastic polymer. Another object of the invention is a precursor material of such a reinforcement material, as well as their preparation method and the methods for manufacturing a preform or a composite part from such materials.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 3/10 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
A moulding material which comprises: (a) a structural reinforcement layer comprising a fibrous reinforcement material optionally in combination with a second resin composition; and (b) a surface enhancing layer, for contacting a surface of a mould or tool, comprising a first non-woven fibre carrier in combination with a first resin composition containing a rheology modifier and a curing agent, wherein the first resin composition provides an external mould or tool-contacting surface of the moulding material. The moulding material can be cured to form a moulded article having a high quality surface finish that requires minimal preparation before painting and/or application in its intended use. The moulded article may be provided with sacrificial discontinuous indicator means to assist in uniform removal of a part of the surface enhancing layer of the moulded article for specific applications.
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B29C 70/18 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length in the form of a mat, e.g. sheet moulding compound [SMC]
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Plastic composite material in the form of sheets for use in
manufacturing aerospace, space and defense, recreation,
electrical, architectural, marine, transportation and
general industrial projects; structural insulated
construction panels, namely, non-metallic honeycomb-shaped
structural insulated construction panels for use in the
aerospace, space and defense, recreation, electrical,
architectural, marine, transportation and building
industries; tamping material made of thermoset or
thermoplastic copolymeric material in the form of tape or
mat for use as a composite material in manufacturing
aerospace, space and defense, recreation, electrical,
architectural, marine, transportation and general industrial
projects; thermoplastic elastomer resins in the form of tape
or mat for use as a composite material in further
manufacture in the aerospace, space and defense, recreation,
electrical, architectural, marine, transportation and
general industrial industries; thermoplastic composite tapes
or mats containing glass fiber for use as a composite
material in the manufacture of other goods in the aerospace,
space and defense, recreation, electrical, architectural,
marine, transportation and general industrial industries;
thermoplastic section tapes or mats for use as a composite
material in the manufacture of façade and partitions for use
as building materials for heat-insulating applications in
the aerospace, space and defense, recreation, electrical,
architectural, marine, transportation and general industrial
industries; semi-processed thermoplastics in tape or mat
form for use as a composite material in manufacturing
aerospace, space and defense, recreation, electrical,
architectural, marine, transportation and general industrial
projects; plastic composite material in the form of tape or
mat for use in manufacturing aerospace, space and defense,
recreation, electrical, architectural, marine,
transportation and general industrial projects; continuous
or discontinuous fiber reinforced molding materials in the
form of tape, fabric, non-woven, mat, tow or roving fully or
partially impregnated with a thermoset, thermoplastic or
other matrix material for use as a composite material in
manufacturing aerospace, space and defense, recreation,
electrical, architectural, marine, transportation and
general industrial projects; non-metallic honeycomb for use
in structural reinforcement, and aerospace, space and
defense, recreation, electrical, architectural, marine,
transportation and general industrial projects; synthetic
resins for use in the manufacture of moulding compounds;
carbon fibers not for textile use; material for thermal
insulation and fire protection, namely, fire-resistant
composite panels made of aramid, glass, carbon or ceramic
fibers.
34.
PREPREG OR SEMIPREG PRECURSOR AND METHOD OF MANUFACTURING SAME
A prepreg or semipreg precursor comprising a fibre reinforcement and a resin composition fused thereto, the resin composition containing at least one epoxy resin and a latent curing agent, wherein the epoxy resin and the latent curing agent form a solid phase at ambient temperature, the latent curing agent forming a discrete phase within the epoxy resin. The stabilized uncured resin composition and prepregs and semipregs incorporating the same are easy to handle, have desirable curing temperatures and show good outlife at ambient to mid range temperatures.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Combination of continuous or discontinuous reinforcement
fibers in the form of tape, fabric, non-woven, mat, tow or
rovings impregnated with a thermoset, thermoplastic or other
matrix material for use as a composite material; molding
material for further manufacture consisting of reinforcing
fiber pre-impregnated with a matrix resin.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Combination of continuous or discontinuous reinforcement
fibers in the form of tape, fabric, non-woven, mat, tow or
rovings impregnated with a thermoset, thermoplastic or other
matrix material for use as a composite material; Molding
material for further manufacture consisting of reinforcing
fiber pre-impregnated with a matrix resin.
