Class / Patent application number | Description | Number of patent applications / Date published |
264258000 | Joining a plurality of superposed fibrous or textile layers | 52 |
20080237923 | PROCESS FOR THE PRODUCTION OF A SHAPED ARTICLE - The invention relates to a process for the production of a shaped article comprising the compression of one or more fibre layers containing polyolefin fibres. The invention also relates to shaped articles obtainable with the process according to the invention and their use in anti-ballistic applications. In the process according to the invention the fibre layers contain 0.02 to 25 wt. % of a solvent for the polyolefin. The shaped articles obtained have an improved anti-ballistic quality. | 10-02-2008 |
20090026655 | FORMING METHOD FOR FIBER REINFORCED RESIN - A forming method for fiber reinforced resin includes the following steps. First, put a stack of pre-pregs into a cavity of a die having a plurality of openings in communication with the cavity and the space outside the die. Then heat the die and exhaust air through the openings from the cavity of the die. Thus, the air bubbles between the pre-pregs as well as surplus resin can be drawn out such that the product has improved mechanical strength. | 01-29-2009 |
20090051076 | Method and Apparatus for Providing polymer to be Used at Vacuum Infusion - The invention relates to a method of producing a shell member of fibre composite material by means of vacuum infusion, where the fibre material is impregnated with liquid polymer, and applying a mould ( | 02-26-2009 |
20090057947 | Method and Apparatus for Fabricating Articles having Textured Surfaces - Decorative textured surfaces are formed on articles having curved or contoured surfaces. A reusable, flexible textured blanket is placed in a mold along with a first material charge. A pressurizer is used to both impart the texture of the blanket to the first material charge and consolidate the charge to form a textured shell. The blanket is removed from the mold and a second material charge is introduced into the mold over the shell. The application of heat and pressure consolidates the second material charge and the shell to both form and cure the completed article. | 03-05-2009 |
20090057948 | Method and apparatus for manufacturing a curved elongated structural element - A method and an apparatus for manufacturing of a curved elongated structural element of composite material. The curved elongated structural element includes a first elongated portion and a second elongated portion in an angled relation. A substantially flat blank of composite material including a first and second elongated edge is provided. The blank is folded over a first portion forming surface and a second portion forming surface of a forming tool's flexible tool body for forming the first elongated portion and the second elongated portion. The forming tool's tool body is bent such that its bending moment center prevails essentially adjacent the first portion forming surface. | 03-05-2009 |
20090065975 | MANUFACTURING PROCESS FOR HIGH PERFORMANCE LIGNOCELLULOSIC FIBRE COMPOSITE MATERIALS - The present invention relates to a process for the manufacture of composite materials having lignocellulosic fibres dispersed in a thermoplastic matrix, while generally maintaining an average fibre length not below 0.2 mm. The process comprises defibrillation of the lignocellulosic fibres using a mixer and at a temperature less than the decomposition temperature of the fibres in order to separate the fibres and generate microfibres, crofÊbres, followed by dispersion of the fibres in the thermoplastic matrix by mechanical mixing to get the moldable thermoplastic composition, followed by injection, compression, extrusion or compression injection molding of said composition. The process produces high performance composite materials having a tensile strength not less than about 55 MPa, a flexural strength not less than about 80 MPa, a stiffness not less than about 2 GPa, notched impact strength not less than about 20 J/m, and un-notched impact strength not less than about 100 J/m. The composite materials of the present invention are well-suited for use in automotive, aerospace, electronic, furniture, sports articles, upholstery and other structural applications. | 03-12-2009 |
20090072439 | Self-Tooling Composite Structure - Composite structures with internal cavities are constructed with relatively stiff walls that can support additional composite laminate layers, creating a self-tooling structure. The structure is subsequently simulcured, preferably in combination with elevated temperatures or pressures. Preferred structures are long and slender, and are constructed with one or more internal cells. Rotor blades are especially suited to the preferred construction methods. The walls can be advantageously constructed using composite sandwich panels, having an exterior laminate layer. In preferred embodiments, additional composite layers can be added before or after the simulcuring process. | 03-19-2009 |
