Abstract: Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

Abstract: A method of connecting together two unit elements (4, 4?) of a fluid transport pipe, each unit pipe element being covered in an outer insulating coating (6, 6?) made of a thermoplastic material, with the exception of an end portion that does not have an outer insulating coating. The method includes: a step of welding together two abutting unit pipe elements; a step of positioning an annular sleeve (14) around a cut-back and in part around the outer insulating coatings of the two unit pipe elements, the sleeve being made of a thermoplastic material; a step of fastening the sleeve in sealed manner by weld bonding on the outer insulating coatings; and a step of applying an external pressure on the sleeve to enable it to be deformed elastically and match the shape of the respective end portions of the two unit pipe elements.

Abstract: An eversible liner is provided for insertion into a pipe for pipe repair. The liner comprises: an extender tube; a connector portion; and a liner tube; a first end of said extender tube being in substantially fluid tight communication with a first end of said connector portion; a second end of said connector portion forming a substantially fluid tight, detachable connection with a first end of said liner tube to form a first connection; said extender tube, connector portion and liner tube forming a continuous tubular construction which is capable of eversion; wherein the liner comprises a sealing member arranged to inhibit passage of a fluid from the liner tube to the extender tube or the connector portion. The present invention aims to improve detachability of a liner tube from an extender tube over currently available technology, while providing improved accuracy when repairing a pipe with said liner tube.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A method for molding a composite pressure vessel liner to secure a boss to the liner is described. The method comprises providing a moldable liner having an end section with a neck and a port. A boss is positioned around the neck of the liner and the liner is heated and pressure is applied to mold the liner to form to the shape of the boss. The angle of the molded liner secures the boss in place around the liner and it is able to withstand high pressures. A tool for molding the liner and a method for using the tool is also described. The tool comprises a tool body and a pipe having external threads. The tool body abuts the liner and the boss. Winding the pipe exerts pressure on the liner, which when heated, forces the liner to mold to the shape of the boss.

Abstract: Manufacturing systems for expandable components may include a controller, a heat and/or pressure source, and a transfer line. For example, the expandable components may be configured to transform from a compressed configuration to an expanded configuration upon application of heat and/or pressure. In addition, the controller may activate the heat and/or pressure source to release heat and/or gases that are directed to the expandable components via the transfer line. Further, the manufacturing system may also include an igniter, a manifold, and a valve to further control the release of heat and/or gases. Moreover, at least a portion of the heat and/or gases may be recaptured in a closed chamber and redirected to additional expandable components in other closed chambers. Furthermore, various post-processing may be performed on the components in their expanded configurations.

Abstract: Aircraft wing composite ribs having electrical grounding paths are described. An example composite rib includes a carbon fiber reinforced plastic (CFRP) panel, a metallic rib post, a metallic fitting, and a metallic grounding member. The metallic rib post is coupled to the CFRP panel and configured to be coupled to a spar of an aircraft wing, the spar being coupled to a current return network (CRN) cable. The metallic fitting is coupled to the CFRP panel and configured to be coupled to a skin panel of the aircraft wing. The metallic grounding member is positioned between the CFRP panel and the metallic fitting. The metallic grounding member provides an electrical grounding path extending from the metallic fitting to the metallic rib post.

Abstract: A method of fabricating a composite structure includes laying at least one composite ply about a bladder, the bladder comprising a phase change material in a first phase having a first volume, positioning an outer mold about the bladder and the at least one composite ply, and curing the at least one composite ply to form the composite structure. Curing causes the phase change material contained within the bladder to change to a second phase to expand from the first volume to a second volume and apply a pressure to an interior surface of the composite ply and press an outer surface of the composite ply against the outer mold to form an interior cavity. The bladder is not removable from the formed interior cavity.

Abstract: According to exemplary embodiments, a method for manufacturing a display device may include providing a bending object on a stage, bending the bending object by bringing a bending bar into contact with the bending object, and measuring a movement route of the bending bar.

Abstract: A method and system for fabricating a composite structure is provided. At least a first layer of reinforcement material is placed on a surface of a tool. At least a first layer of veil material is then wrapped around the first layer of reinforcement material while the first layer of reinforcement material is positioned on the tool to produce a first reinforced ply.

