Abstract: A process of production of a monolithic article from a web of fibres of oriented polypropylene polymer, comprising the steps of subjecting the web to elevated temperature and pressure sufficient to melt a proportion of the polymer and compact it, and then cooling the compacted web, wherein an accelerated rate of cooling is employed down to 100° C. The process is of particular benefit when the weight average molecular weight (Mw) of the fibers is 250,000 or below. The resultant articles have good stiffness and strength, yet with reasonable ductility. Similar articles cooled slowly are brittle.

Abstract: A composite fabrication apparatus which may include a first tooling die and a second tooling die movable with respect to each other; a thermal control system having induction coils disposed in thermal contact with the first tooling die and the second tooling die; a first die susceptor provided on the first tooling die and a second die susceptor provided on the second tooling die and connected to the induction coils; and a cooling system disposed in thermal contact with the first tooling die and the second tooling die. A composite fabrication method is also disclosed.

Abstract: A method of fabricating a composite article comprising the following steps. A plurality of support templates is provided. The support templates are arranged to define a shape of the composite article. A plurality of primary panels are provided, where each primary panel defines at least one edge, a first surface, and a second surface. The first surface of the plurality of primary panels is secured to the plurality of templates such that at least one edge of one of each the primary panels is adjacent to at least one edge of another of the primary panels and the primary panels conform to the shape of the composite article. The adjacent edge portions of adjacent primary panels are joined.

Abstract: The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.

Abstract: A method of making tough, water-proof building panels depositing a first fiber-rich layer onto a support, the first fiber-rich layer having a width defined by first and second side edges, a length direction, and a top surface; placing foam blocks on the first layer, lengths of the foam blocks extending generally between the first and second side edges of the first fiber-rich layer; depositing a second fiber-rich layer onto the combination of the first fiber-rich layer and the foam blocks, thereby to develop an uncured precursor to the building panel; and curing the uncured precursor to the building panel thereby to make a generally rigid structural building panel.

Abstract: A method of forming a fishing rod with at least one integrally formed support includes providing a bladder over a mandrel, wrapping a resin-impregnated material over the bladder to provide a wrapped resin-impregnated material, removing the mandrel from the wrapped resin-impregnated material, folding the wrapped resin-impregnated material onto itself at least once to form a tubular body, wherein folding the wrapped resin-impregnated material forms at least two separate bladder portions and the integrally formed support within the tubular body, placing the tubular body into a mold, and molding the tubular body to provide the fishing rod with the integrally formed support.

Abstract: A composite laminate includes a plurality of sheets of prepreg stacked one over another, and a scrim layer provided on an exterior surface of the sheets of prepreg. Each prepreg sheet is formed of fibers preimpregnated with resin. The scrim layer and the sheets of prepreg form a composite laminate whereby the scrim layer constitutes an outer, exposed surface of the composite laminate. The scrim layer may be a nonwoven carbon or glass fiber scrim that has absorbed resin from the sheets of prepreg. A method of making a composite laminate includes placing into a mold a scrim and a plurality of sheets of prepreg, with the scrim extending between an exterior surface of the sheets of prepreg and an inner surface of the mold; forming a composite laminate whereby the scrim is adhered to the sheets of prepreg; and removing the composite laminate from the mold. An outer layer of the composite laminate includes the scrim.

Abstract: Methods for making components having improved erosion resistance including providing a component having a surface, applying at least one layer of an erosion system to at least a portion of the surface of the component, each layer of the erosion system containing a support, and a toughened resin applied to the support, and co-molding the component having the applied erosion system to produce a coated component having from about a 50% increase to about a 400% increase in erosion resistance per layer of the erosion system.

Abstract: A mold and method for vacuum assisted resin transfer molding of a fiber reinforced laminated structure are provided. The mold includes a first mold part and a second mold part. The first mold part defines a negative impression of the laminated structure, being structurally stable and forming a support for fiber reinforcement layers of the laminated structure. The second mold part connectable to the first mold part for closing the mold and defines together with the first mold part an enclosed space which can be evacuated. The mold further includes a flow duct for guiding a liquid polymer which is formed as a recess in the first mold part and/or a recess in the second mold part that is open towards the enclosed space and extends along a section of the periphery of the first mold part and/or the second mold part.