20090102092 | METHOD FOR MANUFACTURING BEAMS OF FIBER-REINFORCED COMPOSITE MATERIAL - 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. | 04-23-2009 |
20090108494 | CUSHION BODY, SEAT, AND METHOD OF MANUFACTURING THE SAME - A cushion body, which can secure both soft touch feeling and durability, a seat having the same, and a manufacturing method thereof are provided. | 04-30-2009 |
20090194906 | Process of draping a non-crimp fabric over a forming tool - A method of producing a non-crimp fabric and a non-crimp fabric comprising a layup of fabric plies stitched together by a thread, at least part of which is fusible, is provided. The method can include heating the stitched plies to soften or melt the fusible thread. The use of fusible thread can act as an in situ binder within the non-crimp fabric and tension created by the unfused stitching may create channels for matrix resin infusion during manufacture. | 08-06-2009 |
20090309260 | Method of delivering a thermoplastic and/or crosslinking resin to a composite laminate structure - The present invention provides a process for producing a prepreg of high modulus reinforcing fibers, the process comprising the steps of: a) providing a reinforcing fiber bundle layer wherein such bundle contains a thermoplastic and/or crosslinking resin within the fiber bundle; b) providing a layer of a thermoplastic and/or crosslinking material layer on at least one side of the high modulus fiber layer of step a); c) compressing the layers from step b) under an appropriate amount of heat and pressure, and thereby producing a prepreg of high modulus reinforcing fibers. | 12-17-2009 |
20100283180 | APPARATUS FOR THE INFUSION OF RESIN INTO A PREFORM IN A CLOSED MOULD - 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. | 11-11-2010 |
20100295210 | METHOD OF PRODUCING A STRUCTURAL PART MADE FROM A THERMOSETTING RESIN BY DRAWING - 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:
| 11-25-2010 |
20100320642 | APPARATUS AND METHOD FOR TAKING UP, POSITIONING AND DRAPING DRY TEXTILE FIBER SEMI-FINISHED PRODUCTS - The invention relates to an apparatus ( | 12-23-2010 |
20110037199 | RESIN CONTAINMENT AND INJECTION SYSTEM AND METHOD - 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. | 02-17-2011 |
20110062626 | FELT BODY MANUFACTURING METHOD - 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. | 03-17-2011 |
20110115124 | Method For Manufacturing A FRC/FRP- Component From Rovings With A Moulding Tool And Moulding Tool For Implementing The Method - 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. | 05-19-2011 |
20110121487 | METHOD OF MANUFACTURING A COMPOSITE ELEMENT - 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. | 05-26-2011 |
20110210476 | Composite Laminate Having An Improved Cosmetic Surface And Method Of Making Same - 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. | 09-01-2011 |
20110215502 | CERAMIC COMPOSITE WITH INTEGRATED COMPLIANCE/WEAR LAYER - 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. | 09-08-2011 |
20110241250 | MANUFACTURING METHOD AND MANUFACTURING APPARATUS OF FIBER REINFORCED COMPOSITE MATERIAL - A manufacturing method and a manufacturing apparatus of a fiber reinforced composite material are provided, in which the whole fiber-based material is impregnated with a resin and a molding can be performed with high dimensional accuracy. A manufacturing method of a fiber reinforced composite material according to the present invention includes fixing a fiber-based material having a first surface to a first mold to provide an opening for the first surface; setting a second mold having a second surface such that the first surface faces the second surface through a space; filling resin into the space; and relatively moving the second mold and the first mold to bring the second surface closer to the first surface, such that the fiber-based material is impregnated with the resin. | 10-06-2011 |
20110298152 | Thermoplastic Fiber Material Spun from a Raw Material Containing Polyhydroxyether, Methods for Its Production and Uses for It - The invention describes a new synthetic fiber material of polyhydroxyether, as well as a melt-spinning method for its production. The new material can be used, in particular, for stabilization of the reinforcement fibers of high-performance fiber composite materials before they are embedded in the matrix material. During this usage, the polyhydroxyether fiber material dissolves at a temperature above its glass transition temperature entirely in the matrix material, so that the reinforcement fibers can be arranged largely free of kinking. In addition, it forms cross-links with the matrix material to form a homogeneous matrix and thus does not constitute a disruptive third phase in the composite material. The compatibility of the matrix and reinforcement fiber is also improved. It was possible to improve the bending strength of test slabs by 12% as compared to that of reference slabs with polyester filament. | 12-08-2011 |