Abstract: A tool assembly includes a first piece, a second piece, and a fastener. The first piece has a first joint portion including a top surface and at least a first interlock surface. The second piece has a second joint portion configured to interlock with the first joint portion. The second joint portion includes a top surface and at least a second interlock surface that is complementary to the first interlock surface. The fastener extends through the first and second joint portions. The first interlock surface and the top surface of the first joint portion form an obtuse angle corner and the second interlock surface and the top surface of the second joint portion form an acute angle corner. The first interlock surface is configured to contact the second interlock surface to inhibit relative movement between the first piece and the second piece along a longitudinal axis of the tool assembly.

Abstract: Equipment (100) for processing items intended for commercial and non-commercial distribution, said equipment comprising a conveyor belt (1) for transporting and/or moving said items, means (30) for applying individually a label onto each of said items, said equipment (100) being configured so that each label is generated by means (34) for generating individual labels based on the identification data of the associated or corresponding item.

Abstract: A support structure for reinforcing first and second skins in an aircraft component includes a plurality of spars. A plurality of ribs is positioned on opposite sides of the spars. Each rib has a height extending from adjacent the first skin to adjacent the second skin. A plurality of first pis connects the ribs to the spars with each first pi having a length. A plurality of second pis secures the spars to the first and second skins. A plurality of third pis secures the ribs to the first and second skins. The first pis overlap with at least one of the second pis or the third pis.

Abstract: A team of robots may fabricate a tubular structure. Each robot may fabricate a tube by winding resin-covered fiber around an inflated, cylindrical mandrel of the robot. The resin may cure, resulting in a hardened tube segment The robot may extend the tube by fabricating additional segments of the tube, one segment at a time. After a first segment cures, the mandrel may deflate, then the robot may move up inside the tube, then the mandrel may inflate, and the robot may begin fabricating another tube segment. After completing a tube segment, the robot may tilt relative to that segment, before starting the next segment. By doing so, the robot may cause the tube to be curved. A computer may guide the team of robots during fabrication of the tubes, by executing a flocking algorithm. The algorithm may prevent collisions with already fabricated tube segments.

Abstract: A method and apparatus for a composite structure manufacturing system. The system comprises a heating system and one or more smart bladders that encompass the heating system. The heating system and the one or more smart bladders form a curing tool defining a volume for the composite structure when one or more smart bladders in the one or more smart bladders is in a rigid state.

Abstract: Apparatus and systems provide for the construction of wing sections having a plurality of wing spars abutted against each other to form a contiguous multi-box wing spar layup. An aircraft wing includes a plurality of wing spars configured to be attached to an aircraft fuselage, an upper wing surface, and a lower wing surface. The plurality of wing spars are in a multi-box wing spar layup. The plurality of wing spars, the upper wing surface, and the lower wing surface are composite layers having continuous fibers.

Abstract: A composite assembly has an outer spar component having an outer spar component inner profile, an inner spar component having an inner spar component outer profile substantially complementary to the outer spar component inner profile, and an adhesive disposed between the outer spar component and the inner spar component.

Abstract: A curable resin composition containing: (a) at least one resin; and (b) curative selected from the group consisting of (i) a mixture of at least one low temperature curative and at least one high temperature curative or (ii) a curative that has a low temperature curative part and a high temperature curative part wherein the amount of the low temperature curative is sufficient to cause enough resin-curative addition reaction to effect B-staging in the full resin-curative formulation, the amount of the high temperature curative is sufficient to cause the resin to cure catalytically but insufficient to cause resin-curative addition reaction in the final cure, and the ratio of the resin (a) to the curative (b) is greater than or equal to about 5. The present composition may be used to make prepregs for automotive or aerospace application.

Abstract: A rotor blade for a wind turbine comprising a blade root to be fastened to a rotor hub, a blade tip opposite the blade root, a rotor blade longitudinal axis extending from the blade root to the blade tip, an inner rotor blade part on the near side of the blade hub, especially encompassing the blade root, and an outer blade part on the far side of the blade hub, especially encompassing the blade tip. The inner rotor blade part and the outer rotor blade part are joined to one another in a joining zone which forms a bulge in the rotor blade.

Abstract: The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

Abstract: A method of manufacturing a tire curing bladder, the method includes the steps of (i) providing a cured tire curing bladder; and (ii) applying an air barrier composition to the cured tire curing bladder to form an air barrier layer. A method of restoring the air retention of a tire curing bladder, the method includes the steps of (i) providing a used tire curing bladder; and (ii) applying an air barrier composition to the used tire curing bladder to form an air barrier layer.

