Abstract: A fiber-reinforced resin material includes: a first fiber-reinforced resin layer; a second fiber-reinforced resin layer having higher ductility and lower elasticity than those of the first fiber-reinforced resin layer; and a third fiber-reinforced resin layer having higher ductility and lower elasticity than those of the second fiber-reinforced resin layer. The first layer, the second layer, and the third layer are laminated and integrated in this order, wherein the laminate is made of the fiber-reinforced resin material. The manufacturing method includes: stacking a sheet-shaped product obtained by forming continuous fibers into a sheet shape and a resin sheet that serves as a first thermoplastic resin, a second thermoplastic resin, or a third thermoplastic resin so as to obtain a laminated structure in which the first layer, the second layer, and the third layer are laminated in this order; and heating and compressing the obtained stacked product in a stacking direction.

Abstract: This invention relates to a washable multi-component magnetic floor mat. The floor mat contains a textile component and a base component. The textile component and the base component are attached to one another by magnetic attraction. The magnetic attraction is provided by incorporation of magnetic particles in both the textile and base components. The textile component is designed to be soiled, washed, and re-used, thereby providing ideal end-use applications in areas such as building entryways. The present invention eliminates the need to wash the base component of the floor mat which results in environmental, cost and labor conservation. Alignment and deployment of the textile component with the base component in an efficient manner is also described herein.

Abstract: A method used for forming ceramic matrix composite components includes several steps. The method comprises arranging a layup of a predetermined number of prepreg ceramic plies on a layup too and a plurality of different stages to debulk and consolidate the layup.

Abstract: An aircraft structure (such as a T-shaped structure, a convex structure, a curved structure, or the like) includes: a laminated structure including composite-material layers that are laminated; and wherein the composite material aircraft structure is a three-dimensional structure that includes at least one of a standing structure, a convex structure, or a curved structure. The composite-material layers include at least a composite-material layer in which a reinforced fiber is a single continuous fiber, wherein the single continuous fiber includes a partial slit region. When a thickness of a flat-plate formed body including a same laminated structure as the aircraft structure but not including the three-dimensional structure, is defined as a reference thickness, the aircraft structure includes a thin plate region which has a thickness that is smaller than the reference thickness while maintaining the laminated structure.

Abstract: A structural component, comprising at least two organo-sheet pieces which at least sectionally lie one on top of the other and which each include a fiber layer, wherein at least in the fiber layers of the organo-sheet pieces at least one pair of mutually aligned holes is formed, at which the organo-sheet pieces are positively connected to each other. There is furthermore proposed a method for manufacturing a structural component.

Abstract: A roller including: a main body portion configured to include an outer ring and a rotatable inner ring on an inner circumferential side of the outer ring; and a covering portion disposed on an outer circumferential surface of the outer ring, the covering portion being made of a synthetic resin in which reinforced fibers are dispersed, wherein the covering portion includes a region in which arrangement directions of the reinforced fibers are aligned.

Abstract: In accordance with at least one aspect of this disclosure, a composite structure can be formed of or including a plurality of composite strips. The plurality of composite strips include one or more filler strips which can have at least one filler edge having a filler edge geometry between a first surface and second surface, the second surface being opposite the first surface. The filler edge geometry can be configured to prevent formation of one or more gaps between one or more adjacent composite strips.

Abstract: Underwater Deployable Structures (UDSs) capable of achieving inflation via mechanical pumps, moisture-activated expanding foams, water swelling material, or a hybrid of a mechanical pump and water swelling material. Moisture expanding foams begin as polyurethane-based resins of low viscosity, and react in the presence of water to become solid foam. In their final forms, the foams exist as open- or closed-cell, and vary in strength, elasticity, and rigidity. Water swelling material is also disclosed wherein the water swelling material is capable of achieving expansion numerous (e.g., up to about 250) times its initial volume when in contact with water and can shrink back to its initial volume upon dehydration, making the UDSs reusable. A mechanical pump may optionally be used to assist in initial inflation until the water swelling material reaches full expansion.

Abstract: The present invention relates to a structure for producing ballistic protection which combines high levels of performance in terms of stopping bullets and reducing trauma with great flexibility and breathability. A ballistic laminate comprising joined together unidirectional layers is produced. The ballistic laminate provided by the present invention is preferably produced by superposing at least two layers of ballistic yarns 101 and 103, arranged unidirectionally according to directions inclined relative to one another by approximately 90° (+/?10°). Each layer comprises a plurality of fibres arranged unidirectionally according to a substantially mutually parallel direction (+/?10°).