Abstract: The instant disclosure relates to a laminated composite and methods of making the same. The laminated composite includes a plurality of stacked prepregs having an interface formed between each pair of adjacent prepregs. Each prepreg includes a matrix material and reinforcing fibers dispersed therein. At least one fibrous veil is laminated to at least a portion of at least one of the interfaces, the at least one fibrous veil having graphite nano-platelets attached to at least one surface thereof.

Abstract: A process for producing mosaics, tiles or various figures where the construction of these items retains the article or design inside the mosaic, tile or figure. The article or design may be of many different themes, such as underwater life including fish, shells and sea plants. Other themes might include, but not be limited to, trees, flowers, vegetables, fruits, etc. These finished mosaics, tiles or figures can be displayed anywhere that will allow the mounting of a tile such as in bathrooms, on walls, ceilings, floors, swimming pools (interior or exterior), etc.

Abstract: The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.

Abstract: The present invention relates to an apparatus and a method to activate a binder on a semi-finished fiber material containing carbon fibers or on a preform. The binder is applied to the semi-finished fiber material or the fiber preform and subsequently activated through increasing the temperature by conducting an electrical current through the carbon fibers of the preform.

Abstract: This invention is A prepreg comprising a reinforcing fiber base material impregnated with a thermoplastic resin, wherein the reinforcing fiber base material comprises from 0 to 50% by mass of reinforcing fibers each having a fiber length of more than 10 mm, from 50 to 100% by mass of reinforcing fibers each having a fiber length of from 2 to 10 mm, and from 0 to 50% by mass of reinforcing fibers each having a fiber length of less than 2 mm, the average of two-dimensional orientation angles each formed by a reinforcing filament (a) and a reinforcing filament (b) intersecting the reinforcing filament (a) is from 10 to 80°, the thickness h0 (mm) at 23° C. is 0.03 to 1 mm, and the tensile strength ? is 0.01 MPa or more. The prepreg can be applied for thin molded products which have been considered unsuitable as a laminated molded product and can provide molded products that have a complicated shape and have isotropically high mechanical properties.

Abstract: An epoxy resin composition suitably used for a prepreg which can complete curing in a short time even at a low temperature and secure a sufficient usable period under preservation at room temperature, in comparison with conventional epoxy resin compositions. An epoxy resin composition comprising at least one of an epoxy resin, an amine compound having at least one sulfur atom in the molecule thereof, and a reaction product of an epoxy resin and an amine compound having at least one sulfur atom in the molecule thereof, and an amine compound having at least one sulfur atom in the molecule thereof, and a urea compound and a dicyandiamide, wherein each of the contents of the sulfur atom and the urea compound in the epoxy resin composition is respectively 0.2 to 7% by mass and 1 to 15% by mass.

Abstract: Hardboards and laminates containing one or more layers of scrap carpet, with or without optional external and/or internal layers of other materials, including fibers, particles, liquids, woven and nonwoven fibrous mats, fabric and scrim, and shredded scrap carpet, and the are disclosed. The systems and methods for making the hardboard and laminates using cyclical or continuous hot consolidation are also disclosed. Various uses for the hardboard and laminates are also disclosed.

Abstract: Tooling aids for applying pressure in laminating, and methods for their use, are described herein. In one embodiment, a caul for applying pressure in laminating includes a base portion positioned between first and second corner portions. The base portion can have a curved shape when it is in a relaxed state, but it moves to a flatter shape when subjected to pressure during lamination. Movement of the base portion to the flatter shape causes the first and second corner portions to move outwardly and away from the base portion. In this manner, the caul can be used to compact laminating materials into corner regions of a corresponding female mold surface.

Abstract: The invention relate to a process for forming a cured, partially cured or uncured thermosetting material, comprising: an irradiation step wherein the thermosetting material is exposed to electromagnetic radiation which to a significant extent is within the neat-infrared range in such a way that the temperature of the irradiated thermosetting material is brought to between 40° C. and 400° C., and a forming step wherein the irradiated thermosetting material is brought into a desired shape, whereby the forming step is executed during and/or subsequent to the irradiation step. The invention also relates to an apparatus for carrying out the said process and to a thermosetting material.