An assembly (113) for composite manufacture is provided. The assembly comprises a cured resin impregnated reinforcement material (112) comprising a fibre component and a resin matrix component, in which the resin matrix component comprises polyurethane, the assembly having a length to width ratio of at least 5:1, and the assembly defining a longitudinal direction (L) along its length; and a peel ply (116) in contact with the cured resin impregnated reinforcement material (112), the peel ply (116) comprising a woven layer having a plurality of longitudinal fibres (118) extending in the longitudinal direction (L); and a plurality of transverse fibres (120) extending in a transverse direction (T) normal to the longitudinal direction (L); in which the areal density of the plurality of transverse fibres (120) is higher than the areal density of the plurality of longitudinal fibres (118).
B29C 70/52 - Pultrusion, i.e. forming and compressing by continuously pulling through a die
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
A self-adhesive prepreg comprising a fibre reinforcement layer having a first side and a second side, wherein the first side of the fibre reinforcement layer has been pre-impregnated with a self-adhesive resin composition. The self-adhesive may be used as a structural reinforcement and is especially adapted for direct bonding to oily steel or galvanized steel in the automotive, aerospace and other sheet metal fabrication industries.
C08G 59/30 - Di-epoxy compounds containing atoms other than carbon, hydrogen, oxygen, and nitrogen
C08G 59/32 - Epoxy compounds containing three or more epoxy groups
C08G 59/38 - Epoxy compounds containing three or more epoxy groups together with di-epoxy compounds
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C08G 59/68 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the catalysts used
C08L 63/00 - Compositions of epoxy resinsCompositions of derivatives of epoxy resins
Protective fabrics used in the manufacture of goods, namely,
armored vehicles, clothing and protective walls; fiberglass
fabrics for solar protection; and fiberglass, carbon and
aramid reinforcement textiles for use in the commercial
aerospace, space and defense, recreation, electrical,
architectural, transportation, marine, and general
industrial fields.
21 - HouseHold or kitchen utensils, containers and materials; glassware; porcelain; earthenware
Goods & Services
Reinforcement fibers made of glass and partially impregnated
with polymeric resin for use in the manufacture of composite
materials for aerospace, space and defense, recreation,
electrical, architectural, marine, transportation and
general industrial products; reinforcement fibers made of
glass and partially impregnated with synthetic resin for use
in the manufacture of composite materials for aerospace,
space and defense, recreation, electrical, architectural,
marine, transportation and general industrial products.
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
Custom manufacture of goods in the nature of airplane parts
and fittings, satellites parts and fittings, engine parts
and fittings, defense aircraft parts and fittings, space
vehicle parts and fittings, launchers and launch pads and
parts and fittings therefor, helicopter parts and fittings,
turbine and nacelle parts and fittings, boats, canoes and
dinghies and parts and fittings therefor, wheels, brackets,
and ducts, and industrial parts to the order and
specification of others; treatment of materials, namely, for
the manufacture of thermoplastic products by extrusion,
compression moulding and plastic injection; treatment of
materials for use in the aerospace, aviation, satellite,
military, space and defense industries; treatment of
materials, namely, selective laser sintering for a wide
variety of goods.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Molding material being semi-finished reinforcing plastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing natural epoxy matrix resin fibers for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermal insulation thermoplastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for insulation and heat resistance for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for heat and acoustical insulation for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use
06 - Common metals and ores; objects made of metal
Goods & Services
Metallic cellular core material and metallic sandwich panels
for use in manufacturing aerospace, space and defense,
recreation, electrical, architectural, marine,
transportation and general industrial products.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Molding material being semi-finished reinforcing plastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing natural epoxy matrix resin fibers for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermal insulation thermoplastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for insulation and heat resistance for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use; Molding material being semi-finished reinforcing thermoplastic fibers pre-impregnated with a matrix resin for heat and acoustical insulation for further manufacture in the aerospace, automotive, transportation, recreation and building industries, not for textile use
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
(1) Custom manufacture of goods in the nature of airplane parts and fittings, satellites parts and fittings, automobile and aircraft engine parts, defense aircraft parts and fittings, space vehicle parts and fittings, space launchers and rocket launch pads and structural parts and fittings therefor, helicopter parts and fittings, aircraft turbine and nacelle being aircraft turbines parts and fittings, boats, canoes and dinghies and parts and fittings therefor, wheels for land vehicles and aircraft, bearing brackets for machines, and air conditioning and ventilating ducts to the order and specification of others; treatment of materials, namely, for the manufacture of thermoplastic synthetic resins, semi-processed by extrusion, compression moulding and plastic injection; treatment of materials for use in the aerospace, aviation, satellite, military, space and defense industries, namely, strengthening, reinforcing, weatherproofing and waterproofing of carbon fibers, structural honeycomb and synthetic resins; treatment of materials, namely, selective laser sintering 3D printing for others for a wide variety of goods.
