Abstract: A mold core for producing a component of fiber composite material with a cavity makes a particularly simple and efficient demolding process possible by the mold core extending along a longitudinal axis and in the form of a hybrid core and which includes, viewed in a cross section perpendicular to the longitudinal axis, a first core portion and a second core portion, wherein the first core portion has a thickness that is substantially greater than a thickness of the second core portion. The first core portion is formed from a first material with high stiffness and low coefficient of thermal expansion, and the second core portion is formed from a second material that differs from the first material, and is configured such that, under predetermined conditions, its form changes in a predetermined manner such that removal of the mold core from a cavity in the cured component is made easier.

Abstract: A propeller includes a plurality of blades that extends outward in a radial direction of a rotation central axis relative to the rotation central axis, and includes an end that is located on an opposite side of the rotation central axis. Each of the plurality of blades has a maximum angle of elevation in a position ranging from 30% to 60% with the rotation central axis as a starting point of a radius of a circle that passes through the end of each of the plurality of blades with the rotation central axis as a center, the maximum angle of elevation being a maximum of an angle of elevation in each of the plurality of blades. A change in the angle of elevation in a longitudinal direction of each of the plurality of blades is within 10 degrees per 5% of the radius.

Abstract: The invention relates to a method for manufacturing a box-shaped monolithic structure with a cavity by curing a fiber-reinforced prepreg material. The method comprises using two or more elongated and internally hollow support tools which have a complementary form to that of the cavities to be manufactured, and a composition based on reinforcement material and polymer suitable to allow the passage from a rigid state to a flexible elastomeric state and vice versa in response to heating/cooling down. In the rigid state, the support tools allow the direct lamination of the prepreg material on their external walls and are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 50° C. During the curing operation, the curing pressure is applied both outside the structure being formed and inside the support tools, whose walls have become flexible, to push on the prepreg material to be cured.

Abstract: An additive manufacturing apparatus includes a first vertically-extending support leg, a second vertically-extending support leg, and a gantry supported on the first and second support legs. The additive manufacturing apparatus also includes a work table movably supported beneath the gantry, a print head supported on the gantry, and a trim head supported on the gantry with the print head.

Abstract: A system is disclosed for use in additively manufacturing a composite structure. The system may include at least one support, and a print head operatively connected to the at least one support and configured to discharge composite material. The system may further include an auxiliary tool operatively connected to the at least one support and configured to receive the composite material discharged by the print head.

Abstract: A method for employing a plurality of automated machines to deposit composite material includes a first tool located in a first station and a second tool located in a second station. The first station and the second station are located on a production line. The first station includes at least one automated machine of the plurality of automated machines and the second station includes at least two automated machines of the plurality of automated machines. At least one of the automated machines is movable from the second station to the first station. The method includes monitoring machine capacity and workload requirements of the plurality of automated machines. The method further includes determining an efficiency threshold based upon the machine capacity and workload requirements. The method further includes reallocating at least one of the automated machines from the second station to the first station once the efficiency threshold is met.

Abstract: A polar end ring mechanism for use with composite pressure vessels. The end ring is designed to support a pressure vessel during its formation via filament winding. The end ring helps define an opening at one of the polar ends of a tank. Spikes positioned along a portion of the end ring help prevent rotation or translation of the tank during formation and provide an improved mechanical lock with the tank body. A cap may then be secured to the polar end ring after formation in order to close the pressure vessel.

Abstract: A method for the manufacture of a fiber-composite article for a bicycle frame or other bicycle component uses an outer mold configured to define an outer surface of the fiber-composite article and an inner mold configured to define an inner surface of the fiber-composite article. The method comprises: securing in the inner mold a supportive armature for a space-filling mandrel, the mandrel being configured to occupy a space within the inner surface of the fiber-composite article during lay up and curing of the fiber-composite article; forming the mandrel by injection molding a solidifiable fluid into the inner mold, around the armature, the solidifiable fluid being configured to form a solidified, molded material; applying a fiber composition to the mandrel; securing the mandrel with the fiber composition in the outer mold; heating the fiber composition in the outer mold to form the fiber-composite article and concurrently heating the solidified, molded material.