20120091627 | METHOD FOR MANUFACTURING A WIND TURBINE ROTOR BLADE - A method for forming a profile for a hollow component is provided. A first composite fibre layer is laid out on a first surface corresponding to a first profile section of the component. A second composite fibre layer is laid out in a second surface corresponding to a second profile section of the component. A collapsed bag is laid out in onto the first composite fibre layer. The bag and the first composite fibre layer are fixed to the first surface. First and second mould elements are coupled such that the first surface and the second surface correspond to the first and second profiles. The bag is inflated such that the first composite fibre layer is pressed to the first surface and the second composite fibre layer is pressed to the second surface so that the first and second layers are coupled to form the profile. | 04-19-2012 |
20120299216 | Vacuum Infusion Adhesive and Methods Related Thereto - An adhesive adapted to enable spray delivery and seamless polymerization during epoxy resin vacuum infusion techniques. | 11-29-2012 |
20130181374 | MOLDING TOOL AND METHOD FOR MANUFACTURING A FIBER REINFORCED PLASTIC AERODYNAMIC AIRCRAFT COMPONENT - A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component, which aircraft component, in order to form several bays arranged on the inside and delimited by an outer skin and spars arranged spaced apart from each other, in each case includes a multi-part mold core that matches the shape of the respective bay, wherein to conform to local skin reinforcements and/or spar reinforcements that extend into at least one of the bays, the multi-part mold core includes four or five core parts, of which two core parts comprising a triangular cross section are arranged along opposing edges of the bay, which edges interact with two or three core parts that fill the space between the two triangular core parts, which space extends diagonally relative to the bay. | 07-18-2013 |
20130221568 | METHOD AND APPARATUS FOR MANUFACTURING FIBER-REINFORCED BASE MATERIAL - It is intended to provide a method and an apparatus for manufacturing a fiber-reinforced base material, which is capable of manufacturing a fiber-reinforced base material of high quality while preventing generation of defects such as wrinkles during stacking of the base material sheet. The method for manufacturing the fiber-reinforced base material formed by stacking a base material sheet including a reinforcement fiber onto a mold having a double-curved surface shape, includes steps of: supplying the base material sheet onto the mold from a base material roll while applying distribution varying in a width direction (X direction) to a length of the base material sheet in a sheet-supplying direction of the base material sheet (Y direction) in correspondence with the double-curved surface shape of the mold; and applying pressure to the base material sheet in contact with the mold. | 08-29-2013 |
20130328237 | METHOD FOR MANUFACTURING PREFORM - A method of manufacturing a preform includes forming a sheet-shaped structure made of a reinforcing-fiber base material with reinforcing fibers arranged in a predetermined direction into a shape along a lower mold having a three-dimensional shape with a recessed section by using the lower mold and a plurality of upper molds each having a pressing mechanism, wherein the sheet-shaped structure is placed on the lower mold while at least one spot in the sheet-shaped structure is temporarily pressed with at least one of the upper molds, and at least one spot other than the temporarily pressed spot in the sheet-shaped structure is pressed with another upper mold and, then, a spot which is neither the temporarily pressed spot nor the pressed spot is pressed with yet another upper mold, and the spot which has been temporarily pressed with the upper mold is pressed by a predetermined pressing force. | 12-12-2013 |