Abstract: Methods for manufacturing elongated structural elements are provided. Such methods provide composite material having optimal properties such as weight and strength which can be produced at much lower costs compared to conventional methods. Composite materials including such elements are also provided. In addition, commercial products incorporating such structural elements are provided.

Abstract: A method of manufacturing a pneumatic tire including forming a green case by cylindrically winding a tire component member which includes at least one layer of a carcass ply. A green tire is shaped by expanding the green case into a toroidal shape with the supply of a fluid into the green case so that the green case adheres to a tread ring arranged radially outside the green case. The green tire is subjected to vulcanization molding within a mold die. During the shaping of the green tire, the fluid is supplied in accordance with a pressure profile which changes in a stepwise manner. The pressure profile is set such that a former stage expansion rate in a former stage is set to slower than a final stage expansion rate in a final stage.

Abstract: Method for manufacturing stiffened panels comprising the following steps: forming a first and a second wet skin, each comprising a plurality of plies of preimpregnated composite material; forming a plurality of pairs of wet stringers, comprising a plurality of plies of preimpregnated material, wherein forming each pair of wet stringers comprises a) forming an assembly having a central web extending between opposite end flanges, and b) cutting the assembly along a median plane so as to form a pair of wet stringers, placing the pairs of wet stringers on the first wet skin by means of removable supporting members; turning the second wet skin over and placing it on the pairs of stringers, so as to obtain a pair of wet panels arranged above each other; and subjecting the pair of wet panels to a same curing cycle.

Abstract: Apparatuses and methods for making reinforcement structures are provided. In one example, an apparatus for making a reinforcement structure includes a rigid mandrel and a flexible bladder. The flexible bladder at least partially surrounds the rigid mandrel for supporting a reinforcement structure-forming material during fabrication of the reinforcement structure. The flexible bladder is configured to apply a force to the reinforcement structure-forming material in a direction opposite the rigid mandrel in response to a pressure differential between inside and outside of the flexible bladder.

Abstract: A system and method for pipe insertion in live gas mains includes isolating a section of the gas main and taking measurements of service line connection points. This data is then used to prepare a pipe to be inserted into the gas main by drilling holes and applying fittings at the appropriate locations. The prepared pipe is then inserted into the gas main and the service lines are connected to it without the need to excavate the street over each service connection. The inserted pipe is then fluidly connected to the cut ends of the gas main and gas flow is routed through the newly inserted pipe and the attached service lines, while gas continues to flow through the original portions of the gas main that still remain in service.

Abstract: A system includes a bladder configured to deform to at least partially surround a draping tool. The bladder has a pattern configured to distort as the bladder deforms. The system also includes an imaging device configured to generate image data of a sequence of images of the pattern of the bladder as the bladder deforms about the draping tool.

Abstract: Devices, systems, and methods for reducing stress on a blood vessel are disclosed herein. A damping device configured in accordance with embodiments of the present technology can include an anchoring member coupled to a flexible, compliant damping member including a generally tubular sidewall having an outer surface, an inner surface defining a lumen configured to direct blood flow, a first end portion and a second end portion, and a damping region between the first and second end portions. The inner and outer surfaces of the damping member can be spaced apart by a distance greater at the damping region than at the first or second end portions. When blood flows through the damping member during systole, the damping member absorbs a portion of the pulsatile energy of the blood, thereby reducing a magnitude of the pulse pressure transmitted to a portion of the blood vessel distal to the damping device.

Abstract: A medical balloon catheter including a catheter shaft and an inflatable balloon secured to a distal portion of the catheter shaft. One or more cutting blades are secured to the inflatable balloon by a first polymeric adhesive material forming a mounting pad encasing a base portion of the cutting blade therein, and a second polymeric adhesive material adhesively bonding the mounting pad to a surface of the balloon. The first polymeric adhesive material has a first ductility and the second polymeric adhesive material has a second ductility greater than the first ductility.

Abstract: A sheet bonding device includes a pressurization mold which is constituted of an upper mold and a lower mold and performs sealing through heating by sandwiching a sealing target portion of a bag main body and a sealing target portion of a gas barrier function sheet with pressurization surfaces; a plurality of support pins which are provided in the lower mold so as to be retractable and position the gas barrier function sheet with respect to one surface of the bag main body by penetrating the sealing target portions of the bag main body and the gas barrier function sheet; and gas spray means for making the gas barrier function sheet float by spraying inert gas to an area-enlarged portion, which does not overlap the bag main body, of the gas barrier function sheet supported by the support pins.

