Abstract: Disclosed herein a method for making a unidirectional continuous fiber-reinforced resin composite material. A resin plasticized and molten by an extruder is transported to a coating guide roller through a die head, and a hot-melt resin film layer with uniform thickness is formed on a roller surface of the coating guide roller. Simultaneously, the coating guide roller guides the hot-melt resin to continuously and uniformly coat on a row of flattened unidirectional continuous fibers along the roller surface of the coating guide roller. Subsequently, the coated flattened unidirectional continuous fibers pass through an open dip-coating roller device to effectively combine with the hot-melt resin to obtain a composite material of the hot-melt resin and fibers, which passes through a cooling and forming device to a winder under a driving force of a main traction to obtain the unidirectional continuous fiber-reinforced resin composite material.

Abstract: A method for producing a foam-molded product uses a producing apparatus including a plasticizing cylinder. The plasticizing cylinder has a plasticization zone, a starvation zone, and an introducing port which is formed in the plasticizing cylinder and via which a physical foaming agent is introduced into the starvation zone. The method includes: plasticizing and melting a thermoplastic resin into a molten resin in the plasticization zone; introducing a pressurized fluid containing the physical foaming agent having a fixed pressure into the starvation zone; allowing the molten resin to be in the starved state in the starvation zone; bringing the molten resin in the starved state into contact with the pressurized fluid having the fixed pressure in the starvation zone; and molding the molten resin into the foam-molded product. At least one pressure boosting part is provided in the starvation zone.

Abstract: A method for forming a multi-layered structure includes forming a resin-infused fibrous material (70) by applying a liquid resin component (60) onto the fibrous material (32) being pulled through an injection box (110) such that the fibrous material is partially impregnated and surrounded by the liquid resin component to form a resin-infused fibrous material. The resin-infused fibrous material is then introduced to a first die (130) and partially cured to form a partially-cured fiber-reinforced core material (80). The core material exits the first die to an intermediate region, where a polymer layer (40) is then applied onto at least a portion of the outer profile surface of the core material. The material then enters a second die (140), where the liquid resin component is fully cured to form a fiber-reinforced thermoset core material (30) having the polymer layer adhered thereon within the second die, thus forming the multi-layered structure (20).

Abstract: A manufacturing method of an abradable coating consisting of depositing, on a substrate surface a filament of a thermosetting material while providing both a relative displacement between the substrate and the filament along a predetermined deposition path and solidification of the filament in order to create a three-dimensional scaffold of filaments, consisting of superimposed layers of which the filaments of a given layer are not contiguous and can be oriented differently from those of an adjacent layer, so as to confer upon it acoustic wave absorption properties, the thermosetting material being a thixotropic mixture free of solvent and consisting of a polymer base and a cross-linking agent in a weight ratio of a polymer base to a cross-linking agent comprised between 1:1 and 2:1, and of a flowing component, typically a petroleum jelly present between 5 and 15% by weight of the total weight of the thixotropic mixture.

Abstract: A method of manufacturing a wind turbine blade body, the method comprising the steps of: providing a mould (40) having a mould surface (43) for forming a first blade body having a first length, the mould having a mould root end and a mould tip end (42); placing a removable insert (50) on the mould surface towards the mould tip end to form a modified mould surface for forming a second blade body having a second length which is less than the first length; and forming the second blade body on the modified mould surface.

Abstract: A method for producing an object from a filamentary building material in an additive fused deposition modelling process, comprising the steps of: providing the building material; transporting the building material into a printhead at a feed rate for the building material, wherein the building material is transported between a driven drive wheel and a second wheel; melting the building material by means of a heating device in the printhead; discharging the molten building material to a discharge location, corresponding to a selected cross section of the object to be produced, at a discharge rate through an orifice of the printhead, with relative movement of the printhead in relation to the discharge location at a predetermined speed to movement along a predetermined path, wherein the path has at each location a curvature that can assume a positive value, zero or a negative value; wherein a control unit controls at least the drive of the drive wheel, the heating device in the printhead and the movement of the p

Abstract: A rotary compression-molding machine includes an upper punch-retaining portion disposed above a table including die bores and retaining an upper punch, a dust-proofing device including a sealing case including a bottom wall that includes an insertion bore penetrated by the upper punch and faces a downward surface of the upper punch-retaining portion, and an outer wall facing an outer surface of the upper punch-retaining portion, and supported by the upper punch-retaining portion, and an expandable dust cover attached to be in contact with a downward surface of the bottom wall of the sealing case and covering a circumferential edge of the insertion bore and an outer circumference of the upper punch, and air passages disposed between the outer wall of the sealing case and the outer surface of the upper punch-retaining portion.

Abstract: A tread pattern of a pneumatic tire includes an inner circumferential main groove and an outer circumferential main groove that have groove walls extending in a tire circumferential direction while the angle of the groove walls relative to a contact surface varies with a predetermined amplitude, an inner lug groove extending from the inner circumferential main groove toward the outer circumferential main groove, an outer lug groove extending from the outer circumferential main groove toward the inner circumferential main groove, and a sipe configured to communicate the inner lug groove with the outer lug groove. A pair of chamfered surfaces are provided on walls of the sipe along an extension direction of the sipe on the contact surface.

