Abstract: A shaped article, a method for making it, and its use. The shaped article is formed from flat fiber material and has a bottom (2), a body (4), and an opening, which is surrounded by a circumferential flange (6). The shaped article (1) comprises a flange stabilizer (10) attached to the second flat side (18) of the flange (6) facing the bottom (2). The flange stabilizer (10) is disc-shaped and has an inner contour (12) corresponding to the desired cross-sectional shape of the shaped article (1) in the region of the opening and can be slipped over the body (4) in the region of the bottom (2) and up to the flange (6). The flat sides (16, 18) of the flange stabilizer (10) extend essentially parallel to the flange (6), defining and stabilizing the cross-sectional shape of the body (4) in the region of the opening and the flange.

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: A packing material including a plurality of discrete cushioning elements and methods for making the same. The discrete cushioning elements may be cellulosic cushioning elements. A flexible linkage may connect the plurality of discrete cushioning elements in the packing material. The packing material may also include a bottom cellulosic sheet connected to a top cellulosic sheet with the plurality of cellulosic cushioning elements positioned between the top cellulosic sheet and the bottom cellulosic sheet. The packing material may also be a molded packing material that includes bonds comprising adhesive and cellulosic fibers. The adhesive and cellulosic fibers of the bonds may be dispersed between the folds of each of the cellulosic cushioning elements.

Abstract: A substantially metal-free exhaust subsystem includes an exterior housing formed of polymer; and a pipe formed of a layered fibers formed at least partially of glass, and bound by an inorganic binder. The fibers may be glass or ceramic, and may define micro-pores on the interior of the pipe that aid in absorbing acoustic energy, and thereby attenuating exhaust noise.

Abstract: A process for shaping a fibrous preform includes the insertion of each attachment tab of a fibrous texture into a corresponding aperture of an impregnation mandrel, the attachment by a removable retaining device of each tab inserted into each aperture against a surface of the impregnation mandrel, the winding under tension of the fibrous texture on the impregnation mandrel in order to obtain a fibrous preform.

Abstract: An abrasive product having an abrasive surface, a belt of an abrasive product, a roll of an abrasive product and a method for manufacturing an abrasive product. An abrasive product includes a backing and an abrasive surface. The abrasive surface includes at least a first abrasive area and a second abrasive area, wherein abrasive properties of the first abrasive area are different from abrasive properties of the second abrasive area.

Abstract: A center wing box assembly for an aircraft which includes: a composite lower wing skin, a composite upper wing skin and a composite spar which extends between the composite lower wing skin and the composite upper wing skin. The center wingbox assembly further includes a composite stringer which extends along a web of the composite spar in a wing span direction. The composite spar has a co-cure securement with the composite lower wing skin and with the composite upper wing skin and the composite stringer has a co-cure securement with the web of the composite spar.

Abstract: Apparatus for forming composite plies on a contoured tool includes a forming head for forming the composite plies on the tool. The forming head is mounted on a manipulator and includes a compliant nosepiece adapted to conform to the contoured tool.

Abstract: Composite structure fabrication systems and methods. The systems include a plurality of ply carriers, each of which is configured to support at least one ply segment, and an elongate forming mandrel, which defines an elongate ply forming surface that is shaped to define a surface contour of the composite structure. The systems further include a carrier transfer device, which is configured to selectively convey a selected ply carrier from a ply kitting area to an intermediate location, and a forming machine, which is configured to deform the selected ply carrier and a respective ply segment over a selected portion of the elongate ply forming surface. The forming machine further is configured to separate the selected ply carrier from the respective ply segment and return the selected ply carrier to the carrier transfer device. The methods include methods of operating the systems.

