Abstract: The invention relates to a multifilament yarn containing n filaments, wherein the filaments are obtained by spinning an ultra-high molecular weight polyethylene (UHMWPE), said yarn having a tenacity (Ten) as expressed in cN/dtex of Ten(cN/dtex)=f×n?0.05×dpf?0.15, wherein Ten is at least 39 cN/dtex, n is at least 25, f is a factor of at least 58 and dpf is the dtex per filament.

Abstract: Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0° and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line.

Abstract: A composite sheet includes a matrix impregnated with a fiber base. The fiber base includes first yarns and second yarns, and the second yarns intersect the first yarns at a constant angle. Each of the first and second yarns has an angle of greater than 0° to less than about 180° relative to a first direction of the matrix. A flexible display apparatus includes the composite sheet.

Abstract: A ballistic laminate includes a layer including first fibers of a first material oriented at both a first direction and a second direction and second fibers of a second material oriented at both the first direction and the second direction. The first fibers are flammable, and the second fibers are flame retardant. A periodic distance greater than about 9 mm is between the second fibers of the second material oriented at the first direction. A periodic distance greater than about 9 mm is between the second fibers of the second material oriented at the second direction.

Abstract: Fabrication of ballistic resistant fibrous composites having improved ballistic resistance properties. More particularly, ballistic resistant fibrous composites having enhanced a dynamic storage modulus, which correlates to low composite backface signature.

Abstract: A multilayer structure (4) of the present invention includes a hollow plate-like body (1) made of a thermoplastic resin, and a fiber sheet (2) and a thermoplastic resin film (3) that are laminated on at least one principal surface of the hollow plate-like body. Even if this multilayer structure (4) is curved, raised wrinkles (6) are not formed or not likely to be formed on the inner surface due to buckling or bending, so that the strength is not likely to be reduced. Thus, the multilayer structure can satisfy both flexural rigidity and flexural strength while maintaining the light weight. The fiber sheet (2) is preferably a multiaxial fiber sheet and/or a woven fabric. The lamination is preferably thermal lamination using an adhesive film interposed between the layers.

Abstract: Electromagnetic radiation scanning is used to monitor the integrity of a composite laminate structure. The laminate is designed to be optically resonant at the frequency of the radiation, allowing the inconsistencies in the laminate to be detected and mapped.

Abstract: Fabrication of ballistic resistant fibrous composites having improved ballistic resistance properties. More particularly, ballistic resistant fibrous composites having high interlaminar lap shear strength between component fiber plies or fiber layers, which correlates to low composite backface signature. The high lap shear strength, low backface signature composites are useful for the production of hard armor articles, including helmet armor.

Abstract: High tenacity, high elongation multi-filament polymeric tapes as well as ballistic resistant fabrics, composites and articles made therefrom. The tapes are fabricated from multi-filament fibers/yarns that are twisted together, bonded together, compressed and flattened.

Abstract: A composite laminate is made by providing at least a first composite ply and a second composite ply, each having longitudinally oriented fibers in a thermoplastic matrix. The second composite ply is disposed on, and in transverse relation to, the first composite ply. Preferably, the second ply is disposed at 90° relative to the first ply. An article can be manufactured by providing a core material and applying a reinforcing material to a portion of the core material. The reinforcing material is a reinforcing composite ply or a composite laminate as described herein. Optionally, the core material is a prepreg that may be a composite laminate.

Abstract: The present disclosure describes use of filamentous algae to form insulating construction materials which provide thermal and noise insulation. Algae from the order Zygnematales, the Cladophorales, or the Ulotrichales can be dried and formed for use as insulating material. Algae mass can be combined into several layers, using a binder to attach the layers to each other. A composite material of algae mass and an additive can be used and form the body of insulation panels having honeycomb-shaped chambers, which are sealed by a foil that is laminated onto the body.

