Abstract: A heart valve is at least partially constructed from a block-copolymer, the block-copolymer having a phase structure formed by its constituent blocks, and wherein the phase structure is arranged so as to produce anisotropic physical properties in the heart valve.

Abstract: The present invention discloses an assembled bamboo sleeper, which is obtained by using a bamboo unit as a raw material, dried and modified at the temperature of 110-180° C., undergone coating treatment using a dopamine solution, adhesive dipping, curing and solidifying, assembling and gluing, further solidifying, further treatment using a dopamine solution, and anti-mildew and/or anti-corrosion and/or anti-insect treatment, and then fastened. The present invention further provides a preparation method for the foregoing bamboo sleeper. The bamboo sleeper prepared in the present invention is green and environmentally friendly, and applicable for ballasted tracks of railways and urban rail transit systems.

Abstract: An artificial gravity heating system includes a cylindrical compartment formed of a hollow cylinder having a bottom base and an open top end. An electric motor rotates the cylindrical compartment to provide centripetal motion of materials inside the cylindrical compartment. While rotating, the materials move towards an inner wall of the cylindrical compartment. A heating element is conductively coupled along an outer wall of the cylindrical compartment for heating the materials against the inner wall via conduction. A temperature sensor is operatively coupled to the cylindrical compartment for monitoring a temperature of the cylindrical compartment. A controller is configured to control operation of the heating element based on the temperature monitored via the temperature sensor. An artificial gravity heating method is used to process materials including heating ingredients to cook food. The artificial gravity heating system may also be configured as a vapor generator dehydrator or a thermal gas generator.

Abstract: A grass trimming head includes a housing assembly and a spool. The housing assembly is formed with a housing cavity and an outer aperture for allowing a cutting line to be inserted from an outside of the housing assembly into the housing cavity. At least a portion of the spool is arranged inside the housing cavity, and the spool is rotatable with respect to the housing assembly about a central axis. The spool is formed with an inner aperture for allowing the cutting line to be inserted into the spool or a clamping portion configured to fix the cutting line.

Abstract: A process for additive manufacturing of a thermoset resin fiber reinforced composite comprises depositing a fiber material along a path having a direction; heating the fiber material using a heater to generate a moving thermal gradient in the fiber material trailing the heater relative to the path direction; and dispensing a thermosetting polymer material on the heated fiber material at a trailing distance the from the heater along the path. The thermosetting polymer dynamically wicks into the fiber material along the thermal gradient in the path direction.

Abstract: According to exemplary inventive practice, a personal armor system includes a textile-based layer not exceeding ½-half-inch thickness, and an elastomeric coating not exceeding ?-inch thickness. The textile-based layer includes a fiber reinforcement and a resin binder. The combined areal density of the textile-based layer and the elastomeric coating does not exceed 2.5 psf. According to a first mode of inventive practice, the elastomeric coating is essentially a strain-rate-sensitivity-hardening elastomer, and the areal density of the textile-based layer does not exceed 2.3 psf. According to a second mode of inventive practice, the elastomeric coating is essentially a microparticle-filled strain-rate-sensitivity-hardening elastomeric matrix material, and the areal density of the textile-based layer does not exceed 1.7 psf. The microparticles (e.g., spherical glass microparticles) do not exceed, by weight, 30 percent of the strain-rate-sensitivity-hardening elastomeric matrix material.

Abstract: A method of evaluating a composite sample comprises providing a flatbed scanner comprising a scanning head movable along a scanning direction; providing a composite sample comprising a plurality of plies arranged on planes parallel to a longitudinal direction and comprising a scanning plane containing ply edges, wherein the ply edges are oriented parallel to the longitudinal direction; arranging the composite sample on the flatbed scanner such that the scanning plane is parallel to the scanning direction and the ply edges of the scanning plane are perpendicular to the scanning direction; moving the scanning head along the scanning direction and perpendicularly to the ply edges to scan the scanning plane of the composite sample and obtain an image of the scanning plane; and evaluating the image to identify possible defects in the composite sample.

