Abstract: A fiber reinforced core panel is formed from strips of plastics foam helically wound with layers of rovings to form webs which may extend in a wave pattern or may intersect transverse webs. Hollow tubes may replace foam strips. Axial rovings cooperate with overlying helically wound rovings to form a beam or a column. Wound roving patterns may vary along strips for structural efficiency. Wound strips may alternate with spaced strips, and spacers between the strips enhance web buckling strength. Continuously wound rovings between spaced strips permit folding to form panels with reinforced edges. Continuously wound strips are helically wrapped to form annular structures, and composite panels may combine both thermoset and thermoplastic resins. Continuously wound strips or strip sections may be continuously fed either longitudinally or laterally into molding apparatus which may receive skin materials to form reinforced composite panels.

Abstract: A connection between composites with non-compatible properties and a method of preparing of such connections are provided. The composites comprise first and second type fibers, respectively, as well as resin. The connection comprises a transition zone between the composites having a layered structure. The transition zone may optionally comprise a transition member and the transition member may optionally be integrated with one or more of the composites. Examples of non-compatible properties where the present connection will be appreciated are great differences in stiffness, e.g. Young's modulus, or in coefficient of thermal expansion.

Abstract: A method for manufacturing a fiber-composite component with a cladding field and a primary component for reinforcing the fiber-composite component includes the steps of: applying a prepreg semifinished product to a mold to form the cladding field, where in the prepreg semifinished product fibers extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fiber-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fiber-composite fuselage component of an aircraft with a shell component with at least one re

Abstract: The invention concerns a wind power installation rotor blade. The rotor blade has a rotor blade root, a rotor blade tip, a rotor blade leading edge and a rotor blade trailing edge. The rotor blade further has a pressure side and a suction side as well as at least one web at least partially between the suction and pressure sides. The rotor blade has a longitudinal direction between the rotor blade root and the rotor blade tip. The web is of a wave-shaped configuration in the longitudinal direction of the rotor blade.

Abstract: An inflatable compaction tool for consolidating a composite material inside a faceted hollow or tubular mold for a composite part is made from an elastic material. The compaction tool includes relatively flat wall segments conjoined by corner segments that define a sealed chamber. The wall segments curve away from the mold surface toward the midpoint of each wall segment, so that as a pressurized fluid is introduced into the compaction tool, a component of the force exerted on the tool interior surface is transmitted through the wall segments toward the corner segments. Thus, during initial inflation, the corner segments are forced toward the corner regions of the mold before the wall segments contact the composite material, firmly compressing the composite material into the corner regions of the mold before the friction of the wall segments against the composite material inhibits expansion of the corner segments into the mold corner regions.

Abstract: A leaf spring for a motor vehicle is made from a fiber composite component including individual fibers in form of at least two textile layers stacked on top of each other and a matrix made of a duroplastic or thermoplastic resin surrounding the fibers. The resin is hardened in a mold tool by applying pressure and heat. The stacked textile layers are formed inside a mold tool and fixed by a dry binder applied to at least one of the textile layers to form a dry preform. A fiber composite blank is stamped from the preform and subsequently infiltrated with the resin in a RTM cavity and hardened. The binder applied in dry form may only be arranged in certain areas of the textile layers.

Abstract: The invention relates to a method of making a composite sheet. A plurality of layers is first assembled, each layer being comprised of an untreated, unidirectional array of strands. The assembled layers are then placed adjacent one another to form an assembled sheet, with adjacent layers being in a non-parallel orientation, and without any of the layers having been treated with a matrix or binding component. The assembled sheet is then impregnated with a matrix component, which comprises a binding component and may also comprise a radiation-absorbing component.

Abstract: A method of manufacturing an interior substrate material, e.g., for an automobile includes impregnating a sheet-shaped, nonwoven mat material, which consists of glass fibers, with a urethane-yielding liquid, and heating the mat material impregnated with the urethane-yielding liquid to foam and heat cure the urethane-yielding liquid in the mat material, thereby producing the interior substrate material.