Abstract: Methods and systems are disclosed for encasing various structures with a seamless continuous sleeve, where the presence of existing supports does not allow slipping a sleeve over the structure. In these methods strips of fabrics smeared with or saturated by resin are helically or non-helically wrapped or placed around desired shape mandrels that are located around a support of the structure. As the resin is partially cured, a portion of the sleeve segment is moved away from the mandrel, leaving the rest of the sleeve on the mandrel to be attached to the next will-be-fabricated sleeve segment. The process will continue as many times as needed to create a sleeve of a desired length. In various embodiments the strength of the sleeves varies at different locations. In some embodiments the gaps between the sleeves and the structures are filled with gas, liquid, solid, or any other materials.

Abstract: The present invention relates to a brush with fusion interlocking bristle strip and a method of manufacturing the same. The brush includes carrier strips and knotted bristle strips bonded together by ultrasonic welding and interlocking.

Abstract: There is described a hot-stamping press (10; 10?; 10??) comprising a foil application unit (2; 2*) designed to allow transfer or lamination of foil material (FM) by hot-stamping onto a substrate (S) supplied in the form of successive sheets or successive portions of a continuous web, which foil material (FM) is fed to the foil application unit (2; 2*) in the form of a foil carrier (FC) supplied by means of a foil feeding system (3). The hot-stamping press (10; 10?; 10??) further comprises at least one UV-curing unit (61; 62; 63) located along a path (A) of the substrate (S) downstream of the foil application unit (2; 2*) to subject the foil material (FM) transferred or laminated onto the substrate (S) to a UV-curing operation.

Abstract: The present invention discloses a shaft-tube joint structure of a carbon fiber reinforced plastic (CFRP) drive shaft. The shaft-tube joint structure includes a hollow shaft tube, a plurality of first rectangular teeth being uniformly and circumferentially arranged at both ends of the hollow shaft tube; two shaft-tube joints which are respectively fixed at two ends of the hollow shaft tube, the thickness of the shaft-tube joint being smaller than that of the hollow shaft tube, and an inner wall of the shaft-tube joint being smoothly connected to an inner wall of the hollow shaft tube; and a universal joint, an end thereof being tubular, a plurality of second rectangular teeth being uniformly and circumferentially arranged, the universal joint being matched with and sleeving the outer wall of the shaft-tube joint, and the second rectangular teeth being meshed with the first rectangular teeth.

Abstract: An example mandrel for processing a part is described including an inner core having a material with first thermal properties, and an outer layer surrounding the inner core. The outer layer includes a material with second thermal properties different than the first thermal properties to enable uniform pressure distribution within the mandrel. An example method for fabricating a composite part is described including placing a base composite layer into a cavity of a tooling surface, inserting a mandrel into the cavity, applying a skin to the mandrel and the base composite layer forming a package, enclosing the package in a vacuum bag and curing the base composite layer and the skin such that during curing a pressure due to thermal expansion of one of the inner core and the outer layer is distributed by the other, and removing the mandrel from the cavity of the tooling surface following the curing.

Abstract: A method for manufacturing a plastic fabric-film composite product includes forming an extruded-film web with at least one sealing layer by film extrusion in such a way that the sealing layer is located on a first side of the extruded-film web and then, feeding and laminating a plastic-fabric web made of film-strip fabric and the prefabricated extruded-film strip with one another to form a composite web. The composite web is formed in such a way that a second side of the extruded-film web faces a first side of the plastic-fabric web.

Abstract: In a method of producing symmetrical carbon fiber reinforced composite parts, a plurality of sheets of fibrous material configured as a single structure are positioned on a tool surface where the single structure is comprised of a first composite part joined to a symmetric, second composite part. The single structure is infused with resin and cured on the tool surface, producing a single cured structure comprised of a first cured composite part joined to a second cured composite part. The single cured structure is then divided along a dividing plane, producing the symmetric first cured composite part and second cured composite part.

Abstract: An additive manufacturing system is disclosed for use in fabricating a structure. The additive manufacturing system may include a support, and an outlet configured to discharge a material. The outlet may be operatively connected to and moveable by the support in a normal travel direction during material discharge. The outlet may include a guide, and a compactor operatively connected to the guide at a trailing location relative to the normal travel direction. The compactor may be moveable in an axial direction of the guide. The outlet may also include at least one cure enhancer mounted to move with the compactor relative to the guide. The at least one cure enhancer may be configured to expose the material to a cure energy.

Abstract: A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.