(1) Protective fabrics used in the manufacture of goods, namely, armored vehicles and protective walls; fiberglass fabrics for solar protection for use in land, sea and aerospace applications; and fiberglass, carbon and aramid reinforcement textiles for use in the commercial aerospace, space and defense, recreation, electrical, architectural, transportation, marine, and general industrial fields.
21 - HouseHold or kitchen utensils, containers and materials; glassware; porcelain; earthenware
Goods & Services
(1) Reinforcement fibers made of glass and partially impregnated with polymeric resin being glass fibers for reinforcing plastics for use in the manufacture of composite materials for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products; reinforcement fibers made of glass and partially impregnated with synthetic resin being glass fibers for reinforcing plastics for use in the manufacture of composite materials for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products.
17 - Rubber and plastic; packing and insulating materials
Goods & Services
(1) Plastic composite material in the form of sheets for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; non-metallic honeycomb-shaped structural fire-resistant insulated construction panels for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; tamping material made of semi-processed thermoplastic polymer resins and thermosetting copolymeric resins in the form of tapes and mats for use as a composite material in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; thermoplastic elastomer resins in the form of thread seal tapes and mats for use as a composite material in further manufacture in the aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial industries; thermoplastic composite tapes and mats containing glass fiber for insulation for use as a composite material in the manufacture of other goods in the aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial industries; semi-processed thermoplastic polymer resins in tape and mat form for use as a composite material in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; plastic composite material in the form of plastic tape and mat for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; non-metallic fiberglass insulation in the shape of a honeycomb for use in aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; carbon fibers not for textile use; material for thermal insulation and fire protection, namely, fire-resistant composite insulated panels made of aramid, glass, carbon and ceramic fibers.
06 - Common metals and ores; objects made of metal
Goods & Services
(1) Metallic cellular core material and metallic sandwich panels for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products.
54.
UREA DERIVATIVES AND THEIR USE AS CURATIVES AND CURATIVE ACCELERATORS FOR RESIN SYSTEMS
Bisorthohydroxy aromatic urones and their use as curatives and cure accelerators in resin systems particularly epoxy resin systems provide formulations with good outlife, low curing temperatures and desirable glass transition temperatures after curing, they are particularly useful in prepregs used in the production of components for the aerospace and wind turbine industries.
C07C 275/34 - Derivatives of urea, i.e. compounds containing any of the groups the nitrogen atoms not being part of nitro or nitroso groups having nitrogen atoms of urea groups bound to carbon atoms of six-membered aromatic rings of a carbon skeleton being further substituted by singly-bound oxygen atoms having nitrogen atoms of urea groups and singly-bound oxygen atoms bound to carbon atoms of the same non-condensed six-membered aromatic ring
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
Custom manufacture of goods in the nature of airplane parts and fittings, satellites parts and fittings, engine parts and fittings, defense aircraft parts and fittings, space vehicle parts and fittings, launchers and launch pads and parts and fittings therefor, helicopter parts and fittings, turbine and nacelle parts and fittings, boats, canoes and dinghies and parts and fittings therefor, wheels, brackets, and ducts, and industrial parts to the order and specification of others; treatment of materials, namely, for the manufacture of thermoplastic products by extrusion, compression moulding and plastic injection; treatment of materials for use in the aerospace, aviation, satellite, military, space and defense industries, namely, strengthening, reinforcing, weatherproofing and waterproofing of carbon fiber, structural honeycomb and synthetic resins; treatment of materials, namely, selective laser sintering for a wide variety of goods
An adhesive composition comprising a silane-modified epoxy resin, a dicyclopentadiene novolac epoxy resin and a curing agent. The composition shows good oily steel bonding, even in the absence of CTBN rubber or rubber adducts as toughening agents, with good Tg values of the cured resin and good Tg retention after hot wet aging.