Abstract: A method of manufacturing a composite element. A stack of plies is assembled on a lay-up table, each ply comprising a plurality of reinforcement elements such as dry-fibres. A first part of the stack of plies is bound to form a partially bound stack of plies, a second part of the stack of plies remaining unbound. The partially bound stack of plies is press-formed in a mould cavity between a pair of mould tools to form a shaped pre-form, plies in the second part of the stack sliding against each other during the press-forming. A liquid matrix material is injected into the shaped pre-form in the mould cavity and subsequently cured.

Abstract: The invention pertains to a method for manufacturing a FRC/FRP-component component from rovings by means of a moulding tool with a mould surface, featuring the steps of: applying rovings formed of dry fibers onto the mould surface by depositing the rovings under tension with predetermined orientations between deflection devices by means of an application device, applying binder material onto the tensioned rovings; consolidating the arrangement of fiber strands and binder material by applying heat and pressure in order to produce a preform for the component to be manufactured; separating the preform from the deflection devices and removing the preform from the moulding tool; and carrying out an injection process or infusion process in order to manufacture the component after separating the preform from the deflection devices; as well as to a moulding tool and a device for implementing the method.

Abstract: A method for producing a fiber-reinforced composite member from prepregs of reinforcing fibers impregnated with a matrix resin, comprising placing the prepregs in a cavity of a molding die, cutting off excess margins of the prepregs along the edges of the cavity, and curing the matrix resin.

Abstract: A curved composite element is laid up over a tool having first and second curved tool surfaces possessing differing radii of curvatures. A plurality of composite fiber ply segments are arranged in substantially side-by-side relationship into a group. The ply segments are formed as a group onto the first curved tool surface, and the group is then formed from the first curved tool surface onto the second curved tool surface.

Abstract: A method is provided for making a composite laminate aircraft skin for a fuselage in multiple composite panels. A resin-impregnated composite tape is placed on a lay-up surface of a mandrel tool to form the composite laminate aircraft skin as a barrel that is substantially the shape of a fuselage section. The barrel is cut into a plurality of panels on the mandrel tool, and at least one panel of the plurality of panels is transferred, individually and independently of all other of the plurality of panels, from the lay-up surface of the mandrel tool to a first cure tool of a plurality of cure tools having an aero surface tooled to an outer mold line. The at least one of the panels is cured on the first cure tool to form a cured composite panel. The first cure tool defines and controls the outer mold line of the at least one panel. The cured composite panel is removed from the first cure tool.

Abstract: The invention relates to a process for making swaged lighting holes (1) in planar areas of parts (5) made of preimpregnated composite, by means of which the part (5) is arranged between a female tooling (11) with the final shape of the bottom side of the swaged part and a caul plate (19) with the final shape of the top side of the swaged part, except in an area (3) which must be swaged, pressure P1 is applied on the caul plate (19) in the area of the part (5) that must be maintained substantially planar, and pressure P2 is applied by means of a male tooling (17) on the area (3) of the part (5) which must be swaged at a forward speed allowing the flow of the resin during the slippage of the fibers of the material so that it may deform, adapting to the final shape of the female tooling (11).

Abstract: A sports racquet having a plurality of string port holes and conventional string holes is formed of a single tube of prepreg material. When molded, mold elements press opposed portions of the prepreg tube into contact with one another, and shape the adjoining prepreg material into a string port hole blanks. The portion of the pressed-together material which initially blocks the string port hole is removed after molding so that the string port holes extend through the frame. Alternatively, the mold elements cause the prepreg tube to follow a serpentine shape, thereby defining string port holes which are open alternately along the top and bottom surface of the frame. A pair of cover rings may be secured to the top and bottom racquet surfaces to cover the open sides of the string port holes.

Abstract: The invention relates to a membrane filter unit for liquid or gaseous media, comprising a bundle of capillary membranes which are open on at least one front surface side and which are cast in an area which is close to the end of the open membrane ends, in a sealing layer forming a hardened head part. The open membrane ends protrude on the outer side of the sealing layer. The sealing layer is arranged on a spacer element which has a layer which is penetrated by the capillary membranes and which is non-permeable in relation to the casting material which hardens in order to form the sealing layer. The invention also relates to a method for the production of a membrane filter unit.