Abstract: A method of producing a composite component (10) having a thermal protection layer (24) including the steps of: providing a composite component (10) with a primary fibre material (12) and with a primer layer (16) of alternative fibre material overlying the primary fibre material (12) at an area of the composite component intended for high thermal exposure, said area defining a thermal exposure area (18); applying a metallic bonding layer (22) to the primer layer (16) of the thermal exposure area (18) to create a bonding surface at the thermal exposure area (18); and applying a ceramic thermal protection layer (24) to the bonding surface for insulating the thermal exposure area (18) and/or for reflecting external thermal energy, the thermal protection layer (24) having a higher melting point than the metallic bonding layer (22).

Abstract: A floor panel for installation in an aircraft includes a plurality of thermoplastic C-shaped stringers, a consolidated thermoplastic deltoid filler, a thermoplastic upper facing sheet, and a thermoplastic lower facing sheet. The stringers are disposed in a parallel arrangement with one another. The deltoid filler is disposed within a longitudinally-extending notch defined by a pair of adjacent stringers. The upper facing sheet covers an upper surface of the stringers and the deltoid filler. The lower facing sheet covers a lower surface of the stringers and the deltoid filler. The stringers, the deltoid filler, and the upper and lower facing sheets are integrally consolidated forming a unitary construction.

Abstract: A device for a fishing reel comprising a resin composition includes a polyarylene sulfide resin composition (component A), a glass fibers (component B) contains 10 to 300 parts by weight of the component B based on 100 parts by weight of the component A, an aramid fibers (component C) contains 1 to 100 parts by weight of the component C based on 100 parts by weight of the component A, and a fluoric resin (component D) contains 5 to 100 parts by weight of the component D based on 100 parts by weight of the component A.

Abstract: A method for applying fibre material on a vertical surface is provided. The method has the following steps: spraying an adhesive on the vertical surface; applying the fibre material on the sprayed surface; spraying additional adhesive on the fibre material for another layer of fibre material; applying another layer of fibre material on the sprayed fibre material; and injecting the layers of fibre material with a resin.

Abstract: Apparatus for manipulating a wind turbine blade and method of blade handling An apparatus for manipulating a wind turbine blade having fixed lifting points (2) on the blade has a blade turner base (36,62,82,100), a frame like support structure (34,64,84,112) carried on the base and connecting structures such as brackets (32,138) which engage in the lifting points (2) on the blade extending into openings in the blade, the support structure (34,64,84,112) having a part-circular portion or periphery at which it connects to the base, being movably supported on the base so as to rotate relative thereto about a substantially horizontal axis in order to vary the orientation of a blade supported thereon.

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: There is provided a method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform including a base and a stiffener, the method including using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform; shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform; positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform; placing the fiber preform with the gaskets in an injection mold; injecting resin into the injection mold; compacting the assembly; heating the injection mold to solidify the resin; and unmolding the resulting platform.

Abstract: The present disclosure is directed to a method of forming a root portion of a wind turbine rotor blade. A plurality of alignment pins coupled to an alignment plate is aligned with a first set of a plurality of insert cavities defined by a prefabricated panel. Each alignment pin is positioned within one of a first set of a plurality of installation apertures defined by the alignment plate. The prefabricated panel and the alignment plate are coupled such that each alignment pin is positioned within one of the first set of the plurality of insert cavities. A first adhesive is placed in each of the second set of the plurality of insert cavities. A first set of inserts are placed into a second set of the plurality of insert cavities. The first set of inserts and the alignment plate are coupled, and the first adhesive is cured.

Abstract: A method of fabricating a thermoplastic composite tubular structure for use as a wind turbine blade is presented using a combination of induction heating with smart susceptors to consolidate a wrapped mandrel. The method can include overbraiding the mandrel with a continuous fiber thermoplastic composite material to form an overbraided mandrel that is then installed in a ceramic induction oven where the mandrel is pressurized internally to consolidate the thermoplastic overbraid during heating.