C08G 59/30 - Di-epoxy compounds containing atoms other than carbon, hydrogen, oxygen, and nitrogen
C08G 59/32 - Epoxy compounds containing three or more epoxy groups
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C09J 5/06 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving heating of the applied adhesive
21 - HouseHold or kitchen utensils, containers and materials; glassware; porcelain; earthenware
Goods & Services
Reinforcement fibers made of glass and partially impregnated with polymeric resin for non-textile purposes for use in the manufacture of composite materials for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products; reinforcement fibers made of glass and partially impregnated with synthetic resin for non-textile purposes for use in the manufacture of composite materials for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Plastic composite material in the form of sheets for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; non-metallic honeycomb-shaped structural insulated construction panels for aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; tamping material made of thermoset or thermoplastic copolymeric material in the form of tape or mat for use as a composite material in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; Thermoplastic elastomer resins in the form of tape or mat for use as a composite material in further manufacture in the aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial industries; Thermoplastic composite tapes or mats containing glass fiber for use as a composite material in the manufacture of other goods in the aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial industries; Semi-processed thermoplastics in tape or mat form for use as a composite material in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; Plastic composite material in the form of tape or mat for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; non-metallic fiberglass insulation in the shape of a honeycomb for use in aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial projects; Carbon fibers not for textile use; Material for thermal insulation and fire protection, namely, fire-resistant composite panels made of aramid, glass, carbon or ceramic fibers
Protective fabrics used in the manufacture of goods, namely armored vehicles, clothing and protective walls; fiberglass fabrics for solar protection for use in land, sea and aerospace applications; fiberglass, carbon and aramid reinforcement textiles for use in the commercial aerospace, space and defense, recreation, electrical, architectural, transportation, marine, and general industrial fields
A method of manufacture of a composite component is provided, the method comprising the steps of providing two layers of pre-preg composite material, one of which has an edge adjacent a surface of the other. Pressure and, optionally, vibrational energy is applied to the edge to thereby smooth the ply drop.
17 - Rubber and plastic; packing and insulating materials
22 - Rope, netting, tents, awnings, sails and sacks; padding and stuffing materials
Goods & Services
Carbon fibers for use in manufacture and for structural reinforcement, other than for textile use Carbon fibers for textile use; Synthetic carbon fibers for use in the manufacture of fabrics, textiles for structural reinforcement
06 - Common metals and ores; objects made of metal
Goods & Services
Metallic cellular core material and metallic sandwich panels for use in manufacturing aerospace, space and defense, recreation, electrical, architectural, marine, transportation and general industrial products
Formulations comprising from 10 to 80% by weight of the formulation of a halogenated epoxy resin; from 1 to 15% by weight of the formulation of an antimony based fire retardant; from 1 to 10% by weight of the formulation of an inorganic or non-polymeric organic phosphorous containing fire retardant; and from 1 to 30% by weight of the formulation of a curative system are provided. The formulations are particularly suitable for producing aircraft interior composite components having good fire retarding properties, low smoke emission, low smoke toxicity and low heat release properties. The formulations also have excellent processing and mechanical properties. Further components may be included in the compositions to improve various properties, including the fire retarding, low smoke emission, low smoke toxicity and low heat release properties and to also further improve the processing and mechanical properties, including toughness. Compositions produced from the formulations have excellent processing and mechanical properties, and may also have good surface finishes.
C08G 59/30 - Di-epoxy compounds containing atoms other than carbon, hydrogen, oxygen, and nitrogen
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C08J 5/04 - Reinforcing macromolecular compounds with loose or coherent fibrous material
A curative system comprising a combination of adipic acid dihydrazide and/or isophthalic dihydrazide and a clathrate in which the guest compound of the clathrate comprises an imidazole, an imidazoline or diazabicycloalkanes (DBCA).
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
C07C 257/22 - Compounds containing carboxyl groups, the doubly-bound oxygen atom of a carboxyl group being replaced by a doubly-bound nitrogen atom, this nitrogen atom not being further bound to an oxygen atom, e.g. imino-ethers, amidines with replacement of the other oxygen atom of the carboxyl group by nitrogen atoms, e.g. amidines having nitrogen atoms of amidino groups further bound to nitrogen atoms, e.g. hydrazidines
C07D 235/00 - Heterocyclic compounds containing 1,3-diazole or hydrogenated 1,3-diazole rings, condensed with other rings
C07D 247/02 - Heterocyclic compounds containing rings having two nitrogen atoms as the only ring hetero atoms, according to more than one of groups having the nitrogen atoms in positions 1 and 3
C08G 59/00 - Polycondensates containing more than one epoxy group per moleculeMacromolecules obtained by reaction of epoxy polycondensates with monofunctional low-molecular-weight compoundsMacromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
C08G 59/68 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the catalysts used
Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy resin component, polyethersulfone as a toughening agent, a thermoplastic particle component, a nanoparticle component and a curing agent
The present invention is concerned with a moulding material comprising: a) A primary non-woven fibre layer; b) A secondary non-woven fibre layer, and c) A resin layer; wherein the resin layer bonds the secondary non-woven fibre layer to a first surface of the primary non-woven fibre layer, and the resin layer is exposed on the second surface of the primary non- woven layer.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/03 - Layered products characterised by the relation between layers Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties Layered products characterised by the interconnection of layers with respect to the orientation of features
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
A moulding material which comprises: (a) a structural reinforcement layer comprising a fibrous reinforcement material optionally in combination with a second resin composition; and (b) a surface enhancing layer, for contacting a surface of a mould or tool, comprising a first non-woven fibre carrier in combination with a first resin composition containing a rheology modifier and a curing agent, wherein the first resin composition provides an external mould or tool-contacting surface of the moulding material. The moulding material can be cured to form a moulded article having a high quality surface finish that requires minimal preparation before painting and/or application in its intended use. The moulded article may be provided with sacrificial discontinuous indicator means to assist in uniform removal of a part of the surface enhancing layer of the moulded article for specific applications.