Abstract: A gas-diffusing device, including a superposition of a layer of composite material including electrically conductive fibres and a polymerized resin coating said conductive fibres; a first electrically conductive layer having an open porosity between first and second faces and including a first void in the second face, the first face making electrical contact with the conductive fibres of the layer of composite material, the polymerized resin coating one portion of the first conductive layer on the first face.

Abstract: The present invention relates to a fastening structure of a composite material structure, and more particularly, to a composite material stitching structure reinforced with z-direction fiber which improves strength in a lamination direction of a relatively weak composite material structure, for a composite material structure, in which composite materials are laminated and bonded.

Abstract: Processes for making high-performance polyethylene multi-filament yarn are disclosed which include the steps of a) making a solution of ultra-high molar mass polyethylene in a solvent; b) spinning of the solution through a spinplate containing at least 5 spinholes into an air-gap to form fluid filaments, while applying a draw ratio DRfluid; c) cooling the fluid filaments to form solvent-containing gel filaments; d) removing at least partly the solvent from the filaments; and e) drawing the filaments in at least one step before, during and/or after said solvent removing, while applying a draw ratio DRsolid of at least 4, wherein in step b) each spinhole comprises a contraction zone of specific dimension and a downstream zone of diameter Dn and length Dn with Ln/Dn of from 0 to at most 25, to result in a draw ratio DRfluid=DRsp*DRag of at least 150, wherein DRsp is the draw ratio in the spinholes and DRag is the draw ratio in the air-gap, with DRsp being greater than 1 and DRag at least 1.

Abstract: Provided is a method of forming a customized alveolar bone tissue. The method includes obtaining first data having image information corresponding to an original alveolar bone of an alveolar bone defect, obtaining second data having image information on a defective portion of the alveolar bone defect, calculating third data having image information on a barrier membrane covering the alveolar bone defect by using the first data and the second data, and forming a barrier membrane artificial tissue corresponding to the barrier membrane by using the third data.

Abstract: According to exemplary inventive practice, a personal armor system includes a textile-based layer not exceeding ½-half-inch thickness, and an elastomeric coating not exceeding ?-inch thickness. The textile-based layer includes a fiber reinforcement and a resin binder. The combined areal density of the textile-based layer and the elastomeric coating does not exceed 2.5 psf. According to a first mode of inventive practice, the elastomeric coating is essentially a strain-rate-sensitivity-hardening elastomer, and the areal density of the textile-based layer does not exceed 2.3 psf. According to a second mode of inventive practice, the elastomeric coating is essentially a microparticle-filled strain-rate-sensitivity-hardening elastomeric matrix material, and the areal density of the textile-based layer does not exceed 1.7 psf. The microparticles (e.g., spherical glass microparticles) do not exceed, by weight, 30 percent of the strain-rate-sensitivity-hardening elastomeric matrix material.

Abstract: A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

Abstract: A lock fastener that can be easily manufactured to have great fastening ability includes a touch fastener and a base member insert-molded to the touch fastener. The base member is formed with a space adapted to be filled with a resin material at a time of insert-molding, and the space includes an opening formed in a surface of the base member. The opening is surrounded by a peripheral wall part of the surface. The peripheral wall part is adapted to abut a base of the touch fastener at the time of insert molding and to serve as a bank for preventing the resin material filled into the space from leaking.

Abstract: Composition of a composite material for containers, method of the preparation thereof and its use. The composition comprises a continuous matrix of a thermoplastic polymer having a melting point higher than 110° C. and, distributed within the matrix, non-fibrillated wood particles having a sieved size greater than 1.0 mm. The weight ratio of thermoplastic polymer to wood particles being 45:55 to 80:20. Material further contains 0.1 to 10% by weight, calculated from the total weight of the thermoplastic polymer and the wood particles, of a slate-like mineral pigment. The material is particularly suitable for containers of cosmetic products, for foodstuff and for beverages.