Abstract: A stiffened structure includes stiffeners (14.1, 14.2, 14.3) and nodes (12) at which three stiffeners (14.1, 14.2, 14.3) of different directions intersect, with the surfaces of the stiffeners (14.1, 14.2, 14.3) being arranged in planes that are perpendicular to the same plane, whereby the stiffened structure includes at least one opening (26) and is characterized in that the opening (26) is surrounded by a hexagonal belt, formed by peripheral stiffeners (40).

Abstract: Electrostatic dry adhesive devices having a microstructured dry adhesive element formed directly into a contact surface of an electrostatic adhesive. The microstructured dry adhesive element, such as in the form of microwedges, can be molded into surface of an electrostatic adhesive. Also provided are associated methods of making such adhesive devices.

Abstract: Ballistic resistant composite articles that are resistant to both backface deformation and ballistic penetration. Multiple composites are attached to each other such that fibers in each adjacent composite are oriented at different angles. Each composite has an areal density of at least about 100 g/m2 wherein the areal density of the strike face composite is greater than half of the total areal density of overall multi-composite article.

Abstract: A composite material structure and a method for making the composite material structure are provided. The composite material structure includes a first stack of fiber panels arranged with fibers parallel to a loading axis to accommodate a first tension load in a first plane. The composite material structure includes a second stack of fiber panels arranged with fibers parallel to the loading axis to accommodate a second tension load in a second plane. The composite material structure includes a pre-consolidated fabric structure between the first and the second stack arranged with fibers plied perpendicular to the fibers of the first stack of fiber panels and perpendicular to the fibers of the second stack of fiber panels, the fibers further being orthogonal to the loading axis.

Abstract: A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.

Abstract: Woven fabrics are formed from high tenacity fibers or tapes that are loosely interwoven with adhesive coated filaments, to composite articles formed therefrom, and to a continuous process for forming the composite articles.

Abstract: A method of manufacturing an electronic component includes disposing a heat radiation material including a plurality of linear structures of carbon atoms and a filling layer of a thermoplastic resin provided among the plurality of linear structures above a first substrate, disposing a blotting paper above the heat radiation material, making a heat treatment at a temperature higher than a melting temperature of the thermoplastic resin and absorbing the thermoplastic resin above the plurality of linear structures with the absorption paper, removing the blotting paper, and adhering the heat radiation material to the first substrate by cooling to solidify the thermoplastic resin.

Abstract: An energy absorbing system has an inner tube and an outer tube that are stitched together. The inner tube contains a set of fibers oriented in a first direction and the outer tube has a second set of fibers oriented in a direction different from the first direction. Preferably these orientations are equal and opposite to each other. The inner tube may be hollow, but preferably has a cellular core. The outer tube may be spaced apart from the inner tube to create an annular cavity that is filled with a cellular material.

Abstract: Fabrication of ballistic resistant fibrous composites having improved ballistic resistance properties. More particularly, ballistic resistant fibrous composites having enhanced flexural properties, which correlates to low composite backface signature. The composites are useful for the production of hard armor articles, including helmet armor.

Abstract: A graphene/carbon nanotube composite structure includes a carbon nanotube film structure and a graphene film. The carbon nanotube film structure includes a number of carbon nanotubes. The carbon nanotubes form micropores. The graphene film is located on a surface of the carbon nanotube film structure. The graphene film covers the micropores.

Abstract: A composite laminate comprises a plurality of plies of reinforcing fibers. At least some of the plies have reinforcing fibers oriented at ±? with respect to an axis of primary loading, where ? is between 2 and 12 degrees. At least some of the plies have reinforcing fibers oriented at ±? with respect to the axis of primary loading, where ? is between 50 and 85 degrees.

Abstract: An open mesh material includes filaments (1, 2, 3, 4, 11, 12, 15, 16) that intersect one another. At least some of the filaments are composite filaments having a carrier portion of a relatively high melting point and a bonding portion of a relatively low melting point, the bonding portion of each composite filament being thermally bonded to other filaments at points of intersection. The material may be a non-woven fabric that contains at least two layers of weft filaments (1, 2, 11, 12) that may be bordered on one or both sides by a layer of warp filaments (3,4, 15, 16). When compared to other open mesh materials, the open mesh material disclosed herein has a superior combination of some or all of high strength, light weight, high dimensional stability, and openness. Also disclosed herein are articles can be made at least in part from the material including L-seam bags (20), form fill and seal (FFS) bags (1020), and multi-substrate bags (2,020). Methods of making those bags also are disclosed.