B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/64 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising fillers only the filler influencing the surface characteristics of the material, e.g. by concentrating near the surface or by incorporation into the surface by force
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
B32B 27/26 - Layered products essentially comprising synthetic resin characterised by the use of special additives using curing agents
Acoustic honeycomb structures that include cells in which a friction-locking insertion process is used to locate acoustic barriers within honeycomb cells to provide multiple degree of freedom (MDOF) acoustic liners having a variety of acoustic resonator depths. Solid polymer films are formed into acoustic barrier caps. The acoustic barrier caps are friction-locked and bonded to cell walls at one or more cell depths to form acoustically reflective hard walls that form effective bottom ends for acoustic resonators.
Acoustic honeycomb structures that include cells in which a friction-locking insertion process is used to locate acoustic barriers within honeycomb cells to provide multiple degree of freedom (MDOF) acoustic liners having a variety of acoustic resonator depths. Solid polymer films are formed into acoustic barrier caps. The acoustic barrier caps are friction-locked and bonded to cell walls at one or more cell depths to form acoustically reflective hard walls that form effective bottom ends for acoustic resonators.
Acoustic honeycomb structures that include cells in which a friction-locking insertion process is used to locate acoustic barriers within honeycomb cells to provide multiple degree of freedom (MDOF) acoustic liners having a variety of acoustic resonator depths. Solid polymer films are formed into acoustic barrier caps. The acoustic barrier caps are friction-locked and bonded to cell walls at one or more cell depths to form acoustically reflective hard walls that form effective bottom ends for acoustic resonators.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
73.
System for identifying parts formed in an additive manufacturing build
A system and method for identifying test bars formed during a selective laser sintering build. A part cake is formed during a selective laser sintering build. The part cake comprises parts formed from a powder by selective laser sintering and unsintered powder around the formed parts. The parts include test bars for performing material testing. Each test bar includes a plurality of indentations in a first grip section and a second grip section. The plurality of indentations are arranged in a information providing pattern that is adapted to be readable after the test part is removed from the part cake.
G01N 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
G06K 19/06 - Record carriers for use with machines and with at least a part designed to carry digital markings characterised by the kind of the digital marking, e.g. shape, nature, code
G01N 3/02 - Investigating strength properties of solid materials by application of mechanical stress Details
G06K 1/12 - Methods or arrangements for marking the record carrier in digital fashion otherwise than by punching
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B33Y 80/00 - Products made by additive manufacturing
B33Y 70/00 - Materials specially adapted for additive manufacturing
A powder composition suitable for laser sintering for printing a three-dimensional object obtained by pre-heating a raw PEKK to evaporate a liquid solvent in the raw PEKK and the grinding the raw PEKK to form a PEKK powder, the powder composition having a first fraction comprising a polyetherketoneketone (PEKK) powder having a plurality of particles, the plurality of particles having a mean diameter D50 in the range of 30 μm to 150 μm. The plurality of particles of the first fraction are substantially non-spherical.