Abstract: Processes for making high-performance polyethylene multi-filament yarn are disclosed which include the steps of a) making a solution of ultra-high molar mass polyethylene in a solvent; b) spinning of the solution through a spinplate containing at least 5 spinholes into an air-gap to form fluid filaments, while applying a draw ratio DRfluid; c) cooling the fluid filaments to form solvent-containing gel filaments; d) removing at least partly the solvent from the filaments; and e) drawing the filaments in at least one step before, during and/or after said solvent removing, while applying a draw ratio DRsolid of at least 4, wherein in step b) each spinhole comprises a contraction zone of specific dimension and a downstream zone of diameter Dn and length Dn with Ln/Dn of from 0 to at most 25, to result in a draw ratio DRfluid=DRsp*DRag of at least 150, wherein DRsp is the draw ratio in the spinholes and DRag is the draw ratio in the air-gap, with DRsp being greater than 1 and DRag at least 1.

Abstract: Described herein are hard armor plate comprising a first molded plate of a plurality of ballistic fibers, a second molded plate of a plurality of ballistic fibers, and a layer of ceramic tiles adhered to the first molded plate and the second molded plate, wherein the layer of ceramic tiles is between the first molded plate and the second molded plate; and methods of making hard armor plates.

Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

Abstract: This document describes a reinforced graphite heat-spreader for a surface of a housing component of an electronic device. The reinforced graphite heat-spreader includes a heat-spreader material stack having a layer of graphite material to spread heat. The reinforced graphite heat-spreader also includes an interface material stack that joins the heat-spreader material stack to the housing surface of an electronic device. The interface material stack, which may be formed using embossing techniques, includes protuberances that may be formed from an adhesive material.

Abstract: Composite panel comprising at least one layer containing at least one tape comprising a thermoplastic polymer selected from the group consisting of polyolefins, polyesters, polyvinyl alcohols, polyacrylonitriles, polyamides or polyketone, wherein the tape has a tensile strength of at least 1.2 GPa and an areal density of between 5 and 150 g/m2, and an adhesive in contact with said layer, whereby the amount of the adhesive in contact with one side of the at least one layer is between 0.2 and 15 g/m2, wherein the adhesive is a plastomer wherein said plastomer is a random copolymer of ethylene or propylene and one or more C2 to C12 a-olefin co-monomers and wherein said plastomer has a density as measured according to 1801183 of between 860 and 930 kg/m3. In a preferred embodiment the tape comprises an ultra high molecular weight polyethylene. The composite panel is used in a ballistic resistant article.

Abstract: A washable nano-stratified encapsulation barrier is provided. The washable nano-stratified encapsulation barrier includes a stratified inorganic layer including an aluminum oxide layer, and a silica-polymer layer provided in direct contact with the aluminum oxide layer and having silicon (Si)-oxygen (O) bond. An electronic device is provided. The electronic device comprises a substrate; the washable nano-stratified encapsulation barrier and provided on the substrate; and an organic electronic device provided on the substrate.

Abstract: A laminate comprising a first ply, a second ply, and a third ply which sandwiching the second ply between the first ply and the third ply. The laminate further includes a first plurality of interfacial modifiers arranged between opposing faces of the first ply and the second ply. The first plurality of interfacial modifiers are arranged in a first pattern. The laminate includes a second plurality of interfacial modifiers arranged between opposing faces of the second ply and the third ply such that the first plurality of interfacial modifiers and the second plurality of interfacial modifiers are arranged on opposite faces of the second ply. The second plurality of interfacial modifiers are arranged in a second pattern. The first pattern and the second pattern are configured to increase crack growth resistance of the laminate by selectively toughening portions of the laminate to control propagation of interfacial cracks within the laminate.

Abstract: Method for seaming a multi-sectional composite tooling for use in molding large composite structures. The tooling includes at least two tooling sections that are made from quasi-isotropic sheet molding compound. The two tooling sections are seamed together with a scarf plug at the tooling surface. The scarf plug is composed of specially oriented layers of consolidated quasi-isotropic sheet molding compound. The scarf plug is made from the same type of quasi-isotropic sheet molding compound that is used to make the tooling sections.

Abstract: Embossed fibrous structures containing a plurality of filaments and methods for making same are provided.

Abstract: A floating platform for a wave energy converter (WEC), comprising a hollow body, in which energy converting machinery may be positioned, characterised in that the floating platform has an underside facing the water in use, an upper side facing the opposite direction and a first long-side forming a front and a second long-side forming a back, and two short-sides, wherein at least one aligning means is provided, the aligning means is configured to align the front of the floating platform with the wave front, i.e. perpendicular to the direction of the wave, wherein the front of the floating platform is at least 20 m long.