Abstract: A pre-form and a method of preparing pre-forms are provided. The pre-forms comprise a resin and at least two layers of oriented fiber tows. The pre-forms comprise fiber tows instead of the traditional prepregs to enhance rearranging of resin and/or fibers during subsequent processing as well as provide greater freedom, a price reduction and/or a reduction of waste. The pre-forms may be formed three-dimensionally to enhance coupling to further pre-forms or other structures and/or to enhance shaping of the pre-form to a final three-dimensional shape. The method of preparation of pre-forms involves providing an adhesive between layers of fibers and providing a resin in contact with at least one of the layers of fibers. The resin is preferably provided in a non-continuous layer to allow for removal of gas at least partially in a direction orthogonal to the layers of resin. The pre-forms are suitable for preparation of composite structures like for example spars for wind turbine blades.

Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 10 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: A process for producing a reinforcing-fiber strip substrate having a circular-arc part includes contacting one surface of a strip-shaped, unidirectional reinforcing-fiber substrate formed by arranging a plurality of reinforcing-fiber strands in one direction in parallel with each other with a flexible member; deforming the unidirectional reinforcing-fiber substrate into a circular-arc shape by deforming at least a part of the flexible member into a circular-arc shape in a direction extending along its contact surface with the unidirectional reinforcing-fiber substrate; and thereafter, separating the flexible member from the unidirectional reinforcing-fiber substrate having been deformed.

Abstract: The present invention relates to a fiber having starch and a high polymer, and a web employing such a fiber.

Abstract: A laminated base material includes a lamination and integration of prepreg base materials each of which includes many reinforcing fibers arranged substantially in one direction and a matrix resin adhered to the reinforcing fibers, wherein at least one of the laminated prepreg base materials is formed with a prepreg base material having, throughout its whole surface, many incisions each extending in a direction crossing the reinforcing fibers, substantially all of the reinforcing fibers divided by incisions, and wherein a length L of each of reinforcing fiber segments formed by the incisions is 10 to 100 mm, a thickness H of the prepreg base material is 30 to 300 ?m, and a fiber volume content Vf of the reinforcing fibers is 45 to 65% and arranging directions of the reinforcing fibers between one and another laminated prepreg base materials have at least two directions different each other.

Abstract: The present invention relates to a fibre sheet material and method of laying up fibre sheet material to manufacture wind turbine blades. The invention further comprises a blade manufactured by the method as well a use of such a blade. One aspect relates to an oblong fibre sheet material (26) for wind turbine blades, where a surface layer (14) is having a width, which in the lateral direction is broader than a lateral, unidirectional layer (10), and lengthwise side faces of at least the surface layer is provided with a thinning of a thickness of the layer to obtain favourable joints. Another aspect concerns manufacturing a wind turbine blade shell comprising laying fibre sheet (26) materials in a blade mould (20), where the sheet materials lengthwise are positioned in a direction corresponding to a chordwise direction of a turbine blade direction of the mould and overlapping in a spanwise direction.

Abstract: A plate-shaped carbon fiber-reinforced carbon composite has a longitudinal length-to-widthwise length ratio of more than 1. The carbon fiber-reinforced carbon composite is such that at least two layers that are a first carbon fiber-reinforced carbon composite layer in which carbon fibers are placed in the carbonaceous matrix and are oriented in the longitudinal direction and a second carbon fiber-reinforced carbon composite layer different in the arrangement of the carbon fibers from the first carbon fiber-reinforced carbon composite layer are stacked, the first carbon fiber-reinforced carbon composite layer forms an outermost layer of at least one plate surface, the thickness thereof is 70% or more of the thickness of the carbon fiber-reinforced carbon composite, and the longitudinal bending elastic modulus is 150 GPa or more.