Abstract: A honeycomb body includes wound and/or stacked layers having a geometric center axis, a cavity rotationally symmetrically around the center axis and an outer lateral surface. Each layer extends approximately concentrically around the axis. At least one of the layers is at least partially structured forming channels through which a fluid can flow. The channels extend from the cavity outward to the outer lateral surface at a non-right cone angle to the axis. The channels have a cross-section changing along the channels from inside to outside. At least one structured layer and at least one intermediate layer are alternatingly disposed and helically layered. The structure height of the structured sheet-metal layer forming the channels is substantially constant and channel cross-sectional areas increase from inside to outside. The intermediate layer can be made of simple wires or of specially cut or folded smooth sheet-metal layers.

Abstract: A manufacturing method and structure of a carbon fiber rim is revealed. A metal strip is formed by heating a metal substrate to a moldable temperature and then extruded molding. The metal strip comprises two side walls, a connecting wall and an inner rim wall to form a space surrounded by the side walls, the connecting wall, and the inner rim wall. Next, two terminals of the strip are connected to form a circle as a rim frame's embryo. The two side walls, or the two side walls and the inner rim wall of the rim frame's embryo are milled to form plural through holes and become a rim frame. Afterwards, the surface of the rim frame is roughened and covered with a trimmed carbon fiber cloth having a predetermined shape. After heatsetting and surface treating, a carbon fiber rim having a light weight and a strong structure is obtained.

Abstract: A product made from an extruded sheet or web of material having a non-linear cross-section, and the process of making the product are provided. The extruded web or extrudate is plastically deformed in selected areas and then folded. When folded into the appropriate shape, the extrudate is formed into a product having a plurality of cells. The cells may have one or more openings, allowing access to an interior of the cell and reducing the weight of the product.

Abstract: A method for joining fittings to a composite sandwich shell edge includes laying up an inner facesheet and positioning a wrapped flute mandrel on top; applying a layer of adhesive on the inner facesheet and positioning spacer-supported fittings on top; applying adhesive over the co-bonded fittings and laying up an outer facesheet forming an assembly; curing the assembly under heat and pressure; removing the fittings by first collapsing the spacers and removing the flute mandrel; placing an adhesive layer on the fittings with collapsible spacers inserted therein; reinserting the fittings between the inner and outer facesheets and effecting bonding and curing; and removing the spacers from the fittings by collapsing the spacers.

Abstract: This invention relates to a method of making a container having a separable inner lining and outer shell, and in particular to a method of forming a flexible lining for a container. This invention also relates to apparatus for use in such methods. A method of forming a flexible lining for a container comprises providing a former having a substantially flat end face and a perimeter surface extending from the end face, the former having external shape and dimensions substantially the same as the internal shape and dimensions of the container, forming a sleeve of plastics material around the perimeter surface of the former, an edge region of the sleeve extending beyond the end face of the former, heating the edge region to substantially conform the edge region to an edge portion of the end face of the former, and bonding a sheet of plastics material to the conformed edge region of the sleeve to form a base of the lining.

Abstract: A method for producing a fiber preform by winding at least one thread in a groove of a mold. The method involves using a flexible element which is capable of becoming deformed by means of flexion, in a plane which contains the winding axis, in order to penetrate into the groove in order to push the sections of the thread(s) towards the base of the groove and/or towards zones which cannot be accessed directly by the thread(s). A set of tools for implementing the method is also provided.

Abstract: Methods and tools for forming composite structures with predetermined, non-planar patterns of contours, as well as apparatuses including such composite structures, are disclosed herein. Example methods include defining a pattern of contours in a flexible sheet of composite material, conforming the flexible sheet of composite material to a layup mandrel, and curing the flexible sheet of composite material. Example tools include a body with an engagement surface for engaging a flexible sheet of composite material, the body having regions of relative stiffness and regions of relative compliance, and a vacuum distribution manifold configured to selectively apply a vacuum to the regions of relative compliance to deform the engagement surface to define a predetermined, non-planar pattern of contours.