Abstract: A lining plate having an outer decorative layer, a support layer having at least magnesium oxide or magnesium oxide with perlite and/or vermiculite and/or cellulose, a barrier membrane to reduce or avoid water and moisture intrusion, and a self-adhesive foam material layer with an adhesive surface to be placed on a surface to be lined, the layer being provided with a plurality of perforations. The support layer has a non-homogeneous density in its thickness, distinguishing a first thickness, following the decorative layer, and a second thickness, between the first thickness and the barrier membrane, in which the density in the first thickness is greater than the density in the second thickness. The support layer is provided with a reinforcing structure formed by meshes or by a fabric of a composite material located within the second thickness of the support layer.

Abstract: Systems for manufacturing a composite extruded product formed of a substrate and a film. The system includes an extruder, a film application section for integrally bonding the film to the substrate, a heating section for increasing the temperature of the composite extruded product, an embosser for embossing a pattern into the composite extruded product, and a cooling section for cooling the composite extruded product. The cooling section applies pressure to the composite extruded product and sprays cooling fluid onto the composite extruded product such that the composite extruded product is cooled and the pattern embossed into the first surface is permanently set.

Abstract: A wheel suspension link including a structure connection location for connecting the link to a vehicle structure and a wheel carrier connection location connecting the link to a wheel carrier. The structure connection location and wheel carrier connection location arranged on a link member extending along a link plane. The link member including a base member formed in a materially integral manner from a discontinuously reinforced plastic material. The link member including a reinforcement, containing continuous fibers, connected to the reinforced plastic material. In one embodiment, the reinforcement limited with respect to the link plane to a first region of the link member while the base member extends into a second region.

Abstract: An interleaved layer construction of a composite panel and a composite plank constructed of three sub-planks that are adhered together and secured to the panel stiffen and strengthen the panel.

Abstract: Radius fillers for composite structures, composite structures that include the radius fillers, and systems and methods of forming the radius fillers. The systems and methods may be configured to create a pre-form that may be utilized to form a radius filler and/or to create a radius filler from the pre-form. The systems may include an apparatus configured to form the pre-form for the radius filler. This apparatus includes a composite tape source, a pre-forming structure, and a drive mechanism. The systems also may include an apparatus configured to form the radius filler. This apparatus includes a pre-form supply, a first radius filler die, a second radius filler die, and a die selection structure.

Abstract: A system is disclosed for additively manufacturing a composite structure. The system may include a print head configured to receive a continuous reinforcement, and at least one of a matrix jet and a matrix bath configured to wet the continuous reinforcement with a liquid matrix during passage through the print head. The system may also include a coating mechanism configured to dispense at least one of metallic and ceramic particles onto the wetted continuous reinforcement during passage through the print head, and at least one cure enhancer configured to at least one of cure the liquid matrix and cause the at least one of metallic and ceramic particles to coalesce around the continuous reinforcement. The system may further include a support configured to move the print head in multiple dimensions during discharging.

Abstract: A medical implant comprising a plurality of biocomposite layers, each layer comprising a polymer and a plurality of uni-directionally aligned continuous reinforcement fibers. The medical implant is suitable for load-bearing orthopedic implant applications and comprises one or more biocomposite materials where sustained mechanical strength and stiffness are critical for proper implant function.

Abstract: The invention relates to ballistic underwear. The base area of the underwear is composed of shrapnel-resistant UHMWPE knitwear 1 and at least one other, different textile material 2, 200, 14. The UHMWPE knitwear is arranged in a first zone of the base area.

Abstract: A hybrid material mat for use in the manufacture of fibre-composite articles, in particular parts for wind turbine blades, is described. The mat comprises a plurality of glass fibre rovings provided on top of a relatively thin planar substrate of carbon fibres. Such a hybrid mat construction provides for an improvement in the structural properties of a component manufactured using the mat, as well as allowing for ease of handling and manufacturing of both the mat itself and the component.