Abstract: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fiber layers is largely completed in a first forming step, while in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.

Abstract: A method of making an aircraft component is provided, wherein the method comprises the steps of: providing a mould (1) for the receipt of a material (3) from which the aircraft component is to be made providing the mould with said material providing an intensification tool (14) in spaced relationship to the mould and heating the material, tool and mould so that the tool expands and applies pressure to the material and so as to form the component and wherein the linear coefficient of thermal expansion of the tool in a first direction is matched to the coefficient of thermal expansion of the component in the first direction, and the coefficient of thermal expansion of the tool in a second direction is greater than the coefficient of thermal expansion of the component in the second direction, the tool being provided with at least one contacting surface for contacting the material and through which pressure is applied to the material, the expansion of the tool in the second direction causing the at least one cont

Abstract: A method for the manufacture of spatial objects of a fleece or felt, wherein the fibers are deposited on a mold that is preferably air-permeable. The fibers may be attracted to the mold by a vacuum applied to the underside of said mold. Preferably, the mold has several spatial structures that define the shape of the fiber web that is being formed and that correspond at least approximately to the desired final shape. By subsequent compacting of the thusly obtained fiber web, a spatially three-dimensional felt object is obtained. In this method, subsequent deforming steps are unnecessary or reduced to a minimum, so that the material to be produced does not experience any substantial distortion.

Abstract: An article (10) such as a grid fin that controls the direction of flight of a vehicle, has precisely formed passages (14) with porous locating walls (52A, 52B) and a layer of fibrous material (86) such as graphite cloth lying against one or both opposite sides of the locating wall, and with the locating wall and fibrous material impregnated with resin (84). Locating blocks (30) of foam are molded and the fibrous material (42) is wrapped around each block. The wrapped blocks (44) are each inserted into a passage (54) of a locating grid (50), so the fibrous material is compressed. The locating grid lies in a grid-holding mold (60). With the fiber-wrapped blocks inserted, the grid-holding mold is closed and resin is injected into the mold and allowed to harden. The foam blocks are removed by eroding them, as by sand blasting them, to leave a final article.

Abstract: A new cladding panel for use on recreational vehicles is produced by either a hand-laid or vacuum infusion process. In hand-laid method, the cladding is formed by first introducing and curing a layer of gel coat onto a mold surface. Layers of fiber reinforced resin material are subsequently laid onto the gel coating and molded to form the cladding panel. In the vacuum infusion process, the gel coating is first laid onto a mold surface of a vacuum infusion mold, and then a dry ply materials are laid onto the gel coating. The mold is closed and a resin component is infused into the dry laminate material under vacuum pressure and cured. The cladding panels produced by these methods produced are seamless and have limited waste associated with post-production trimming processes. Cladding panels produced using the vacuum infusion process have a more consistent composition and achieve improved part-to-part consistency.

Abstract: A method for fabricating stringers is provided. The co-cured composite stringer includes a stringer and a mandrel positioned within a channel defined in the stringer. A plurality of strips are positioned within an opening of the mandrel, and a substrate layer, such as aircraft skin, is positioned adjacent to the stringer. During application of the substrate layer to the stringer, the mandrel and plurality of strips support the stringer.

Abstract: The invention relates to a method of producing a shell member of fiber composite material by means of vacuum infusion, where the fiber material is impregnated with liquid polymer, and applying a mould (18) with a mould cavity. In the mould cavity a lower distribution layer (11) is placed. A fiber insertion (1) including a plurality of fiber layers is placed above the lower distribution layer (11). A first upper distribution layer (9) and a second upper distribution layer (10) are placed at a transverse distance of each other above the fiber insertion, so that at least a part of the first distribution layer overlaps a first zone (2) of the fiber insertion (1), and at least a part of the second distribution layer overlaps a second zone (3) of the fiber insertion (1), the first zone (2) and the second zone (3) being separated by an intermediate zone (6) neither overlapping the first nor the second distribution layer (9, 10).