C08G 65/46 - Post-polymerisation treatment, e.g. recovery, purification, drying
B02C 23/10 - Separating or sorting of material, associated with crushing or disintegrating with separator arranged in discharge path of crushing or disintegrating zone
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B33Y 70/10 - Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials
C08G 65/40 - Macromolecular compounds obtained by reactions forming an ether link in the main chain of the macromolecule from hydroxy compounds or their metallic derivatives derived from phenols from phenols and other compounds
There is provided a resin composition for producing a composite part, comprising: a) from 30 to 90 wt% by weight of the composition of an epoxy resin component; and b) from 5 to 50 wt% by weight of the composition of a curative component; wherein the epoxy resin component comprises N,N,N',N'-tetraglycidyl-4,4'-diamino- 3,3'-dimethyldiphenylmethane (M-TGDDM) in an amount of at least 30 wt% by weight of the epoxy resin component; and further wherein the curative component comprises one or more of a diaminodiphenyl sulfone, a diaminobenzophenone, a fluorene diamine, a methylene bis aniline, including hybrid methylene bis anilines, or a substituted diamine toluene. There is also provided the use of N,N,N',N'-tetraglycidyl-4,4'-diamino-3,3'- dimethyldiphenylmethane (M-TGDDM) as a compression performance improving additive in a resin composition for producing a composite part. There are also provided curable composite components, cured composite components produced therefrom and the use of such components as aircraft components.
Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy resin component, polyethersulfone as a toughening agent, a thermoplastic particle component, a nanoparticle component and a curing agent.
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
B32B 27/26 - Layered products essentially comprising synthetic resin characterised by the use of special additives using curing agents
A process for layer-by-layer manufacturing a three-dimensional object from a powder and objects made from the same is described. The process includes the step of applying a layer of a powder on a bed of a laser sintering machine. The powder includes polyetherketoneketone. The process further includes the step of solidifying selected points of the applied layer of powder by irradiation using heat energy introduced by a laser having a power L and successively repeating the step of applying the powder and the step of solidifying the applied layer of powder until all cross sections of a three-dimensional object are solidified. L is between 1 W and 20 W. In some embodiments L is between 1 and 10 W. In some embodiments, the powder is recycled PEKK powder. In some embodiments, the powder includes carbon fiber.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29K 71/00 - Use of polyethers as moulding material
78.
SELECTIVE CONTROL OF OXIDATION ATMOSPHERES IN CARBON FIBER PRODUCTION
A method for making carbon fiber in which the tensile strength of carbon fiber is increased without dehumidifying the ambient air that enters every oxidation oven in a multiple oxidation oven system. A positive effect on tensile strength is provided when ambient air entering only the first oven in a series of oxidation ovens is dehumidified. In addition, the ambient air entering the last oven is not dehumidified when one or more of the preceding oxidation ovens is operated with dehumidified air.
D01F 6/18 - Monocomponent man-made filaments or the like of synthetic polymersManufacture thereof from homopolymers obtained by reactions only involving carbon-to-carbon unsaturated bonds from polymers of unsaturated nitriles, e.g. polyacrylonitrile, polyvinylidene cyanide
D01F 9/22 - Carbon filamentsApparatus specially adapted for the manufacture thereof by decomposition of organic filaments from polyaddition, polycondensation or polymerisation products from macromolecular compounds obtained by reactions only involving carbon-to-carbon unsaturated bonds from polyacrylonitriles
A fast cure cycle for thermocurable resins coupled with long storage stability is achieved by applying a curative containing particulate cure initiator to the surface of a layer of the thermocurable resin and by employing conditions of temperature and pressure to drive the curative into the resin to cause rapid cure of the resin.
A method for making carbon fiber in which the tensile strength of carbon fiber is increased without dehumidifying the ambient air that enters every oxidation oven in a multiple oxidation oven system. A positive effect on tensile strength is provided when ambient air entering only the first oven in a series of oxidation ovens is dehumidified. In addition, the ambient air entering the last oven is not dehumidified when one or more of the preceding oxidation ovens is operated with dehumidified air.
D01F 9/22 - Carbon filamentsApparatus specially adapted for the manufacture thereof by decomposition of organic filaments from polyaddition, polycondensation or polymerisation products from macromolecular compounds obtained by reactions only involving carbon-to-carbon unsaturated bonds from polyacrylonitriles
C01B 32/05 - Preparation or purification of carbon not covered by groups , , ,
Composite honeycomb that may be contoured to form composite honeycomb structures, which have tight radii of curvatures and/or compound curvatures, and which are suitable for use in high temperature environments. The method for making the composite honeycomb involves using high temperature prepreg to make a flexible composite honeycomb that is formed into a composite honeycomb precursor. A high temperature coating resin is applied to the composite honeycomb precursor to form the high temperature composite honeycomb.
Composite honeycomb that may be contoured to form composite honeycomb structures, which have tight radii of curvatures and/or compound curvatures, and which are suitable for use in high temperature environments. The method for making the composite honeycomb involves using high temperature prepreg to make a flexible composite honeycomb that is formed into a composite honeycomb precursor. A high temperature coating resin is applied to the composite honeycomb precursor to form the high temperature composite honeycomb
B32B 3/08 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
83.