Abstract: The present invention concerns a process for the production of a wind power installation rotor blade. To permit more economical manufacture at high quality the following steps are provided: providing at least one mold, placing a layered fiber composite having at least one core in the mold, wherein the core has a top side with first channel portions and an underside with second channel portions, and connecting portions between the first and second channel portions, and feeding resin, in particular through the first and/or second channel portions, until the layered fiber composite is adequately saturated.

Abstract: A composite fabrication apparatus which may include a first tooling die and a second tooling die movable with respect to each other; a temperature 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 resin transfer system delivers resin from a resin source to the tooling dies to allow resin transfer molding. A composite fabrication method is also disclosed.

Abstract: A composite structure is provided. The structure includes at least one ply of preimpregnated material formed into a curved elongated member of continuous fibers onto a mandrel. The fibers have a select orientation. The curved elongated member has a length and a cross-sectional geometry that varies along the length.

Abstract: Polymer articles are often reinforced by addition of fibers which may be assembled into a structured reinforcement such as a woven mat or sheet and the mat or sheet serves as the reinforcement. Such woven fiber-reinforced polymer composite articles may exhibit undesirable variations in surface height which mimic the geometry of the underlying reinforcements, a phenomenon known as print through. By forming, on the surface of the article, a relatively thin, layer of a compatible polymer incorporating closely-spaced, short, carbon nanotubes more or less uniformly dispersed throughout the layer and oriented normal to the article surface, print through may be reduced or eliminated. Methods for fabricating such an article are detailed.

Abstract: A stitching geometry and method for selective interlaminar reinforcement of a CMC wall (20A). The CMC wall is formed of ceramic fiber layers (22) individually infused with a ceramic matrix, stacked, and at least partially cured. A row of holes is formed in the wall, and a ceramic fiber thread (25) is infused with a wet ceramic matrix and passed through the holes to form stitches (28, 30, 31). The stitches are then cured, causing them to shrink more than any remaining wall shrinkage, thus tensioning the stitches and compressing the wall laminae together. The stitches may have through-wall portions (30, 31) that are angled differently in different wall areas as a function of interlaminar shear over interlaminar tension, optimizing wall reinforcement locally depending on magnitude and direction of shear. Alternate rows of stitches (54, 56) may have offsets in a stitch direction (34) and/or different through-wall angles (A1, A2).

Abstract: A method for fabricating an insulated flame retardant panel includes the provision of a mixture of rice hulls and adhesive adhered to one or more skins of the panel with pressure in which the adhesive is either a urethane adhesive or a sodium silicate adhesive that is set by applying pressure, with the rice hulls providing an R value comparable to that associated with expanded polystyrene foam or urethane foam but with significantly improved structural properties and without involving environmentally unfriendly processes.

Abstract: A complex-shaped, three-dimensional fiber reinforced composite structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers. The wetted fibers are arranged on pressurizable members and may be configured to include internal structural features, such as shear webs. A reinforcement stiffener may be located adjacent to at least one of the pressurizable members and the wetted fibers that form the internal structural feature. The reinforcement stiffener includes a modulus of elasticity that is substantially higher than a modulus of elasticity of the resin used to wet the fibers. In one embodiment, the reinforcement stiffener may be received in a pocket of one of the pressurizable members and may include a releasing agent that permits removal of the stiffener after the composite structure has been pressurized and cured.

Abstract: A method and apparatus for manufacturing composite components. A tool is present for use in manufacturing composite components. The tool comprises an encapsulation layer having a shape, an insulation layer on the encapsulation layer, and an isolation layer on the insulation layer. The isolation layer has an outer surface capable of contacting a composite material laid up on the outer surface. The insulation layer is capable of insulating the encapsulation layer from heat applied to the composite material. The encapsulation layer is capable of maintaining a shape with the composite material laid up on the isolation layer during a curing process to form a composite component from the composite material.