Abstract: A resin containment and injection system includes a tool, a resin storage well provided in the tool, a composite layup location provided on the tool and a vacuum bagging film provided over the resin storage well. The vacuum bagging film is configured to define a volume in the resin storage well responsive to establishment of a pressure equilibrium across the vacuum bagging film and substantially eliminate the volume responsive to application of positive pressure against the vacuum bagging film.

Abstract: A filter element comprises a top frame member, a bottom frame member and a pleated filter assembly received in respective channel sectioned formers comprised by said top and bottom frame members. The formers are integrally bonded with a polyurethane resin core formed in the formers. A mould may include a core member or projections which maintain air passages during moulding, and serve to locate the pleats of the filter element in relation to the air passages.

Abstract: Methods of making a fiber-reinforced composite article are described. The methods may include providing fibers to an article template, where the fibers have been treated with a coupling-initiator compound. They may further include providing a pre-polymerized mixture that includes a monomer and a catalyst to the article template. The combination of the fibers and the pre-polymerized mixture may be heated to a polymerization temperature where the monomers polymerize around the fibers and form at least a portion of the composite article. The article may then be removed from the article template. Examples of the fiber-reinforced composite articles may include wind turbine blades for electric power generation.

Abstract: A method of making an armrest that is mountable between adjacent left and right passenger seats includes: separately forming two receptacle parts by molding a prepreg in a first mold assembly, the receptacle parts being adapted to hold personal objects and each having a looped wall surrounding a slot; forming an armrest frame by molding a prepreg in a second mold assembly, the armrest frame including a lower frame portion having a plurality of downwardly extending legs, and an upper frame portion disposed on top of and bridging the legs; and positioning the receptacle parts within the second mold assembly and combining the receptacle parts with the upper frame portion during the forming of the armrest frame in the second mold assembly, thereby providing a one-piece unitary structure having the receptacle parts and the armrest frame.

Abstract: A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.

Abstract: An object of the present invention is to improve the abrasion resistance and controllability in a golf ball having a polyurethane cover containing a layered silicate or the exfoliated layer thereof. The present invention provides a golf ball comprising a core and a cover covering the core, wherein the cover comprises a polyurethane resin having a secondary or tertiary amine structure in a molecular chain thereof, the secondary or tertiary amine structure being cationized, and a layered silicate and/or an exfoliated product thereof, having an average aspect ratio of unit layers thereof ranging from 10 to 50.

Abstract: A method of producing a bicycle rim including, positioning a first quantity of woven fiber strips having a first width and a first length and a second quantity of strips of said woven fibers having a shape different from the first shape to form a first laminated band from the first quantity and the second quantity of strips. A second narrower laminated band is produced. The first band is re-shaped to a V-shaped band before the first band is inserted along the periphery of a mold interior. A core is positioned on the first band and the second band is positioned on the first band. Rim well rings are positioned from outside on the second band, to abut the sides of the second band. A spreader ring is inserted between the rings to join the material near the upper rim flanks and the rim flanges.

Abstract: A high quality finished prototype fuselage structure of an aircraft is manufactured using a cured female tool and an automated composite layup machine, and then touched up by hand to meet a tolerance or other specification. The female tool is preferably made from a male mold, by depositing layers of composite material over the mold, curing the tool together at a first cure temperature, separating the tool from the mold, and then curing the tool at a second, higher temperature. The first cure temperature should be at or below an upper limit temperature no greater than 180° F. The second cure temperature is preferably in the range of 250° F. to 350° F. The step of hand touching up can comprise one or more of mechanically abrading and deforming a first portion of the fuselage structure to mate with a second portion of the fuselage structure.

Abstract: The invention relates to an apparatus (10) for taking up, positioning and draping dry textile fiber semi-finished products (34) and comprises a housing (12) with an open housing side, a membrane (14) disposed inside the housing (12) and running parallel to the open housing side, which divides the housing (12) into a first upper chamber (16) and a second lower chamber (18), as well as at least one fluid guidance opening (22, 24) disposed in the first chamber (16) for pressure control in the upper chamber and for supplying and removing a heatable fluid into the upper chamber (18). The membrane (14) is formed from a flexible and fluid-tight material and the membrane (14) comprises a plurality of suction heads (26) directed into the lower chamber (18), the suction heads (26) being connected via a flexibly configured suction line (30) guided through the upper chamber (16) to a vacuum shaft.