Abstract: A method of manufacturing an elastic composite includes forming a preform from a filler filled one-dimensional elastic structure that contains a filler and a matrix material forming a pattern that provides elasticity to the one-dimensional elastic structure; and forming the elastic composite from the preform via one or more of the following: sintering; compression molding; or hot isostatic pressing.

Abstract: A fiber-reinforced material includes a discontinuous reinforcing fiber aggregate of a discontinuous reinforcing fiber having a number average fiber length of 3 to 100 mm and a matrix resin, the discontinuous reinforcing fiber aggregate including a plurality of discontinuous reinforcing fiber bundles having a predetermined number of unidirectionally-bundled single yarns of the discontinuous reinforcing fiber, wherein the discontinuous reinforcing fiber bundle has a cut surface inclined at a predetermined angle with respect to an orientation direction of the single yarn of the discontinuous reinforcing fiber bundle and has different fiber bundle lengths defined as a distance between both ends along the orientation direction of the single yarn of the discontinuous reinforcing fiber bundle, the shorter the fiber bundle length of the discontinuous reinforcing fiber bundle, the smaller a tip angle defined as an acute angle at an end of a two-dimensional plane projection of the discontinuous reinforcing fiber bundle

Abstract: A method of molding composite materials including shaping a laminate having fiber sheets laminated over one another, by bending the laminate in an X-direction and a Y-direction, in a three-dimensional orthogonal coordinate system. The method further includes mounting the laminate that has been shaped, onto a mold material deformed in a Z-direction, impregnating a resin material into the laminate while adjusting an amount of the resin material filled in, and molding the composite materials that have cured such that the composite materials are shaped to have a first inclined surface inclined at a first inclination angle with respect to a reference plane in the Z-direction. The mold material has a first inclination molding surface that molds the first inclined surface, and a second inclination molding surface that molds a surface of the composite materials into a second inclined surface having a second inclination angle smaller than the first inclination angle.

Abstract: In a nonwoven fabric, uniaxially oriented bodies each including a thermoplastic resin layer and first and second adhesive layers respectively stacked on both surfaces of the thermoplastic resin layer and having melting points lower than that of a thermoplastic resin constituting the thermoplastic resin layer are warp-weft laminated with the first or second adhesive layer interposed between the uniaxially oriented bodies in such a manner that orientation axes thereof intersect each other. The nonwoven fabric has a mass per unit area of 5 to 13 g/m2, a layer composition ratio of the first adhesive layer, the thermoplastic resin layer, and the second adhesive layer in each of the uniaxially oriented bodies is 20/60/20 to 30/40/30, and an average value of bending resistances by a cantilever method is less than or equal to 50 mm.

Abstract: A load-bearing and heat-insulating structural element having a thickness and a planar extension composed of longitudinally cut Typha leaves, which yield rod-shaped Typha leaf particles, wherein the rod-shaped Typha leaf particles are oriented perpendicularly to the thickness of the structural element and are joined among each other by way of bonding, preferably a mineral bonding having no significant non-mineral additives.

Abstract: A sealed attic insulating and roof ventilating system includes a plenum formed in part by a barrier material attached to adjacent pairs of rafters and having a radiant or reflective upper surface and a corrugated lower surface to which an insulation material may be secured. This arrangement creates an uninterrupted air chamber or ventilation plenum between the barrier material, the adjacent rafters, and the roof decking through which exterior air can circulate unimpeded from the lower vents to the upper vents of the roof. The circulation through the ventilation plenum prevents moisture from accumulating or condensing under the roof decking and warping the roof decking, which ultimately leads to deterioration of the roof decking and failure of the roof covering, and eliminates ice damming on the top surface of the roof covering.

Abstract: A mesh nonwoven fabric which is seamless and excellent in appearance is provided. A seamless mesh nonwoven fabric is prepared by laminating a first mesh film 20 containing stem fibers 20a stretching parallel to each other in a first direction and branch fibers 20b connecting adjacent stem fibers 20a together, and a second mesh film 30 containing stem fibers 30a stretching parallel to each other in a second direction intersecting the first direction and branch fibers 30b connecting adjacent stem fibers 30a.