Abstract: Provided is a welding method including: a sheet disposition process of disposing a first and a second protection sheet such that the first and the second protection sheet come into contact with a first and a second composite material and disposing an energization sheet such that the energization sheet comes into contact with the first and the second protection sheet; and a welding process of applying a voltage to a pair of electrode portions disposed at the energization sheet and welding the first and the second composite material, the energization sheet contains the carbon fiber base material oriented in a first predetermined direction connecting the pair of electrode portions, and the first and the second protection sheet contain the carbon fiber base material oriented in a second predetermined direction that substantially perpendicularly intersects the first predetermined direction.

Abstract: Method and apparatus for splaying fibers for the forming preform charges for the production of composite discs, and for the production of composite disc, wherein rotary compaction is applied to an appropriately arranged assemblage of preforms.

Abstract: A mooring buoy includes a cylindrical structural shell. The cylindrical structural shell includes fiberglass reinforced plastic (FRP) and has a first open end and an opposite second open end. A plurality of annular stiffeners are bonded to an inside of the cylindrical structural shell. A first endcap is disposed on the first open end of the cylindrical structural shell. The first endcap is configured to substantially cover the first open end. A second endcap is disposed on the second open end of the cylindrical structural shell. The second endcap is configured to substantially cover the second open end. At least one cylindrical attachment mechanism is coupled to an outside of the cylindrical structural shell. The cylindrical attachment mechanism is configured to attach mooring lines to the cylindrical structural shell.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.

Abstract: An apparatus for resisting a gravity load is disclosed. The apparatus has a first end member, a second end member, and a plurality of elongated structural members, each of the plurality of elongated structural members including a first end portion attached to the first end member and a second end portion attached to the second end member. The plurality of elongated structural members is oriented to resist compressive stresses or tensile stresses induced by the gravity load. The plurality of elongated structural members is formed from plants with a harvest cycle of four years or fewer.

Abstract: A method of forming a part includes forming a glass-ceramic matrix composite material to form a pre-consolidated feedstock sheet with a pre-determined shape. The pre-consolidated feedstock sheet is sectioned into a first piece of pre-consolidated feedstock sheet and a second piece of pre-consolidated feedstock sheet. The first piece of pre-consolidated feedstock sheet and a second piece of pre-consolidated feedstock sheet are assembled with a second piece of pre-consolidated feedstock sheet to form a composite layup. The first piece of pre-consolidated feedstock sheet and the second piece of pre-consolidated feedstock sheet are joined by compressing the composite layup to form a glass-ceramic matrix composite part.

Abstract: Systems and methods for making and/or using a hybrid laminate composite tube structure. The methods comprise: wrapping a plurality of lamina layers around a male cylindrical tool (e.g., mandrel); treating the lamina layers with heat/pressure to form the hybrid laminate composite tube structure; and assembling a structure by adhesively bonding the hybrid laminate composite tube structure to a metallic fitting. The lamina layers comprise: at least one first lamina layer formed of a first material having a first CTE; and at least one second lamina layer formed of a second material different from the first material and having a second CTE different than the first CTE. The hybrid laminate composite tube structure has at least one property that is different in the axial direction than the hoop direction. An axial CTE of the hybrid laminate composite tube structure is tailored to provide a net zero CTE for the assembled structure.

Abstract: A method includes laminating a plurality of fiber reinforced sheets to create a charge; and shaping, by pressing, the charge created in the lamination step into a shaping mold. The charge has a predetermined angle layer including the plurality of fiber reinforced sheets, the fiber direction of which is aligned in a single direction. The predetermined angle layer has n-number of constitutional layers (n?2) ranging from a first constitutional layer to an n-th constitutional layer each including the plurality of fiber reinforced sheets, wherein the n-th constitutional layer is laminated on an (n?1)-th constitutional layer, the plurality of fiber reinforced sheets in each of the constitutional layers have dividing portions which are along the fiber direction and which are disposed one by one at respective positions within a predetermined range along the fiber direction in the predetermined angle layer.