Abstract: An apparatus and methods for forming a composite part are provided. A method for forming a composite part may include placing initial composite material on a base tool, placing a tooling mandrel on the composite material, placing additional composite material over the tooling mandrel, covering at least a portion of the composite material that overlays the tooling mandrel with a composite forming tool, heating the composite material to at least partially cure the composite material, and permitting a first portion of the composite forming tool to change size during the heating of the composite material to a greater degree than a second portion of the composite forming tool. In this regard, the second portion of the composite forming tool is closer to the base tool than the first portion of the composite forming tool. A composite forming tool is also provided that permits differential expansion of different portions of the tool.

Abstract: A method for preparing a high-temperature heat-resistant composite material by combining a mixture of submicron alumina powder and submicron silica powder, wherein the ratio of alumina to silica is from about 4:1 to about 5:1, submicron Group II metal oxide powder, and a Group I metal silicate solution to form a slurry, wherein the weight of the Group II metal oxide powder is an amount corresponding to about 5% to about 10% of the weight of the silicate solution; contacting reinforcing high-temperature resistant fibers with the slurry to form a composite precursor composition; and curing the composition at a temperature sufficient to produce the high-temperature heat-resistant composite material capable of resisting temperatures up to about 1400° C. Composite materials prepared according to the method and articles incorporating the material are also presented.

Abstract: A test blade and a method for fabricating the test blade are presented for use in calibrating a tomography system configured to inspect turbomachine blades for defects. The test blade may include a three-dimensional fiber blank and a polymerized resin. The blank may be created by weaving synthetic material fibers. The resin may be configured to be injected into a mold as a liquid where the resin may polymerize around the fiber blank. The test blade may be configured to be modified to include particular defects such as cut fibers and/or cavity defects which are perceived by the tomography system. The dimensions of the cavity defects may be substantially created by pulling two or more fibers apart at a specific distance with a spreading tool.

Abstract: A process for the production of a structural part of an aircraft, whereby the part is made of composite material that includes a thermosetting resin and that has a section profile that can be stamped, whereby the process includes: producing a flat blank by draping layers of supports that are preimpregnated with thermosetting resin, partially cross-linking the flat blank, and stamping the flat blank between a matrix (14) and a punch (16) that are called the equipment, each including an impression that is adapted to the shape of the surface that is in contact with the part that is to be produced and whose air gap is sized based on the part that is to be produced, wherein the equipment is heated to modulate the progress of the cross-linking at the end of the forming operation.

Abstract: A robot hand member mounted on an arm unit of an industrial robot and a method of producing the same, wherein there are successively executed a step of laminating prepreg sheets each containing a reinforcing fiber on the outer peripheral surface of a core member having a predetermined shape in cross section, a step of heating the laminated prepreg sheets to a predetermined temperature to thermally set, to form a fiber reinforced plastic, and a step of removing the core member from the fiber reinforced plastic to obtain a hollow structure.

Abstract: A curved reinforcing fiber substrate having a curved planar shape comprising a plurality of reinforcing fiber yarns arranged parallel to a direction along a circumferential direction of the curved shape, and auxiliary weft yarns arranged in directions crossing the plurality of reinforcing fiber yarns each arranged in one direction of the circumferential direction.

Abstract: A tool for the infusion of a resin into a preform made of fibre material includes a mould which can be closed around the preform and in the body of which at least one inlet duct is formed to allow resin to be injected into the mould so that the resin can be infused into the preform. At least one reservoir which can contain the resin, is also formed in the body of the mould and is connected to the at least one inlet duct. The mould can be inserted in an autoclave and the reservoir is configured to permit the transfer of the resin from the reservoir to the inlet duct under the effect of the temperature and of the pressure that are produced in the autoclave, thus allowing the resin to be injected into the mould.

Abstract: A construct for a hockey blade that includes a foam core. The foam core includes a first core face, a second core face, and a core edge. A first layer of resin preimpregnated tape is wrapped continuously around the first core face, the core edge and the second core face. A thread is stitched along the first layer of preimpregnated tape. A second layer of resin preimpregnated tape wrapped continuously around the first layer of resin preimpregnated tape.