Abstract: A three-dimensional object shaping method includes the steps of a powder layer forming step, a sliding step of a squeegee on the supplied powder, and a sintering step of irradiating the powder layer, all successively repeated, wherein after dividing shaping regions into a plurality of laminating units, each laminating unit of the plurality of laminating units is divided into an inside region including a maximum prearranged sintering region, and an outside region not including the maximum prearranged sintering region, and wherein the squeegee sliding speed in the outside region is set to be greater than the sliding speed in the inside region.

Abstract: Described is a method of manufacture of 3D objects from composite materials. The method includes the use of an extrusion nozzle configured to extrude the composite material, including a multistrand filament with a thixotropic acrylic matrix material surrounding the multistrand filament. Extruding a 3D object surface segment spanning in the air over at least a segment of a discontinuous work surface and operating concurrently a source of curing energy to pin and enhance the strength of a 3D object surface segment spanning in air. The 3D object extruded surface segment spanning in the air is sufficiently rigid and maintains its shape without the use of a mandrel.

Abstract: A method for manufacturing a centre wing box which includes inner stiffeners, at least one of which has at least one through-hole is described. For each stiffener having at least one through-hole and having a first leg of a first U-shaped and C-shaped profile and a second leg of a second U-shaped and C-shaped profile, the method includes, for each through-hole, the steps of producing a first section of the through-hole in the first U-shaped or C-shaped profile and of producing a second section of the through-hole in the second U-shaped or C-shaped profile before the first and second U-shaped or C-shaped profiles are positioned on the mould.

Abstract: A method of manufacturing a cold box core includes injecting unbonded sand into a cold box core tool, the unbonded sand including sand mixed with a resin, the cold box core tool including: a first platen; a first insert half secured to the first platen; a second platen; and a second insert half secured to the second platen and configured to alternately mate with and separate from the first insert half, each of the first insert half and the second insert half being three-dimensionally printed from a polymer material, the first insert half and the second insert half together forming a cavity therebetween defining an outer geometric shape of the cold box core; and injecting gas into the unbonded sand to harden the cold box core.

Abstract: A method for manufacturing an enclosure for a utility meter is provided, wherein at least two of a main cover part, an exterior terminal cover part, and an interior terminal cover part are at least partly formed jointly as a cover assembly in an injection moulding device. Further provided is a utility meter with an enclosure manufactured by the method.

Abstract: A process is provided for forming a pre-consolidated fiber preform for use in a molding process. The process includes layering a plurality of preform sheets on a pre-consolidation mold. Heating the plurality of preform sheets to a first temperature. Applying a first pressure to the plurality of preform sheets using the pre-consolidated mold. Maintaining the first temperature and the first pressure and heating for a first duration of time. A second pressure and a second temperature are then applied to the plurality of preform sheets for a second duration of time.

Abstract: Methods for fabricating Class-A components (CAC) include providing a molding precursor which includes a first and second skin layer each including a fiber reinforcing material embedded in a polymer matrix, a third layer between the first and second skin layers and including a third polymer matrix and a filler material interspersed therein. The fiber reinforcing materials include a plurality of substantially aligned carbon fibers having a plurality of low strength regions staggered with respect to the second axis. The method includes disposing a molding precursor within a die, compression molding the molding precursor in the die, wherein the die includes a punch configured to contact the second skin layer, opening the die to create a gap between the punch and an outer surface of the second skin layer, and injecting a Class-A finish coat precursor into the gap to create a class-A surface layer and form the CAC.

Abstract: Disclosed is a method, a mould system and a mould part for a mould system, for manufacture of a component for a wind turbine blade. The mould part may have a moulding surface with a primary side section, a secondary side section, and a central portion between the primary side section and the secondary side section. The mould part has a primary connection interface configured to abut a secondary connection interface of a second mould part. The primary connection interface comprises a primary connection surface substantially perpendicular to the moulding surface. The primary connection interface comprising an outlet configured to be connected to a vacuum source.

Abstract: A method of constructing a catheter assembly having an integrated septum. The method comprising molding a catheter hub having a distal end, a proximal end, and an internal wall defining an internal fluid passageway therebetween, the internal fluid wall defining an injection mold window located between the distal end and the proximal end; seating a catheter tube within the internal fluid passageway of the catheter hub, such that a proximal end of the catheter tube resides within the internal fluid passageway of the catheter hub, and a distal end of the catheter tube extends distally from the distal end of the catheter hub; plugging at least a proximal end of the catheter hub with a mold core shut off pin; and injection molding a septum in at least a portion of the internal fluid passageway between the mold core shut off pin and the proximal end of the catheter tube through the injection mold window.

Abstract: The invention relates to a method of manufacturing at least one tank with a shell, in particular a turbojet engine oil tank. The method comprises the following stages: (a) definition of different shell sections (58) for each tank, whereof a first shell section (58) has a recess (60) and a second shell section (58) a boss (62); (b) production of the shell sections (58) by additive manufacturing in which the boss (62) on the second shell section is produced in the recess (60) in the first shell section; then (c) welding of the sections (60) one to the other.

Abstract: A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

Abstract: Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.