20130334735 | WIND TURBINE BLADE TUBULAR SPAR FABRICATING METHOD - A method of fabricating a wind turbine blade tubular spar, wherein the tubular spar extends along a designated axis, is made of reinforced polymer material having fibers arranged in at least two directions, and a polymer matrix incorporating the fibers, and has two caps and two webs; the method including the steps of: molding and cross-linking at least part of a cap or web in composite material; molding and cross-linking an L-shaped structure, which has two opposite parallel flanges, and at least partly incorporates the previously molded, cross-linked cap or web of composite material; repeating the above steps to mold and cross-link a further L-shaped structure; and joining the two cross-linked, L-shaped structures, with the flanges positioned facing in pairs. | 12-19-2013 |
20140035195 | DEVICE AND METHOD FOR PRODUCING FIBER PREFORMS - A device for producing fiber preforms includes a plurality of unwind stations, a plurality of grippers and at least one first molding tool. Each gripper is movable on a path between a maximum position and a pick-up position. The pick-up position is provided at a thread transfer point and is closer to the unwind station than the maximum position. The first molding tool has a draping position in the region of the connecting lines between the maximum position and the thread transfer points, and a starting position outside the connecting lines. A thread tension control for the threads or rovings is provided. | 02-06-2014 |
20140077413 | AIRFOIL MANUFACTURING SYSTEM - An apparatus and method for shaping an airfoil. A prepreg assembly is positioned relative to a part in a plurality of parts for a tool for the airfoil using a positioning section for a frame. The positioning section is configured to move relative to the tool and a base of the frame and move a number of parts in the plurality of parts for the tool relative to each other. A number of sections in the prepreg assembly are heated. A force is applied to the number of sections in the prepreg assembly that have been heated to conform to the tool to cause the number of sections in the prepreg assembly that have been heated to conform to the tool with a shape for a component of the airfoil. | 03-20-2014 |
20140124977 | COMPOSITE STRUCTURAL ELEMENTS AND METHOD OF MAKING SAME - A composite structural element and a method for making same are provided. The element includes a polymer foam core and at least one fibrous layer adhered to the polymer foam core by epoxy. Nano-particles are suspended in the epoxy prior to curing; preferably they are mixed with the hardener before it is mixed with the resin. The polymer foam core is preferably an exothermic foam such as polyurethane, and heat generated by the exothermic foam cures the epoxy, thereby causing the fibrous layer to adhere to the foam core. The nano-particles may be made from at least one of carbon, a ceramic, tungsten, a carbide, titanium, zircon, aluminum, silver, or boron. When carbon nano-particles are used, the strength of the composite is greatly increased, and the curing time of the heat-curable epoxy is significantly reduced. Ceramic nano-particles can be used to increase penetration resistance and provide increased ballistic protection. | 05-08-2014 |
20140138873 | Method for Manufacturing a Reinforced Panel of Composite Material - A method for manufacturing rigid panels made of a composite material requires a caul sheet having a smooth surface that is formed with a plurality of grooves. A first layer of the composite material is laid on the caul sheet, and is cut to create flaps that extend into the respective grooves. Strips of composite material are then placed along the edges of the groove to extend and overlap each other in the groove. Next, a unidirectional ply is placed along the length of the groove, and this combination is then covered with a second layer of the composite material. Together, the combination of the first and second layers, the strips and the unidirectional ply are co-cured to create a rigid panel with integral stiffening members. | 05-22-2014 |
20140151925 | METHOD FOR PRODUCING A CLOSED-SECTION PORTION OF AN AIRCRAFT PROVIDED WITH DEFORMATION SENSORS - A method for producing a closed-section portion of an aircraft wherein a strain gauge is glued on a first face of a flat tape that, in turn, is fastened on a face of a tool comprising a rigid elongated body covered by an extensible sack. The tool supporting the tape is arranged in a cavity of an aircraft structure. A vacuum is then created to obtain the expansion of the vacuum sack and perform the pressure gluing of the tape onto a wall of said cavity. The tool is subsequently extracted from the cavity. Upon conclusion of these operations, the tape is integrally fastened onto a wall of the cavity so that any deformation applied to this wall is transmitted to said strain gauge. | 06-05-2014 |