Abstract: A boss assembly for a pressure vessel includes a boss, a fitting, a first seal and a second seal. The boss includes a bore with an inner surface and a first stop feature. The fitting is configured for at least partial insertion into the boss to prevent fluid communication between an interior and an exterior of the pressure vessel, the fitting including an outer surface and a second stop feature. Each of the first and second seals is positioned along the outer surface. The fitting is movable between first and second positions. In the first position, the first seal is sealingly engaged between the inner and outer surfaces and the second seal is not sealingly engaged therebetween. In the second position, the first seal is not sealingly engaged between the inner and outer surfaces, the second seal is sealingly engaged, and the first and second stop features mutually contact.

Abstract: A catheter shaft is produced by forming a first polymeric layer onto a flexible inner core while maintaining the inner core in a solid state, and solidifying the first polymeric layer, wherein the solidified first polymeric layer fails to bond with the inner core and is slidable thereon upon flexion of the shaft. A second polymeric layer may be formed over the first polymeric layer, and is slidable thereon when the shaft bends.

Abstract: A system is disclosed for use in additively manufacturing a composite structure. The system may include at least one support, and a print head operatively connected to the at least one support and configured to discharge composite material. The system may further include an auxiliary tool operatively connected to the at least one support and configured to receive the composite material discharged by the print head.

Abstract: An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.

Abstract: A composite forming method includes manufacturing either one of a composite structure body and a dry preform having a hollow region, and pulling a core out of the hollow region. In the manufacturing, a rubber-made core having a tubular structure is disposed at a portion that forms the hollow region of either one of the composite structure body and the dry preform. The core has a thickness varied in a direction perpendicular to a longitudinal direction to be foldable inward at a thin portion. In the pulling, the core is folded inward with air being discharged from an inside of the core after either one of the composite structure body and the dry preform is manufactured.

Abstract: Systems and methods are provided for fabricating preforms for composite parts. One embodiment is a method of creating a preform. The method includes conveying a web of fiber reinforced composite material in a process direction, disposing fiber reinforced composite material atop the web, conveying the web and the tow in the process direction to a cutting tool, and cutting out a preform comprising a combination of the tow and the web.

Abstract: A method for fabricating a ceramic matrix composite component having a deltoid region is provided. The method includes providing a porous ceramic preform. The porous ceramic preform includes a layer-to-layer weave of ceramic fibers that forms a modified layer-to-layer woven core and at least one 2-dimensional layer of ceramic fibers that is disposed adjacent to the modified layer-to-layer woven core. The porous ceramic preform is formed into a ceramic matrix composite body having the deltoid region such that the modified layer-to-layer woven core extends through the deltoid region.

Abstract: A substantially air-tight triple seal arrangement along a seam between first and second tool segments comprises inner, middle and outer seals forming first and second substantially air tight vacuum chambers.

Abstract: Disclosed is a method for producing components from fiber-reinforced thermoplastic. The method involves manufacturing a multitude of semifinished products, each of which includes a plurality of impregnated fabric layers that are joined to one another only locally, as well as a frame structure having at least one cutout. The semifinished products are consolidated using a consolidation device, an inlay element being placed in each cutout before the semifinished products are consolidated.

Abstract: The invention relates to a device (1) for coating workpieces (2), preferably consisting of wood, wood-based materials, plastics material or the like at least in sections, comprising a feed device (10) for feeding a coating material (12), a pressing unit (20) for pressing the coating material (12) against a surface (2a) of a workpiece (2), a conveyor device (4) for bringing about a relative motion between the pressing device (20) and the respective workpiece (2), an energy source (30) for applying energy onto the coating material (12) and/or the workpiece (2), and a control device (50) for controlling at least the energy source (30).

Abstract: In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.

Abstract: An additive manufacturing method for fabricating a component having a surface substantially free of imperfections may include providing a mold having a configuration corresponding to the component, and depositing a material on at least one surface of the mold to fabricate the component having the surface substantially free of imperfections.

Abstract: A high-pressure pipe comprises an inner liner (1), an outer coating layer (6) and a reinforcement layer (2, 5) positioned between the inner liner and the outer coating layer. The reinforcement layer has helically wound strips (2, 5) which each comprise a matrix (4) and fibers (3) embedded in the matrix; the fibers consist of a multitude of twisted high-strength filaments. With an aim of providing a relatively high bending flexibility, the filaments of a fiber are sized filaments obtained by subjecting the filaments to a sizing operation.