Abstract: The present invention provides a technique which can disassemble a mandrel having a substantially cylindrical shape and being dividable into a plurality of segments, easily and efficiently. The disassembling method comprises, in the mandrel adhesively attached with a composite material structure on an outer peripheral surface thereof, a rotation step of rotating the pair of support rings along with the mandrel to position a segment which is a detached target to an uppermost portion; and a segment detaching step of detaching the segment which is the detached target positioned at the uppermost portion, from the pair of support rings; wherein in the segment detaching step, the segment which is the detached target is moved in a vertically downward direction to a position inside of the mandrel, between the pair of support rings, and is carried out from between the pair of support rings.

Abstract: A composite enclosure for housing electronic devices, and methods related thereto, are provided. In particular, in some embodiments, a method of manufacturing a composite enclosure for housing electronic devices includes winding composite material about a mandrel and curing the composite material to create a composite hoop. A panel is formed in a separate process that includes stacking a plurality of composite layers in a mold and curing the composite layers to create a composite panel. The composite hoop and the composite panel are bonded together to form the composite enclosure.

Abstract: This invention is directed to a polymeric pressure vessel comprising a wall prepared by living polymerization such that the wall comprises a single layer of polymer having two sub-layers, an inner sub-layer that is not a composite and an outer layer that is.

Abstract: A process for producing a shell-shaped hollow body composed of fiber-reinforced plastic in which, in a first step, a continuous hollow body made of fiber-reinforced plastic is produced. In a second step, the continuous hollow body is separated into a plurality of shell-shaped hollow bodies. Such a shell-shaped hollow body is applicable in vehicle construction, for example, as chassis or bodywork.

Abstract: A non-compliant medical balloon may be changed from a deflated state to an inflated state by increasing the internal pressure within the balloon. The balloon comprises a balloon layer having an outer surface, the balloon layer including a base layer, a first reinforcing layer and a second reinforcing layer. The base layer is formed of a polymer material. The first reinforcing layer is one of either a plurality of discrete inelastic fibers oriented substantially parallel to the long axis of the balloon and a first layer of textile fabric material, the textile fabric material being one of a woven, knitted, braided and non-woven fabric. The second reinforcing layer is one of either at least one inelastic fiber wrapped around the circumference of the balloon substantially transverse to the long axis of the balloon and a second layer of textile fabric material, the textile fabric material being one of a woven, knitted, braided and non-woven fabric.

Abstract: A machine uses a method for producing a cup from an outer shell and inner cup. For this purpose, the machine includes first holding devices that are arranged on a first rotatably housed star- or wheel-like holding device carrier, and second holding devices arranged on a second rotatably housed star- or wheel-like holding device carrier. Further, a first working station arranged at least in the region of the first holding devices for carrying out first working steps and at least one second working station arranged in the region of the second holding devices for carrying out second working steps are provided. Finally, the machine includes a transfer station for transferring a finished outer shell from a first holding device to a second holding device.

Abstract: A method of making a portion of a bicycle frame including positioning a low-friction mandrel adjacent a flexible mandrel with a first fibrous material in between. The mandrels are wrapped with second fibrous material, and the mandrels are inserted into a mold. The second fibrous material is cured to produce a cured assembly, the cured assembly is withdrawn from the mold, and the low-friction mandrel is removed from the cured assembly to produce an internal passageway. The flexible mandrel can includes a recess, and the step of positioning can include inserting the low-friction mandrel into the recess of the flexible mandrel. Preferably, the low-friction mandrel has a cross sectional shape that substantially matches a cross-sectional shape of the recess. The invention is also embodied in a portion of a bicycle frame, such as a portion of the frame during the manufacturing process, and having similar features as recited above.

Abstract: A method of manufacturing a plurality of reinforcing element preforms, involving the steps of: positioning reinforcing elements on the external surface of a die; assembling the reinforcing elements thus positioned with one another so as to form a textile sleeve with a longitudinal axis and surrounding the die; moving the sleeve longitudinally toward a multi-cavity mandrel having an elongate overall shape, the multi-cavity mandrel having on its external surface a plurality of longitudinal cavities which are distributed, when viewed in cross section, around the periphery of the external surface; forming the sleeve on the plurality of peripheral cavities so that the sleeve conforms to the shape of the multi-cavity mandrel and thus adopts the shape of a set of reinforcing element preforms.