Abstract: A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web, an upper front spar cap, and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap. The winglet is manufactured by co-curing the upper skin to the upper main spar cap and the upper front spar cap; and co-curing the lower skin to the lower main spar cap and the lower front spar cap.

Abstract: A braided composite spar or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibers, wherein the spar or preform has a center line which extends lengthwise from a root to a tip, and at least part of the center line follows a curved path which does not lie in a single plane. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A system and method of a method of sealing a leak in an internal bladder within a hollow uncured composite part during cure thereof. The method may include placing a rescue bladder within the internal bladder and sealing an impermeable membrane and/or rigid forming tool to the rescue bladder, such that the uncured composite part is sealed within a chamber cooperatively formed by the impermeable membrane, the rigid forming tool, and the outer surface of the rescue bladder. A vent opening of the rescue bladder and/or a vent opening of the end fitting may remain located outward of the chamber. The method may also include curing the hollow uncured composite part, introducing a pressure differential causing the rescue bladder to inflate and press the internal bladder against an inner surface of the hollow uncured composite part.

Abstract: A braided composite spar or preform for a braided composite spar with a plurality of tubular plies of braided fibers. Each ply has a first set of fibers which wind in a clockwise direction in a first series of turns with a pitch between each adjacent pair of turns, and a second set of fibers which wind in an anti-clockwise direction in a second series of turns with a pitch between each adjacent pair of turns. The first and second sets of fibers in each ply are intertwined to form a braided structure. The spar or preform extends lengthwise from a root to a tip and has a tapered portion which tapers inwardly towards the tip. Each ply has a circumference in the tapered portion which reduces as it tapers inwardly. For at least one of the plies the pitches of the first and second sets of fibers increase continuously as the ply tapers inwardly in the tapered portion. The spar or preform can be used to provide a tubular main spar for a winglet.

Abstract: A composite material structure forming method capable of improving the shape and dimensional accuracy inside a composite material structure. The method includes: winding a prepreg (2) around an inner jig (6); stacking a ply (8) on the prepreg (2) wound around the inner jig (6); and forming a composite material structure by providing composite outer plates (4a, 4b) on an outer periphery of the inner jig (6) on which the ply (8) is stacked and mounting divided outer jigs (9) thereon.

Abstract: In exemplary implementations of this invention, an actuated fabricator deposits structural elements (e.g., tensile structural elements) in a 3D pattern over large displacements. The fabricator is supported by at least three elongated support members. It includes onboard actuators that translate the fabricator relative to the ends of the support members. The fabricator is configured, by actuating different translations along different support members, to translate itself throughout a 3D volume. In some implementations, each of the actuators use fusible material to fuse metal tapes together, edge-to-edge, to form a hollow structure that can be shortened or lengthened.

Abstract: A joint molding apparatus for molding joints between composite panels comprising inflatable molding bladders connectable to a source of pressurized fluid. A bladder support structure supports the bladders in respective positions adjacent an intersection of panels where, when inflated, the bladders support a joint formed at the intersection of panels while an uncured portion of the joint is curing to hold the joint in a desired configuration at the panel intersection.

Abstract: A bicycle assembly can include a main frame having a bottom bracket area to receive a bottom bracket. The bottom bracket area can be made of carbon fiber with one or more embedded seat blanks to serve as bearing surfaces within the bottom bracket area. The disks may be machined to a high tolerance to receive a bottom bracket.

Abstract: A system for manufacturing a filled plastic container includes an actuator, a base unit including a heating surface, and a dispensing device or nozzle. The actuator includes a body portion and a holding/securing member configured to hold or secure a portion of the container. In embodiments, the actuator is configured to apply a force or pressure on the container to contact the base unit, the base unit is configured to receive a base portion of the container, the heating surface is configured to convey energy or heat to a portion of the base portion of the container, and the dispensing device or nozzle is configured to introduce an inert gas into the container. Methods for providing a filled plastic container and providing a thin-walled plastic container are also disclosed.

Abstract: A method for fabricating a flexible substrate and a flexible substrate prefabricated component are disclosed, the flexible substrate comprises an electronic device and a flexible layer provided with the electronic device. The fabrication method comprises: disposing a single-sided adhesive layer at a central portion of a surface of a support substrate, an adhesive side of the single-sided adhesive layer being in contact with the support substrate; disposing a double-sided adhesive layer at a peripheral region of the support substrate; disposing the flexible layer on surfaces of the single-sided adhesive layer and the double-sided adhesive layer, the flexible layer being bonded to the double-sided adhesive layer; disposing the electronic device in a region of a surface of the flexible layer corresponding to the single-sided adhesive layer; cutting the flexible layer along a boundary of the electronic device and removing the flexible layer from the single-sided adhesive layer.