20140183784 | FABRICATION OF REINFORCED THERMOPLASTIC COMPOSITE PARTS - A method of fabricating a reinforced thermoplastic composite part comprises moving a laminate of reinforcing fibers embedded in a thermoplastic matrix for sequential operations through a heating station and then a forming station. The heating station is used to soften the thermoplastic matrix in a portion of the laminate while the forming station is used to impart a geometry to a portion of the laminate whose thermoplastic matrix had just been softened. The softening and the forming are performed simultaneously on different portions of the laminate. | 07-03-2014 |
20140183785 | PROCESS FOR MANUFACTURING A COMPOSITE, GENERALLY TRIANGULAR, STRUCTURAL PART - A method of fabricating an element ( | 07-03-2014 |
20140197569 | METHOD OF FABRICATING A HOLE IN A COMPOSITE PANEL - A method of forming a hole in a composite panel includes positioning a first fiber sheet on a layup table, where the layup table has a forming tool extending outward from a portion of the table, and the fiber sheet includes a plurality of fibers oriented along a first common direction. The method further includes extending the forming tool through the first fiber sheet such that a subset of the plurality of fibers are displaced about the forming tool: applying a resin to the sheet of fibers; pre-curing the resin to form a pre-preg part defining a hole about the forming tool; and removing the pre-preg part from the layup table. | 07-17-2014 |
20140246807 | Method for Forming a Melt-Resistant Glass Fiber Product, and Associated Apparatus - A method is provided for forming a melt-resistant glass fiber product, by applying an insulating material to a glass fiber product comprised of filiform glass fibers so as to substantially coat each of the filiform glass fibers therewith, such that the coated filiform glass fibers render the glass fiber product resistant to heat. In one aspect, such a method comprises forming a wetted mixture including filiform glass fibers and insulating material comprising a fire-retarding solution, wherein the wetted mixture has a solids content of the fire-retarding solution substantially uniformly and thoroughly dispersed therethrough. An associated apparatus is also provided. | 09-04-2014 |
20140265020 | Methods For Three-Dimensional Weaving Of Composite Preforms And Products With Varying Cross-Sectional Topology - Methods creating composite preforms with a three-dimensional weaving pattern include stacking material layers and then connecting them with interlayer reinforcements. First and second layers are aligned and separated by a first layer spacing. First interlayer reinforcements are then inserted through at least the first and the second layers. At least a third layer is aligned with at least the first and second layers. Second interlayer reinforcements are inserted through at least the second and third layers, using the first layer spacing between the first and second layers to manipulated the second interlayer reinforcements during insertion. Following the insertion of at least the second interlayer reinforcement, this layer spacing is closed to bring the first and second layers into contact. Further layers and interlayer reinforcements may be added, using additional layer spacings to manipulate additional interlayer reinforcements to form complex three-dimensionally woven composite preforms. | 09-18-2014 |
20140284843 | PROCESS FOR PRODUCING A REINFORCED PLASTIC ARTICLE - Plastics articles with continuous reinforcement strands are normally produced by pultrusion. Pultrusion methods are known for producing straight or curved plastics profiles. It has not hitherto been possible for reinforced plastics articles of more complex form to be produced by pultrusion methods. The invention provides a pultrusion method in which a part of a curved plastics article serves, together with a mold ( | 09-25-2014 |
20140327178 | METHOD AND APPARATUS FOR MANUFACTURING A WIND TURBINE BLADE COMPONENT WITH UNIFORM TEMPERATURE CURING - A molding apparatus for manufacturing a wind turbine blade component includes a main mold body ( | 11-06-2014 |
20150014883 | METHOD OF MANUFACTURING FIBER-REINFORCED RESIN - A method of manufacturing a fiber-reinforced resin in which resin is injected into a reinforcing-fiber substrate placed in a molding die from an injection port opened in a direction facing a surface of the reinforcing-fiber substrate, and the resin is then impregnated into the reinforcing-fiber substrate includes forming a space for injected-resin transit passage in the reinforcing-fiber substrate in the molding die by at least partially removing in advance a section of the reinforcing-fiber substrate located directly below the injection port in a thickness direction of the reinforcing-fiber substrate, and impregnating the resin injected from the injection port into the reinforcing-fiber substrate through the space for injected-resin transit passage. | 01-15-2015 |