PREPREG OR SEMIPREG PRECURSOR AND METHOD OF MANUFACTURING SAME
A prepreg or semipreg precursor comprising a fibre reinforcement and a resin composition fused thereto, the resin composition containing at least one epoxy resin and a latent curing agent, wherein the epoxy resin and the latent curing agent form a solid phase at ambient temperature, the latent curing agent forming a discrete phase within the epoxy resin. The stabilized uncured resin composition and prepregs and semipregs incorporating the same are easy to handle, have desirable curing temperatures and show good outlife at ambient to mid range temperatures.
Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy component, polyethersulfone as a toughening agent, and a curing agent. The resin matrix is also composed of a thermoplastic particle component that includes hybrid polyamide particles wherein each hybrid particle contains a mixture of amorphous and semi-crystalline polyamide.
This invention relates to a curative composition and its use in curing epoxy resins and prepregs, adhesives and moulded materials derived therefrom. The curative composition comprises a clathrate comprising a host component and a guest component, the host comprising a carboxylic acid or ester compounds as defined or phenolphthalin and the guest comprising an imidazole or imidazoline component.
A powder composition suitable for use in selective laser sintering for printing an object. The powder composition includes a first fraction having a polyetherketoneketone (PEKK) powder having a plurality of particles. The powder composition includes a second fraction having a plurality of siloxane particles that is dry blended with the PEKK powder prior to selective laser sintering of the powder. In some embodiments, the powder composition includes a third fraction of carbon fiber. The powder composition when used in selective laser sintering results in parts with more consistent results and improves process economics.
A system for producing an object from a powder by selective laser sintering. The system includes a chamber and a support platform in the chamber. A spreader applies a layer of powder to a bed surface. An irradiation source irradiates select points in the powdered layer prepared on the support platform. A radiant heater heats at least a portion of the bed surface. A temperature sensor monitors the temperature of select points on the bed surface. A controller adjusts the radiant heater in response to temperature data provided by the temperature sensor.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
A powder composition suitable for use in selective laser sintering for printing an object. The powder composition includes a first fraction having a polyetherketoneketone (PEKK) powder having a plurality of particles. The powder composition includes a second fraction having a plurality of siloxane particles that is dry blended with the PEKK powder prior to selective laser sintering of the powder. In some embodiments, the powder composition includes a third fraction of carbon fiber. The powder composition when used in selective laser sintering results in parts with more consistent results and improves process economics.
C09D 11/102 - Printing inks based on artificial resins containing macromolecular compounds obtained by reactions other than those only involving unsaturated carbon-to-carbon bonds
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B29C 64/20 - Apparatus for additive manufacturingDetails thereof or accessories therefor
B29K 71/00 - Use of polyethers as moulding material
The present invention relates to a reinforcement material including at least one fiber reinforcement associated on at least one of its faces with a porous layer, the porous layer(s) representing no more than 10% of the total weight of the reinforcement material, preferably from 0.5 to 10% of the total weight of the reinforcement material, and most preferably from 2 to 6% of the total weight of the reinforcement material, characterized in that the porous layer contains a partially cross-linked thermoplastic polymer. Another object of the invention is a precursor material of such a reinforcement material, as well as their preparation method and the methods for manufacturing a preform or a composite part from such materials.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/09 - Interconnection of layers by mechanical means by stitching, needling or sewing
B32B 3/10 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
The host compound in a clathrate is an amino or hydroxyl containing aromatic phosphorous compound, clathrates containing a resin curative and their use in curable resin compositions to produce moulded articles particularly fibre reinforced articles.
C08G 59/00 - Polycondensates containing more than one epoxy group per moleculeMacromolecules obtained by reaction of epoxy polycondensates with monofunctional low-molecular-weight compoundsMacromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
C09J 163/00 - Adhesives based on epoxy resinsAdhesives based on derivatives of epoxy resins
A self-adhesive prepreg comprising a fibre reinforcement layer having a first side and a second side, wherein the first side of the fibre reinforcement layer has been pre-impregnated with a self-adhesive resin composition. The self-adhesive may be used as a structural reinforcement and is especially adapted for direct bonding to oily steel or galvanized steel in the automotive, aerospace and other sheet metal fabrication industries.