Abstract: Systems, tools, and methods for forming composite tubular stringers and stiffened composite structures having composite tubular stringers are disclosed. Systems include a tool, a supply of pliable blanks for forming composite tubular stringers with the tool, a supply of skin segments for forming a skin, and a layup mandrel for receiving the composite tubular stringers and the skin to form a stiffened composite structure. Tools include a wrapping mandrel for forming from a pliable blank a tubular structure with a first circumferential profile, and a transition mandrel for conforming the tubular structure to a second circumferential profile. Methods include wrapping a pliable blank around a wrapping mandrel to define a tubular structure having a first circumferential profile, and transitioning the tubular structure from having the first circumferential profile to having a second circumferential profile.

Abstract: A method for joining fittings to a composite sandwich shell edge includes laying up an inner facesheet and positioning a wrapped flute mandrel on top; applying a layer of adhesive on the inner facesheet and positioning spacer-supported fittings on top; applying adhesive over the co-bonded fittings and laying up an outer facesheet forming an assembly; curing the assembly under heat and pressure; removing the fittings by first collapsing the spacers and removing the flute mandrel; placing an adhesive layer on the fittings with collapsible spacers inserted therein; reinserting the fittings between the inner and outer facesheets and effecting bonding and curing; and removing the spacers from the fittings by collapsing the spacers.

Abstract: A method is disclosed of directing bias tows of a fabric to be wrapped around a form to create a fabric preform. The fabric includes at least a first set of bias tows that are generally parallel with one another and a second set of bias tows that are generally parallel with one another but that are not parallel with the first set of bias tows. An edge strip is attached to ends of the first set of bias tows at a first lateral edge of the fabric relative to a feed direction of the fabric onto the form. The edge strip is moved to direct the first set of bias tows. The fabric is wrapped around the form by rotating the fabric and form relative to one another about the central axis of the form to create the fabric preform.

Abstract: A prepreg winding method includes the steps of preparing a plate, a mandrel movable toward and away from the plate, and a press roll movable toward and away from the mandrel and having an axis parallel to the mandrel; mounting a prepreg on the plate, the prepreg being formed by impregnating reinforced fibers with a thermosetting resin sheet; winding a leading end of the prepreg mounted on the plate around the mandrel, and making a pressing force act on the plate and the mandrel therebetween with the prepreg sandwiched between the plate and the mandrel and making a pressing force act on the mandrel and the press roll therebetween with the prepreg sandwiched between the mandrel and the press roll; and winding the prepreg around the mandrel by rotating the mandrel and the press roll.

Abstract: A method for making a gas turbine engine matrix composite structure. The method includes providing at least one metal core element, fabricating a matrix composite component about the metal core element, and removing at least part of the metal core element from the matrix composite component by introduction of a halogen gas.

Abstract: The present disclosure provides a composite material comprising a silicone component and an electrospun, porous polymeric component and methods of producing such a composite material. The layers are preferably processed so as to result in some degree of penetration of the silicone component into the pores of the electrospun polymeric component. The composite materials can be tailored for use in a range of different applications.

Abstract: An optical fiber with a b-stageable hybrid adhesive coating includes an optical fiber and an outer jacket. The outer jacket includes at least one layer that includes a partially cured b-stageable hybrid adhesive.

Abstract: A leaflet for a prosthetic valve formed of at least one layer that includes a composite material containing at least one expanded fluoropolymer membrane having serpentine fibrils and an elastomer is provided. The fluoropolymer may be polytetrafluoroethylene. In at least one embodiment, the elastic properties are present in an axial direction the leaflet. The leaflets may be single layered or multi-layered. The leaflets may be coupled to a support structure and movable between open and closed configurations relative to the support structure to form a heart valve. The elasticity within the leaflets permits, among other things, the leaflets to bend with a reduced occurrence of wrinkles as the valve opens and closes. The elastic properties of the leaflet also, among other things, improve bending properties and reduce closure stresses, thereby extending the life of the leaflet.