20150021818 | Hockey Blade with Wrapped, Stitched Core - 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. | 01-22-2015 |
20150028520 | METHOD FOR MAKING A FEMALE MEMBER OF A HOOK-AND-LOOP FASTENER - A method for making a female member of a hook-and-loop fastener includes the steps of: (a) bonding together a base layer and a surface layer, that is formed from a fiber material and that is superimposed on the base layer, by applying heat to the surface layer so that fibers of the surface layer are curled; and (b) immediately after step (a), subjecting the surface layer to a rapid cooling treatment so as to set the curled fibers of the surface layer. | 01-29-2015 |
20150130109 | METHOD AND DEVICE FOR PRODUCING A TEXTILE PREFORM - A method for producing a textile preform includes manufacturing a multi-layer fiber fabric, which includes a first flange portion and a web portion connected to the first flange portion, deforming a first fiber layer of the first flange portion with respect to the web portion, such that the first fiber layer is at a first flange portion angle to the web portion, a web height of the web portion being set in a variable manner during the deformation of the first fiber layer, and depositing a unidirectional fiber fabric only on the deformed first fiber layer of the first flange portion. | 05-14-2015 |
20150343711 | COMPOSITE STRUCTURE REINFORCEMENT UTILIZING THERMAL PROPERTIES OF FORMING ELEMENTS - Forming systems and assemblies as disclosed herein comprise a composite material comprising a structural component and a resin component combined with the reinforcing component. A forming element is disposed within the composite material and has a coefficient of thermal expansion that is greater than that of the composite material. The forming element is positioned to provide a desired integral structural reinforcement and/or surface feature to the composite. The composite material may comprise one or more passages extending from a surface thereof to the forming element. The composite material may be cured by heat to take a set configuration and then allowed to cool. The cooling of the composite material and the forming element enables the forming element to contract relative to the composite material and become delaminated therefrom to facilitate easy removal, and thereby provide an improved method and assembly for making structural reinforcing features in composite structures. | 12-03-2015 |
20160089841 | Composite Part Forming System - A system and method for forming a composite part. The method comprises positioning a prepreg material relative to a composite forming tool. The composite forming tool comprises a frame associated with a shaping system, a base comprising at least one mold, and the shaping system associated with the frame and configured to move relative to the frame, the base, and the prepreg material. The method also lowers the shaping system of the composite forming tool towards the prepreg material. The method applies pressure to the prepreg material with a centerline presser of the shaping system. The method also applies a force to the prepreg material using a number of compliant elongate members of the shaping system to uniformly apply the prepreg material to the at least one mold of the base of the composite forming tool. | 03-31-2016 |
20160107348 | METHOD FOR PRODUCING A HYBRID COMPOSITE COMPONENT FROM ORGANO SHEETS AND A METALLIC REINFORCING ELEMENT - A method for producing a hybrid composite component from organo sheets and a metallic reinforcing element in such a way that the method may be inexpensively and simply performed and the hybrid composite component has the lowest possible weight and may absorb relatively high forces. | 04-21-2016 |
20160121553 | APPARATUS FOR AND METHOD OF COMPACTION OF A PREPREG - A forming apparatus and method of using the apparatus with a concave mandrel to form composite materials is presented where the apparatus has a forming head with an outer surface having a contour that matches the interior surface of the concave cavity of a matching mandrel. A handle and a grip surface to allow an operator to use the forming apparatus to exert a compaction force to successive plies of prepreg to conform the laminate of plies to the interior surface of the concave cavity. Each ply is heated before contact with the forming head of the apparatus. | 05-05-2016 |
20160176123 | Manufacturing System for Composite Structures | 06-23-2016 |
20160250812 | AUTOMATED LAMINATE COMPOSITE SOLID PLY GENERATION | 09-01-2016 |
20170232688 | Incorporation Of Jamming Technologies In Tooling For Composites Processing | 08-17-2017 |
20190143611 | Laminated Moulded Parts and Manufacture Thereof | 05-16-2019 |