Abstract: Provided are assemblies, each including a first structure having a uniform coefficient of thermal expansion (CTE) and a second composite structure having a variable CTE. Also provided are methods of forming such assemblies. The second structure has overlap, transition, and baseline regions. The overlap region directly interfaces the first structure and has a CTE comparable to that of the first structure. The baseline region is away from the first structure and has a different CTE. Each of these CTEs may be uniform in its respective region. The transition region may interconnect the baseline and overlap regions and may have gradual CTE change from one end to the other. The CTE variation with the second composite structure may be achieved by changing fiber angles in at least one ply extending through all three regions. For example, any of the plies may be subjected to fiber steering.

Abstract: A method of curing a composite layup may include applying an inner bag vacuum pressure to an inner bag chamber and an outer vacuum pressure to an outer vacuum chamber. The vacuum inner bag chamber may be formed by a vacuum bag covering a composite layup and sealed to a forming tool with an inner bag chamber seal. The inner bag vacuum pressure may be no less than the outer vacuum pressure. The temperature of the composite layup may be increased to an elevated temperature to initiate a temperature hold period. The method may additionally include venting the outer vacuum chamber to atmosphere to initiate an outer vacuum chamber venting period during the temperature hold period, and applying compaction pressure to the inner bag chamber seal during the outer vacuum chamber venting period. The outer vacuum pressure may be re-applied to the outer vacuum chamber to terminate the outer vacuum chamber venting period.

Abstract: Provided is a lightweight mesh nonwoven fabric having excellent adhesiveness between uniaxially oriented bodies, excellent low-temperature heat sealability, and high strength. A mesh structure 1 includes two or more uniaxially oriented bodies 2, 3; which include a thermoplastic resin layer and a linear low-density polyethylene layer laminated on at least one side of the thermoplastic resin layer; the mesh structure is produced by laminating or weaving the uniaxially oriented bodies through the linear low-density polyethylene layer in such a way that orientation axes L, T of the uniaxially oriented bodies cross; and the mesh structure has properties of: (1) a fiber weight per unit area of 5 to 70 g/m2, (2) a thickness of the linear low-density polyethylene layer of 2 to 10 ?m, (3) an adhesive force between the uniaxially oriented bodies of 10 to 60 N, and (4) a tensile strength of 20 to 600 N/50mm.

Abstract: A light-weight structural panel is formed by pultruding a closed-cell foam core embedded with high-strength reinforcing pins through a pair of heated platens along with upper and lower sheets of woven fiber glass wetted by a polymer resin. The lengths of the reinforcing pins exceeds the thickness of the core so the platens compress the skin sheets forming pockets which accumulate excess resin that, when it cures, forms a more stable panel.

Abstract: Systems and methods are provided for integrating structural components of a wing box. One embodiment is a system that includes outboard planked stringers within an outboard section of a wing box and are co-cured with composite skin at the outboard section. Each outboard planked stringer of the outboard section includes planar layers of Carbon Fiber Reinforced Polymer (CFRP) that are parallel with the composite skin at the outboard section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the composite skin at the outboard section. The system also includes center planked stringers within the center section and are co-cured with composite skin at the center section.

Abstract: A composite laminate is presented. The composite laminate comprises a plurality of plies having non-traditional angles. Each of the plurality of plies has a respective shape configured to minimize a total length of the ply boundary over all of the plurality of plies. The composite laminate has a stiffness equal to a desired stiffness of a traditional composite laminate.

Abstract: A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

Abstract: A flooring assembly (10) comprising at least one vertically lapped fibrous material layer (14), at least one pressure sensitive adhesive layer (12a) including a flexible substrate (12b), a mesh (12c) and an adhesive (12d) located along the flexible substrate, and at least one moisture impermeable membrane layer (16).

Abstract: A bamboo composite material for structural applications and method of fabricating the same are provided. The method can comprise the steps of providing a bamboo culm; separating a slice or sheet from the bamboo culm such that the slice or sheet has a longitudinal axis along a fiber direction of the bamboo culm; at least partially detaching individual fiber bundles of the slice or sheet from each other along the longitudinal axis of the slice or sheet; applying a glue to the slice or sheet; and curing the glued slice or sheet.