Abstract: A fiber placement system including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a compaction nip region, and a laser heating assembly including a laser that emits a beam of electromagnetic radiation and a scan head defining a scan field, the scan field being aligned with the compaction nip region, wherein the scan head scans the beam within the scan field.

Abstract: Ply layups and methods for forming composite components are provided. For example, a method for forming a composite component comprises laying up a plurality of composite plies to form a composite ply layup; partially processing the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component. In an exemplary embodiment, the composite component is a turbine nozzle airfoil. Another exemplary method comprises laying up a plurality of composite plies to form a composite ply layup; compacting the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component.

Abstract: A system for fabrication of an aerospace structure incorporates a mold having a surface and at least one unidirectional SFL head adapted to lay down a plurality of collimated tows in a predetermined laminated pattern on the mold surface to produce a fuselage skin. At least one cross plied laminate SFL head is adapted to lay down a cross plied laminate base interface on the fuselage skin to establish a lattice rib shape for each of a plurality of lattice ribs. The cross plied laminate SFL head has a band placement head steerable to avoid structural design features and to maintain spacing from adjacent steered lattice ribs. The unidirectional SFL head is further adapted to lay down a plurality of collimated tows on the base interface of each of the plurality of lattice ribs for a first plurality of unidirectional tow plies in each lattice rib.

Abstract: A manufacturing method of a tank including a tubular body portion, and dome-shaped side end portions formed on both sides of the body portion, the manufacturing method includes forming a tubular compact serving as at least part of the body portion from one fiber reinforced resin sheet by winding the fiber reinforced resin sheet including reinforced fibers impregnated with thermoplastic resin is wound several times around a peripheral surface of a core from a direction perpendicular to an axial center of the core in a state where the thermoplastic resin is melted.

Abstract: Various automated fiber placement systems and methods are disclosed. The system can determine steerable paths for the application of a composite material over highly contoured surfaces. The system can determine when a course trajectory would violate a steering limitation (e.g., a maximum bendability of the composite material) and can adjust the trajectory to avoid such violations. The adjustment can create gaps between adjacent courses, which can have a generally flared peripheral shape. The system can fill such gaps with subsequent courses of the composite material. Thus, the system can automatically apply composite material to highly contoured surfaces while also avoiding violation of the steering limitations.

Abstract: Devices and methods are disclosed for depositing reinforcing fiber tapes and detecting laying errors. Automatic depositing of reinforcing fiber tapes on a support can occur by a laying head and at least one roller assigned to the laying head. At least one radiation source and/or at least one sensor is integrated into the at least one roller for the detection of laying errors, and this roller is transmissive at least by region for a radiation emitted by the radiation source.

Abstract: A laying unit for producing a fiber composite component is provided. The laying unit includes a housing and a plurality of fiber coils which are designed so as to be able to be unwound during a movement of the laying unit, wherein the fiber coils are provided in a movably mounted manner inside the housing.

Abstract: A hub for a bicycle wheel includes a hub shell that defines one or more spoke holes. The hub shell includes a fiber reinforced material. The fiber reinforced material has one or more reinforcement fibers bending around the spoke holes to remain continuous around the spoke holes. One or more flanges with the spoke holes extend from the hub shell at an outer radial direction. A clutch or freehub adapter is coupled to the hub shell. Depending on the type of clutch mechanism used in the freehub, different clutch adapters can be incorporated into the hub.

Abstract: A shoe having a bio foot pad, including a plurality of circumferential elastic fibers surrounded by a viscoelastic material; wherein said fibers impart a biphasic characteristic to said viscoelastic material; and wherein said fibers under compression develop a plurality of hoop stresses to facilitate load conversion and distribution of axial forces exerted against a heel area of a user.

Abstract: An apparatus (10) that houses functional components of a mechanical assembly includes a frame component (12) formed of a first material, the frame component (12) bearing primary load, torque or pressure applied to the apparatus (10) during operation of said mechanical assembly. The housing apparatus (10) further includes a composite reinforcement component (130) for resisting forces applied to the apparatus during operation of the mechanical assembly and an enclosure component (80) formed of a second material of lower density than the first material of the frame component (12), the enclosure component (80) covering and sealing at least the functional components of the mechanical assembly from external conditions during operation of the mechanical assembly.