Abstract: A fiber-reinforced composite material (11) is constructed by laminating a plurality of fiber bundle layers formed of a reinforced fiber to form a laminated fiber bundle layer and further impregnating the laminated fiber bundle layer with a matrix. At either side of a neutral surface (16), the number of +? layers which are fiber bundle layers having a fiber orientation angle of +? and the number of ?? layers which are fiber bundle layers having a fiber orientation angle of ?? are the same, the order of laminating the fiber bundle layers is inversely symmetrical with respect to the standard surface, and the number of other fiber bundle layers disposed between the +? and ?? layers at either side of the standard surface is the same.

Abstract: Certain embodiments described herein are directed to composite materials comprising untwisted fibers. In some embodiments, the article can include a core layer comprising a thermoplastic polymer and reinforcing fibers. In other embodiments, untwisted fibers can be disposed on the core layer. In certain examples, the article is effective to provide a Class A finish when painted.

Abstract: A composite laminate, method of forming same, and use for same are disclosed. One example of a composite laminate has multiple layers or plies (305A-305E) composed of generally parallel reinforcing fibers (315A-315E) embedded in a matrix (305M). The reinforcing fibers have orientations in the ranges of 3 to 8 degrees, ?3 to ?8 degrees, 10 to 40 degrees, ?10 to ?40 degrees, and approximately 90 degrees, the orientations being with respect to a predetermined axis (320), such as an axis of tension (T). A method of manufacturing a composite laminate includes laying a resin and fibers having these orientations and then curing the resulting laminate. One example of a use is for the skin on the fuselage or wing of an aircraft.

Abstract: The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 80 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most of or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 and the stack further comprises a plurality of plies having fibres substantially in the same direction 811 as the longitudinally direction L of the article 801 and/or a plurality of plies having fibres in the diagonal direction (812, 813, 815, 816, 817, 818) of the longitudinal direction (L) of the article (801), wherein at least one of the ply/plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 comprise fibres that are stiffer than the fibres in the other plies which have less stiff fibres.

Abstract: A connection is between a monolithic metal component and a continuous-fiber reinforced laminate component wherein the metal component and the laminate component are joined at the ends thereof. A method allows for the production of the connection between the monolithic metal component and the continuous-fiber reinforced laminate component.

Abstract: An aerospace vehicle includes a plurality of composite stiffeners. Each stiffener of the plurality has a stack of plies of reinforcing fibers. At least some of the plies in the stack have reinforcing fibers oriented at ±? with respect to an axis of primary loading, where ? is between 2 and 12 degrees. At least some of the plies in the stack have reinforcing fibers oriented at ±? with respect to the axis of primary loading, where ? is between 50 and 85 degrees.

Abstract: A composite laminate comprises a plurality of composite plies including at least a first composite ply and a second composite ply. The first composite ply and the second composite ply each comprises a plurality of fibers in a thermoplastic matrix comprising polyethylene. The plurality of composite plies are bonded together to form the composite laminate.

Abstract: This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.

Abstract: A stringer made of composite material for reinforcing aircraft skin panels. Plies are introduced at 90° in a segment close to the stringer run-out, and progressively reducing the number of plies at 0°, such that the majority of the number of plies is at 90° in an segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. This is an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing both the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. A method of manufacturing said stringer is also provided.

Abstract: A thermal interface material (1) comprises a bulk polymer (2) within which is embedded sub-micron (c. 200 to 220 nm) composite material wires (3) having Ag and carbon nanotubes (“CNTs”) 4. The CNTs are embedded in the axial direction and have diameters in the range of 9.5 to 10 nm and have a length of about 0.7 ?m. In general the pore diameter can be in the range of 40 to 1200 nm. The material (1) has particularly good thermal conductivity because the wires (3) give excellent directionality to the nanotubes (4)—providing very low resistance heat transfer paths. The TIM is best suited for use between semiconductor devices (e.g. power semiconductor chip) and any type of thermal management systems for efficient removal of heat from the device.