An assembly (113) for composite manufacture is provided. The assembly comprises a cured resin impregnated reinforcement material (112) comprising a fibre component and a resin matrix component, in which the resin matrix component comprises polyurethane, the assembly having a length to width ratio of at least 5:1, and the assembly defining a longitudinal direction (L) along its length; and a peel ply (116) in contact with the cured resin impregnated reinforcement material (112), the peel ply (116) comprising a woven layer having a plurality of longitudinal fibres (118) extending in the longitudinal direction (L); and a plurality of transverse fibres (120) extending in a transverse direction (T) normal to the longitudinal direction (L); in which the areal density of the plurality of transverse fibres (120) is higher than the areal density of the plurality of longitudinal fibres (118).
A semipreg that can be cured/molded to form aerospace composite parts including rocket booster casings. The semipreg includes a fibrous layer and a resin layer located on one side of the fibrous layer. The resin layer includes an epoxy component that is a combination of a hydrocarbon epoxy novolac resin and a trifunctional epoxy resin and optionally a tetrafunctional epoxy resin. The resin matrix includes polyethersulfone as a toughening agent and a thermoplastic particle component.
B29C 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
B29B 15/12 - Coating or impregnating of reinforcements of indefinite length
There is provide a process for unwinding material from a spool (2) wherein the angle (Θ) of take off at the first contact point (4) for the unwind is always in the range 0±20°, and wherein the first contact point (4) for the unwind is no more than 600 mm from the axis (3) of rotation of the spool (2). There is also provided an apparatus for the unwinding of material from a spool (2) comprising an axis (3) upon which a spool (2) may be rotatably mounted and a static first contact point (4) for the unwound material positioned no more than 600 mm from the centre of the axis (3), wherein the angle (Θ) of take off at the first contact point (4) for the unwind is always in the range 0±20°.
A powder composition suitable for use in laser sintering for printing a three-dimensional object. The powder composition includes a polyaryletherketone (PAEK) powder having a plurality of particles. The plurality of particles having a mean diameter of D50. The composition includes a plurality of carbon fibers having a mean length L50. L50 is greater than D50. The particles are substantially non-spherical. A portion of the carbon fiber is embedded into the particle via high intensity mixing.
B33Y 70/00 - Materials specially adapted for additive manufacturing
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B02C 23/10 - Separating or sorting of material, associated with crushing or disintegrating with separator arranged in discharge path of crushing or disintegrating zone
C08G 65/46 - Post-polymerisation treatment, e.g. recovery, purification, drying
C08G 65/40 - Macromolecular compounds obtained by reactions forming an ether link in the main chain of the macromolecule from hydroxy compounds or their metallic derivatives derived from phenols from phenols and other compounds
06 - Common metals and ores; objects made of metal
17 - Rubber and plastic; packing and insulating materials
Goods & Services
Metallic cellular core material and metallic sandwich panels for use in manufacturing aerospace, space and defence, recreation, electrical, architectural, marine, transportation and general industrial products; Metallic honeycomb and metallic sandwich panels. Soundproofing materials for airplane engines and other portions of airplanes in the nature of cellular core material with inserts for noise reduction.
A fast cure cycle for thermocurable resins coupled with long storage stability is achieved by applying a curative containing particulate cure initiator to the surface of a layer of the thermocurable resin and by employing conditions of temperature and pressure that drive the curative into the resin to cause rapid cure of the resin.
An adhesive composition comprising a silane-modified epoxy resin, a dicyclopentadiene novolac epoxy resin and a curing agent. The composition shows good oily steel bonding, even in the absence of CTBN rubber or rubber adducts as toughening agents, with good Tg values of the cured resin and good Tg retention after hot wet aging.
C08G 59/14 - Polycondensates modified by chemical after-treatment
C08G 59/32 - Epoxy compounds containing three or more epoxy groups
C08G 59/40 - Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups characterised by the curing agents used
A powder composition suitable for use in selective laser sintering for printing an object. The powder composition includes a first fraction including a plurality of polyaryletherketone (PAEK) particles having a mean diameter less than 30 microns, a second fraction having a plurality of polyaryletherketone (PAEK) particles having a mean diameter greater than 30 microns, and a third fraction having a plurality of carbon fibers. The first fraction and the second fraction are formed by an air classification separation performed on a pulverized powder. After the separation, the first fraction, the second fraction, and the third fraction are blended in a high intensity mixer. The powder composition when used in selective laser sinter results in parts with increased tensile strength and reduced surface roughness, among other improvements, as compared to similar powders omitting the first fraction. The PAEK may include polyetherketoneketone (PEKK).
A method of manufacture of a composite component is provided, the method comprising the steps of providing two layers of pre-preg composite material, one of which has an edge adjacent a surface of the other. Pressure and, optionally, vibrational energy is applied to the edge to thereby smooth the ply drop.