Abstract: The present invention discloses a device for producing a reinforcing structure, which comprises a strip that is fiber-reinforced and comprises thermoplastic material, on the surface of a molding. The device is characterized in that it is designed such that the laser diode array directly irradiates the heating-up area of the strip and/or the heating-up area of the surface of the molding or of the already formed reinforcing structure, wherein the laser diodes of the laser diode array are formed as surface emitters.

Abstract: Watch bands with multiple light tubes, each light having a light fiber and at least one light-emitting diode for providing light to each light tube. The light-emitting diode may produce a wide color gamut for the light fiber to produce light in each light tube. Each light-emitting diode may produce a different color and light intensity different from the other light tubes in the watch band. The light tubes doubles as the structure for attaching a watch body to a user's wrist and as a carrier of light to add variety and style to the watch band. The watch band may have a variety of different attachment mechanisms for attaching and securing the watch body to the user's wrist.

Abstract: A method and apparatus for laying composite tape. The method may comprise driving a plurality of robots, each having a respective movement system across a movement surface, in which the movement surface faces a workpiece, and laying composite tape from the plurality of robots in a coordinated manner on the workpiece.

Abstract: In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes defined at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region around the holes comprises a first area obtained by bending composite material, which is reinforced using continuous fibers that have been made even in a longitudinal direction, so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction. A tensile rigidity and/or a compressive rigidity in the one direction of the peripheral region around the holes is lower than a tensile rigidity and/or a compressive rigidity in the one direction of other regions that surround the peripheral region.

Abstract: A method of hose construction comprises: providing a sacrificial layer on the surface of a hose former; constructing a hose on the sacrificial layer; forcing pressurized fluid between the sacrificial layer and the hose former to separate the hose former from the sacrificial layer; and separating the sacrificial layer from the hose.

Abstract: Various automated fiber placement systems and methods are disclosed. The system can determine steerable paths for the application of a composite material over highly contoured surfaces. The system can determine when a course trajectory would violate a steering limitation (e.g., a maximum bendability of the composite material) and can adjust the trajectory to avoid such violations. The adjustment can create gaps between adjacent courses, which can have a generally flared peripheral shape. The system can fill such gaps with subsequent courses of the composite material. Thus, the system can automatically apply composite material to highly contoured surfaces while also avoiding violation of the steering limitations.

Abstract: A component made of a fiber composite material contains at least three wound layers made of a fiber material that are arranged one over the other. Each of the wound layers contains one or more windings. For each wound layer containing more than one winding, all windings of the wound layer have the same winding angle and are separated from each other in some sections, whereby intermediate spaces are formed between the windings. All windings of at least two of the wound layers have the same first winding angle. All of the windings of one wound layer, which is arranged between the two wound layers having the windings with a same first winding angle, have a second winding angle. The magnitudes of the first and second winding angles differ, and the windings having the second winding angle intersect with the windings having the first winding angle.

Abstract: A tank port includes a reinforcing sheet, an inner member, and an outer member. The reinforcing sheet is attached around a through-hole on the outer peripheral surface of a cylinder. The inner member includes an inner fitting plate portion attached to the inner peripheral surface of the cylinder and an inner cylindrical portion inserted into the through-hole. The outer member includes an outer cylindrical portion attached to the outer peripheral surface of the inner cylindrical portion protruding from an opening and an outer fitting plate portion attached around the opening of the reinforcing sheet. The entire periphery of the through-hole of the cylinder is reinforced by being disposed between the inner fitting plate portion and the reinforcing sheet.

Abstract: A fiber placement system including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a compaction nip region, and a laser heating assembly including a laser that emits a beam of electromagnetic radiation and a scan head defining a scan field, the scan field being aligned with the compaction nip region, wherein the scan head scans the beam within the scan field.

Abstract: A belt, such as a round baler belt, includes a core region, and at least one peripheral region arranged transversely to a longitudinal direction of the belt, where the peripheral region has a protective element at least sectionally, and the belt is continuously closed in the longitudinal direction. In some cases, the protective element is arranged around the entire continuously closed circumference in the longitudinal direction. The protective element may be stretched more in the longitudinal direction than the core region. The protective element may be a metal element, and in some cases, is a steel wire. Further, the protective element may be configured in an interrupted manner in the longitudinal direction. In some cases, a plurality of protective elements are arranged in a manner overlapping one another sectionally in the longitudinal direction.