Abstract: A plurality of fibre layers is stacked to form a fibre insertion extending in a longitudinal direction of the shell part to be manufactured, whereby a core element having a tapered edge section is arranged along the fibre insertion. The fibre layers are stacked so that the tapered edge section of the core element is wedged into the fibre insertion. The core element is composed by a first and a second core part that are arranged along each other. The first core part forms at least part of the tapered edge section of the core element. The surface of the first core part has a higher permeability to liquid polymer than that of the surface of the second core part so that, during infusion, liquid polymer penetrates the surface of the first core part more readily than it penetrates the surface of the second core part.

Abstract: A fabrication method of forming curved thermoplastic composite laminate parts with tailored and varying thickness in a continuous process. Automated equipment or hand lay-up are used to collate parts or components into a multi-layer stack. Each stack contains all plies, including ply build-up areas, tacked in the proper location to maintain orientation and location. Ply consolidation tooling contains all necessary part features and is coordinated to the customized multiple ply stacks to form a single integrated thermoplastic composite laminate potentially having areas of differing thickness from the multiple ply stacks.

Abstract: A die for producing pressed, fiber-reinforced plastic components, as well as a method for producing the plastic component, and the plastic component itself. The plastic components comprising at least two structural parts which overlap one another a pressing direction such that the die comprises at least one upper die portion formed with a pressing unit for applying a pressing force in the pressing direction, and at least one lower die portion which cooperates with the upper die portion to form a cavity in which the plastic component is formed. A die insert is fitted in the die and can move by and with the upper die portion and is designed to transmit the pressing force to the at least one structural part of the plastic component which is overlapped by the other structural part of the plastic component in the pressing direction.

Abstract: A method for manufacturing a preform and a preform manufactured by the method includes a plurality of substrates to which a binder has been affixed laminated to form a laminate and a forming die is used to form the laminate, thereby manufacturing a preform which is a precursor in resin transfer molding (RTM) of fiber reinforced plastic (FRP). During the manufacturing the laminate is pressed into a predetermined shape by the forming die, the binder is melted by directly heating the binder of the substrates in the laminate being pressed or both and is cooled thereafter to solidify the binder, and the substrates are adhered between layers thereof to retain the formed shape of the preform.

Abstract: The present invention relates to a jig for the manufacture, by means of injection and curing processes, of preforms of composite material frames for aircraft fuselages by using the RTM (resin transfer molding) technology. Two preforms are thus manufactured, one with a C shaped section and another with a L shaped section, together with the preforms of the stabilization ribs for stabilizing the web of the frames and the preform of the roving or staple fiber to cover the gap between the C shaped preform and the L shaped preform. Theses preforms are previously manufactured by any known process for manufacturing preforms. According to a second aspect, the present invention relates to a method of manufacturing composite material load frames for aircraft.

Abstract: The invention relates to a process for the manufacture of a shaped part comprising the steps of—forming a stack by stacking (2) or more sheets comprising mono-layers of unidirectional anti-ballistic fibers and a binder followed by placing the stack in a mould, clamping the stack in the mould with a control member closing the mould—consolidating the stack under temperature and pressure into a curved shaped part. The invention furthermore relates to products obtainable with said process, which are very suitable for use in anti-ballistic applications and include e.g. helmets, curved panels, cones and domes.

Abstract: A composite transmission housing includes resin transfer molding or vacuum assisted resin transfer molding manufacturing processes combined with discontinuous fiber preforms. The preforms are assembled in a prepared injection and cure mold with additional details and fillers. The preforms are constructed such that the preforms are assembled into the mold in a specific order to assure proper arrangement. Using a combination of vacuum and pressure, a resin is injected into the mold to completely infuse the assembled preforms. At completion, the mold is heated to the resin cure temperature and held at this temperature for sufficient time to insure complete cure.

Abstract: A method of manufacturing a panel made of a composite material using a tool having a support on which a lay-up is performed, the lay-up producing a stack of plies of fiber prepregs, followed by consolidating the stack aiming to obtain the panel using a compacting plate arranged above the stack. The method is implemented such that a first set of polyimide films partially covering each other is located in contact with the stack of plies, between the latter and the compacting plate.