Abstract: A silicone tape having inherent elasticity and flexibility to allow for its significant stretching, which when unrolled from its tape roll, and its laminar film removed, can be stretched around the furniture or other componentry to hold it in position until any applied adhesive hardens, during furniture repair or manufacture.

Abstract: A tape laminating machine having a compaction roller lays up composite tape over a substrate having a convex radius. The compaction roller folds the tape as it moves over the convex radius, while simultaneously pivoting about a trailing edge of the tape to prevent the compaction roller from lifting off the tape laid just before the convex radius.

Abstract: A method for manufacturing a radial shaft of a gas-turbine engine which is made up of +/?45° layers, zero layers and +/?30° layers of carbon fiber composite and connected to load-input end pieces via sinusoidal connecting areas.

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

Abstract: The invention provides a method for producing a component (37) for aerospace, with the following method steps: supplying a lay-up arrangement (1) to be laid by means of a tape-laying machine (25), with a glass-fiber lay-up (8), which is preimpregnated with a resin matrix (10), and/or supplying a structural arrangement (12) to be laid by means of a tape-laying machine (25), with a structure (16) which is made of metal and is preimpregnated with a resin matrix (18), laying the lay-up and/or structural arrangement (1; 12) on a laminating apparatus (23) by means of a tape-laying machine (25), and curing the lay-up and/or structural arrangement (1; 12) and therefore forming the component (37).

Abstract: A flexible mandrel 100 has a plurality of flexible elements 130 extending between two spaced flanges 110, 120. A means for adjusting the radial position of each of the flexible elements 130 along the length of the mandrel 100 between the flanges 130 enables the plurality of flexible elements 130 to be configured in a variety of symmetrical and asymmetrical forms. Conventional composite fiber or tape laying techniques may then be used to form one-piece, revolute, composite components. The flexible mandrel 100 can then be collapsed and withdrawn from the interior volume 202 of the formed component.

Abstract: A mandrel suitable for forming a hollow part from a heat curable material includes an (a) an elongate central member having a coefficient of expansion which is different than the coefficient of expansion of the cured heat curable material, (b) at least one lateral member disposed at a first location and projecting away from the outer surface of the central member, the lateral member being slidably attached to the central member, and (c) a rigid elongate strut member having a coefficient of expansion substantially similar to the coefficient of expansion of the cured heat curable material. The first end of the strut member is affixed to the lateral member, and the second end of the strut member is affixed spaced apart from the lateral member.

Abstract: A method for fabricating a one-piece composite fuselage section that minimizes out-of-plane fiber distortion. This is accomplished by fabricating a mandrel having a coefficient of thermal expansion in the hoopwise direction that is sufficiently greater than that of the laid-up composite ply assembly. As a result of this differential in the coefficients of thermal expansion in the hoopwise direction, the laid-up composite ply assembly is stretched circumferentially as the mandrel expands radially during cure, thereby eliminating or reducing out-of-plane fiber distortion. At the same time, the mandrel and part being fabricated should have substantially the same coefficient of thermal expansion in the lengthwise direction. As the outer surface of the mandrel increases in circumference, the circumferentially oriented reinforcing fibers of the inner plies are stretched, while the circumferentially oriented reinforcing fibers of the outer plies do not reduce in circumference and thus do not form waves or wrinkles.

Abstract: A non-compliant fiber-reinforced medical balloon comprises a first fiber layer and a second fiber layer embedded in a continuous matrix of thermally-weldable polymer material defining a barrel wall, cone walls and neck walls. The fibers of the first fiber layer have a pattern of different lengths and are divisible into a first group and a second group based on length. The length of the fibers of the second group varies progressively in accordance to their proximity to the fibers of the first group; the fibers of the second group closest to the fibers of the first group being longer than the fibers of the second group further from the fibers of the first group. The fiber of the second fiber layer winds circumferentially around the longitudinal axis of the balloon substantially over the entire length of the balloon.