Abstract: A machine and method for making an inflatable product is disclosed. The inflatable product has an upper layer and a lower layer. The machine having a presser, a welder press frame, an upper flat plate secured to the presser, and a lower flat plate secured to the welder press frame. Each flat plate has a plurality of slide rests, each slide rest having a plurality of detachable plates positioned along the slide rest. A lower layer of material is placed on top of the lower flat plate and on top of the plurality of detachable plates on the lower flat plate. A plurality of die assemblies is positioned on top of the lower layer of material in a manner where each die assembly is aligned with a corresponding slide rest. Then, an upper layer of material is placed on top of the die assemblies and below the upper flat plate. The upper flat plate is pressed on top of the upper layer of material to perform heat welding.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A tethermast and frag wall includes a fabric device having a fill volume fillable with a fill material on a flexible or compliant mast system. The fill volume may be a chambered curtain. The tethermast and frag wall is self supporting, easily deployed, and may be used in connection with a structure or may be deployed stand-alone. A tether system for an air beam structure utilizing a flexible tethermast, an external frag wall or frag curtain, soft couplings, air beam slings, or combinations thereof to reduce the effects of pressure waves, such as blast waves, onto and into an air beam structure and any inhabitants.

Abstract: Methods of co-curing aligned annular supports in a tubular region of a composite structure, such as a rotor blade, are disclosed. Methods include assembling an uncured composite structure by positioning an inboard annular support and an outboard annular support around an arbor, forming reinforcement fiber into a tubular region in contact with the supports, and applying a matrix material to the reinforcement fiber. The inboard and outboard annular supports are substantially composed of metal. Methods also include concentrically aligning the arbor and the supports along a common axis by applying heat to cause differential expansion of the arbor with respect to the supports, wherein the differential expansion causes an interference fit of the supports against the arbor. Methods also include curing the uncured composite structure to form the composite structure.

Abstract: A system and method for manufacturing a golf ball with one or more patterned film layers is disclosed. The system and method may involve creating a patterned film layer and applying the patterned film layer to the surface of a golf ball. The patterned film layer may include a layer of film having cutouts leaving the remaining portions of film in a pattern. The pattern may include a net pattern. The patterned film layer may include a material that is relatively harder or relatively softer than the surface of the golf ball. The method may include removing portions of film from a film material to create a patterned film material, cutting the patterned film material into sheets, molding two patterned film sheets into substantially hemispherical cups, and applying the two substantially hemispherical cups to a golf ball.

Abstract: An apparatus for the reeling up of fiber bundles, in particular of hollow fiber membrane bundles, and in particular for the manufacture of dialysis filters, includes a reel carrier rotatable around a main axis. The apparatus includes at least two reels which are rotatably supported on the reel carrier, with the axes of rotation of the reels being perpendicular to the main axis of the reel carrier. The apparatus can be used for the wrapping of a fiber bundle with a film, having a receiver of first and second side elements and a flexible channel fastened between them for the reception of the film and the fiber bundle. A drive is provided to move at least the first side element transversely to the channel, and at least one folding device movable transversely to the flexible channel for the folding of the film around the fiber bundle.

Abstract: In order to make a structure of a composite material including elongated hollow shapes, such as hollow shapes associated with stiffeners of a stiffened panel, the invention comprises making cores including a bladder made of an elastomer material. The invention relates to a method for making such extractable cores in order to obtain cores having a very important length, and allowing the use of said cores for the industrial production of composite parts. The bladder is a cylindrical bladder that is conformed in a core mould, wherein the core itself does not have to be cylindrical, before being filled with a granular material and submitted to a negative pressure in order to impart a stable shape to the core by compaction of the granular material.

Abstract: A container for containing a liquid or pasty material which is combined with a system for collecting and dispensing without taking in air. The container is rigid and includes a flexible bag which contains the material to be dispensed and which is combined with the collecting system. The bag is produced separately from the rigid container and has an overall cylindrical reservoir which is open at the top portion thereof and which is divided into four areas defined by a rigid upper sidewall, a flexible deformable lower sidewall, and a fillet connecting the flexible side wall to a base.