Abstract: A process for producing a molded fiber-reinforced resin by an RTM method includes disposing a molding precursor in a molding cavity of a mold; closing the mold in which the molding precursor is disposed; injecting a heated and pressurized resin into the molding cavity of the mold closed; solidifying the resin injected into the molding cavity; opening the mold after the resin has been solidified; and taking out the molded fiber-reinforced resin from the mold opened.

Abstract: An adhesive adapted to enable spray delivery and seamless polymerization during epoxy resin vacuum infusion techniques.

Abstract: A resin transfer molding process for an article incorporating a protective insert of polymer material such as polyether ether ketone (PEEK). A piece of PEEK material is cut and thermoformed to the required shape and then placed in position in a mold. A bead of elastomer material is formed around the edge of the insert to seal it against an internal wall of the mold in order to prevent resin tracking between the mold and insert faces during subsequent injection into the mold.

Abstract: A tool for the infusion of a resin into a preform made of fiber 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: An apparatus to prepare a preform for fabrication includes a mandrel, anchoring groove, anchoring device, tensioning groove, and tensioning device. The mandrel receives the preform. The mandrel has a first mandrel end and a second mandrel end. The preform has a first preform end and a second preform end. The anchoring groove is disposed at the first mandrel end. The anchoring device is configured and located to urge the first preform end towards the anchoring groove to secure the first preform end therebetween. The tensioning groove is disposed between the first mandrel end and the second mandrel end. The tensioning device is configured and located to urge a portion of the preform into the tensioning groove.

Abstract: Absorbent members and methods of making the same are disclosed. In one embodiment, the absorbent member is a unitary absorbent fibrous web having a density profile through its thickness. In one embodiment, the density profile is relatively centered through the thickness of the web and the maximum density of the web is located between about 35% and about 65% of the distance through the thickness of the web. In one embodiment, the method involves subjecting a precursor web to at least one cycle (or pass) through a mechanical deformation process. Typically, the method involves subjecting the precursor web to multiples cycles (or passes) through a mechanical deformation process.

Abstract: A matched mold curing apparatus defining a molding cavity has two sets of layers of curable, fiber-reinforced, thermosetting composite material laminated on a lower forming tool and upper forming tool. Closed-cell foam core segments are provided and placed adjacent to each other on the layers. The core segments are oversized with respect to the nominal size determined by the molding cavity in the closed condition, minus the thickness of the layers of composite material. A controlled temperature is applied firstly to allow plastic deformation of the core segments, but without closing completely the matched mold. The temperature and pressure are then applied to cause complete closure of the matched mold and curing of the laminated layers.

Abstract: A method for manufacturing a hollow load-bearing beam structure of fiber-reinforced composite material. The method includes preparing a first lay-up of a first plurality of layers, and a second lay-up of a second plurality of layers. The first and second lay-ups are positioned on different sides of a mandrel and formed to a beam structure by bending the lay-ups against the mandrel, such that the side edges of the respective layers of the first and second lay-ups are arranged as offset butt joints in the circumferential direction of the formed beam structure.

Abstract: A computer implemented method, apparatus, and computer usable program code for providing ply lay-up data for a composite part. A designation of a location is received for the composite part in a three dimensional object from a requester. A three dimensional model is opened in which the composite part is located. The ply lay-up data is extracted for a section within the composite part within the three dimensional model to form extracted ply lay-up data for the section. An output file is created containing a drawing of the composite part overlaid with a grid containing the section with the ply lay-up data identifying a ply stacking sequence, an orientation of each ply in the ply stacking sequence, and a material for the each ply in the ply stacking sequence. The output file is returned to the requester.

Abstract: The present invention relates to a supporting structure (200) for a nacelle of a jet engine, in particular provided with a thrust reverser device, including at least one base body (201) made of a composite material, characterised in that the base body has a transverse section which is essentially open and provided with at least one reinforcement means.