Abstract: Doctor blade material, which is composed of a number of layers that are connected to each other and include at least a frame layer. The frame layer, includes outer layers on both sides and is constructed of carbon fiber and/or mineral fiber, e.g. glass fiber, basalt fiber, et cetera. The outer layers include carbon fiber. The outer layer is a compact-multiaxial layer composed of a surface layer containing carbon fiber and of two or more support layers. The surface layer includes carbon fibers that are at a 90° angle with respect to the longitudinal direction of the doctor blade, wherein the fibers in the first support layer following the surface layer are at an angle between (?70°)-(?20°) or (+20°)-(+70°) with respect to the fibers of the surface layer. The fibers in the second support layer following this are at an angle between (+20°)-(+70°) or (?70°)-(?20°) with respect to the fibers of the surface layer.

Abstract: Disclosed herein is a wood plastic composite panel made of a resin composite in which wood fiber having a size of 80 to 300 meshes is included in a synthetic resin matrix, the wood plastic composite panel being provided at the entire surface thereof with an embossed structure of a lumber cut-open pattern having an average depth of 200 to 900 ?m and a linear micro concavo-convex structure having an average depth of 10 to 500 ?m, the panel having a reflection rate of 10 to 50% when light is incident on the surface of the panel at an incidence angle of 60 degrees. The wood plastic composite panel according to the present invention has excellent strength and durability. Furthermore, the wood plastic composite panel according to the present invention exhibits excellent appearance and texture comparable with cut-open surfaces of natural lumbers although the panel has a surface structure different from the cut-open surfaces of the natural lumbers.

Abstract: A porous web for filtering fluids has a plurality of adjacent layers of fiber material having anisotropic properties. The anisotropic directions of a given vectorial property of at least two adjacent layers differ one from the other by an angle greater than 0°, and preferably of at least 8°. The porous web is particularly useful as a filter element for the filtration of biological fluids, such as blood and blood components.

Abstract: Ballistic resistant composites having improved durability. More particularly ballistic resistant composites including a protective thermoplastic overlay that enhances composite abrasion resistance while also permitting exploitation of the properties of an underlying binder system.

Abstract: An in situ compositionally modulated meltspun fabric and method for making the same. The meltspun fabric has at least one layer comprising a plurality of discrete regions of fiber. At least two discrete regions of fiber are inelastic or extensible and at least one discrete region of fiber is elastic or extensible. The layer is compositionally modulated in the cross direction.

Abstract: A cross arm is provided, for use in a support structure for conductors within an electrical grid. The cross arm is made of weather resistant glass fiber reinforced two component polyurethane based polymers and has a “C” cross sectional shape typically arranged in a double configuration. Pairs of the cross arms are attached to utility poles in a parallel position on opposite sides of the utility pole to meet predefined design conditions. Alternatively, a single cross arm may be attached to a utility pole.

Abstract: Material composites are provided that have improved shock and impact resistance.

Abstract: Methods for fabricating sub-lithographic, nanoscale microstructures in one-dimensional arrays utilizing self-assembling block copolymers, and films and devices formed from these methods are provided.

Abstract: The present invention relates to an EMF-screened plastic-organic sheet hybrid structural component, preferably a battery housing, and to its use in motor vehicles, preferably in electrically powered motor vehicles or hybrid motor vehicles, the abbreviation EMF meaning electromagnetic field(s).

Abstract: A method of manufacturing a multi-axial laminate of webs produced from cables stretch broken into strips includes arranging, at an entry of a conveyor table, a first layer of pre-wound pre-cut strips along the longitudinal axis of the table, the strips being partially superimposed; arranging along the table at least two cross lappers transferring and depositing in an oblique and/or divergent position at predetermined angles a stretch broken strip; and arranging the strips in successive superimpositions on the first layer of pre-cut strips in different planes, to form a multi-axial web of stretch broken strips. The web then being treated by a fixing device. Movement of the support belt of the table taking place in steps to ensure the superimposition of the different layers of pre-broken strips deposited by the cross lappers. Implementation of the method taking place without any prior cohesion treatment of each strip.