Abstract: Components are produced by injecting a thermoplastic melt into a mold, wherein a flat blank of two or more fiber woven or non-crimp fiber fabrics connected at one or both sides thereof with a randomly oriented fiber layer and impregnated with a thermoplastic is heated to above the softening temperature of the thermoplastic, the thus expanded porous blank is laid out adjacent to one of the two inner walls of the mold, the mold is closed, compressing the blank, reopened to a desired width, and thermoplastic melt is injected into the porous core.

Abstract: A filter element (1), for example a cabin filter for a motor vehicle, includes a pleated fold pack (2), a plastic frame (4) that is molded at least in part to the fold pack (2) supporting pleat profiles (3), and a plastic foam seal (7) that is foamed at least in part onto the plastic frame (4). In a method for producing a corresponding filter element (1), a plastic frame (4) is generated at least in part around a fold pack (2) in a first injection molding process, and subsequently a plastic foam seal (7) is generated at least in part on the plastic frame (4) in a second injection molding process.

Abstract: Herein disclosed is a frac ball comprising three orthogonal axes x, y, and z; wherein the frac ball has approximately equal strength in each direction of the three axes x, y, and z. In an embodiment, the frac ball comprises a resin. In an embodiment, the frac ball comprises glass fibers or carbon fibers or both. In an embodiment, the frac ball comprises an equal amount of glass fibers in each direction of the x, y, and z axes. In an embodiment, the frac ball comprises glass fibers in the x and y axes and carbon fibers in the z axis. In an embodiment, the frac ball comprises no interlaminar layers. In an embodiment, the frac ball has different diameters. Also disclosed herein are methods of making and using such frac balls.

Abstract: Techniques and apparatus for providing a fly away caul plate are disclosed. In an embodiment, a method for curing a composite structure includes placing a pre-cured caul plate proximate an uncured composite lay-up, the lay-up may or may not include one or more stiffeners extending substantially perpendicular to the lay-up surface, the caul plate including an aperture for receiving the at least one stiffener. A force may be exerted against the caul plate to engage the composite lay-up. Heat and/or pressure may be applied to the composite lay-up to cure the stiffener panel and co-bond the caul plate to the composite lay-up.

Abstract: In accordance with certain embodiments of the present disclosure, a process of forming a prosthetic device is provided. The process includes forming a dispersion of polymeric particles, a fiberizing polymer, and a solvent, the dispersion having a viscosity of at least about 50,000 cPs. A tubular frame is positioned over a tubular polymeric structure. Nanofibers from the dispersion are electrospun onto the tubular frame to form a prosthetic device. The prosthetic device is heated.

Abstract: A stack of 50 layers of a first pitch-base carbon fiber sheet is formed, two sets of stack each having two second pitch-base carbon fiber sheets stacked therein are fabricated. At this time, the second carbon fiber sheets have a thermal expansion coefficient larger than that of the first carbon fiber sheet. Next, the stack of the first carbon fiber sheet is then held between two sets of stack of the second carbon fiber sheets. The stack of the first and second carbon fiber sheets are then impregnated with an epoxy-base resin composition and the resin is solidified. As a result a prepreg composed of the first and second carbon fiber sheets and the resin component composed of the epoxy-base resin composition is obtained. Thereafter, interconnections and the like are then formed on the prepreg, to thereby complete a multilevel interconnection board.

Abstract: Machinable composite molds for use in molding composite structures. The mold includes a mold body having a tool surface that is shaped to provide the molded surface of the composite structure. The mold body is made up of at least one mold layer composed of a quasi-isotropic material composed of a plurality of randomly oriented fiber bundles or chips impregnated with a resin. The use of randomly oriented fiber chips allows post-cure machining of the mold body.

Abstract: In accordance with certain embodiments of the present disclosure, a process for forming a multilayered electrospun composite is provided. The process includes forming a dispersion of polymeric particles, a fiberizing polymer, and a solvent, the dispersion having a viscosity of at least about 50,000 cPs. Nanofibers from the dispersion are electrospun onto a first ePTFE layer. A second ePTFE layer is applied onto the nanofibers to form a composite structure. The composite structure is heated.

Abstract: According to the invention, one or more thermoplastic sheets (NdT: “feuilles thermoplastique” in the original) (2) are applied on a flat or curved tool (13), and strips (NdT: “des bande” in the original) of a polymer are applied and pressed onto the sheets (2). They are maintained by suction pumps (8), the orifices (4) of which open into a closed volume or one substantially delimited by a sealing joint (3) and occupied by a draining fabric (7). The heating treatment concomitant to the deposition to harden or consolidate the prepreg softens the sheets (2), distorts them to the curvature of the tool (13) and incorporates them in the structure of the prepreg. Application to methods of draping parts with composite material.

Abstract: Materials and methods are provided for producing preform materials for impact-resistant composite materials suitable for liquid molding. Interlayers formed of nonwoven, continuous fibers, such as spunbonded, spunlaced, or mesh fabric, are introduced between non-crimped layers of unidirectional reinforcing fibers to produce a preform for use in liquid-molding processes to produce a composite member. Curing of the preform provides increased impact resistance by increasing the amount of energy required to propagate localized fractures due to impact.

Abstract: A method of making a composite rotor yoke includes preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, preparing the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material.

Abstract: A machine and a method for forming composite materials are provided. The machine includes a frame and at least one forming beam attached to the frame, the at least one beam being arranged to align with a mandrel. The forming beam is pivotally segmented into at least two segments to conform to the shape of the mandrel, or alternately is bendable to conform to the shape of the mandrel. The mandrel is receivable within the frame in alignment with the forming beam. An apparatus is also provided to position a composite charge over the mandrel, and to position the mandrel within the frame. A further apparatus is provided to transport the mandrel, and to urge the mandrel toward the forming beam, forming a composite charge.

Abstract: A non-compliant fiber-reinforced medical balloon comprises a first fiber layer and a second fiber layer embedded in a continuous matrix of thermally-weldable polymer material defining a barrel wall, cone walls and neck walls. The fibers of the first fiber layer run substantially parallel to one another and substantially parallel to the longitudinal axis. The fibers of the first fiber layer have a pattern of different lengths and are divisible into a first group and a second group based on length. Each fiber of the first group begins in the neck wall at one end of the balloon, extends continuously in the longitudinal direction and terminates in the neck wall at the opposite end of the balloon. Substantially all of the fibers of the first group have a generally uniform length. Each fiber of the second group begins in the cone wall at one end of the balloon, extends continuously in the longitudinal direction and terminates in the cone wall at the opposite end of the balloon.

Abstract: The present invention relates to a method of manufacturing a laminate with the formation of underpressure between a mold (103) and a vacuum foil (105) and supply of resin from injection areas to the layers of the laminate situated in the mold. The novel aspect according to the invention comprises movement of the injection areas while the resin is supplied, This is accomplished by use of a movable suction unit (200) which is arranged on top of the vacuum foil and which, by means of an underpressure between the suction unit and the vacuum foil, forms injection areas for supply of the resin, which can be moved by moving the suction unit. The invention further relates to such movable suction unit and the use thereof in the manufacture of laminates.

Abstract: The method for making a continuous laminate, in particular suitable as a spar cap or another part of a wind energy turbine rotor blade comprises the steps of providing a plurality of parallel fibers, embedding the fibers in a curable matrix material, curing the matrix material so as to obtain a fiber reinforced laminate having upper and lower major surfaces, and forming channels into at least one of the upper and lower major surfaces of the laminate wherein the channels on the upper and/or lower major surfaces are angled with respect to the direction of the fibers.

Abstract: The present invention discloses a method of producing and application for a projectile resistant matrix that allows for manufacture of low weight projectile resistant armor trauma shields without metal or ceramic plates using projectile resistant textiles encapsulated in a composite matrix through use of injection molding process or spray-on technique as constituents of the projectile resistant trauma shield without metal or ceramic plates of the present invention.