Abstract: A composite charge used to compression form a stringer comprises multiple plies of unidirectional, prepreg having various fiber orientations. Certain of the plies have a pattern of angled cuts allowing the plies to stretch both longitudinally and transversely during forming, thereby reducing ply wrinkling in contoured areas of the stringer.

Abstract: Systems and methods for protecting an aerodynamic structure, e.g., a wind turbine blade, rotor blade, aerodynamic aerostructure, etc., are provided. Long fiber reinforced composites having a helicoidal architecture with material aligned with a graded hardness and stiffness are used to develop an efficient and highly tailorable leading edge protection (LEP) solution with longer durability than conventional solutions while yielding lighter, and optionally, more environmentally sustainable solutions. At least a portion of the plurality of plies are helicoidally arranged relative to one another to tailor stress wave propagation speed of the aerodynamic blade and to provide load carrying strength for the aerodynamic blade.

Abstract: A blade is provided. The blade comprises a plurality of a first composite fiber plies and a plurality of a second composite fiber plies. Ends of the second fiber plies are staggered such that interlock between the first composite fiber plies and the second composite fiber plies is formed in a region where the second composite fiber plies end and meet with the first composite fiber plies. The blades are used for an engine of an aircraft.

Abstract: A method and apparatus for forming a radius filler. A lattice is formed of connecting elongate members having a three-dimensional shape of the radius filler. A resin is placed within the lattice.

Abstract: The invention relates to a method for manufacturing a nonwoven fabric having an air permeability of 2000 l/m2/s or less when measured at a pressure difference of 200 Pa according to EN ISO 9237, the method comprising the steps of: providing at least two sets of fibers, wherein a first fiber set comprises a significant level of splittable fibers and a second fiber set comprises a low level of splittable fibers or no splittable fibers; using the first fiber set to form at least one first fibrous web in a first web formation process and using the second fiber set to form at least one second fibrous web in a second web formation process; stacking the first and second webs so obtained to provide a multilayer web including two distinct layers of fibrous webs; and bonding the multilayer web. The invention further relates to a nonwoven fabric obtainable by such process and the use of such nonwoven fabric in acoustic isolation applications.

Abstract: A morphing airfoil includes a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. A plurality of standoff mounts is attached to an inner surface of anisotropic skin. The standoff mounts include through apertures for receiving a flexible stringer. The anisotropic skin is attached to underlying structure through the flexible stringers. The flexible stringers interface with actuated position control ribs and passive compliant support ribs. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift and drag distributions along a span of the airfoil without separate control surfaces.

Abstract: A tackified ceramic fabric sheet includes a pre-preg layer having a fabric of woven ceramic tows and a tackifier compound surrounding the tows and comprising 15% to 60% polyvinyl butyral with ethanol. The sheet further includes a removable first backing film layer on a first side of the pre-preg layer.

Abstract: Disclosed are curable polymer compositions, elastomers thereof and release layers useful in the art of printing made of the disclosed elastomers. Disclosed are also intermediate transfer members having a release layer useful in the art of printing. Disclosed are anisotropic intermediate transfer members. Disclosed are curable adhesive compositions, that in some embodiments are useful in preparing intermediate transfer members useful in printing. Also disclosed are intermediate transfer members useful in the art of printing having a release layer with an image transfer surface having protonatable functional groups apparent thereupon. Also disclosed are methods of making such intermediate transfer members.

Abstract: A method for binding photovoltaic cells to a substrate, each photovoltaic cell comprising a rear face and a front face, comprises: providing the substrate, said substrate being flexible and impregnable; impregnating portions of the substrate with a crosslinkable polymer material, said portions being impregnated along the thickness of the substrate, with a view to bonding the photovoltaic cells to the substrate; bringing the rear faces of the photovoltaic cells into contact with the impregnated portions of the substrate; crosslinking the crosslinkable polymer material.

Abstract: An object of the present disclosure is to provide a cellulose acetate film having excellent bending properties and high transparency. The subject cellulose acetate film contains cellulose acetate having a cellulose triacetate I crystal structure, the cellulose acetate film having a light transmittance of 70% or higher at 660 nm.

Abstract: Semiconductor assemblies including thermal layers and associated systems and methods are disclosed herein. In some embodiments, the semiconductor assemblies comprise one or more semiconductor devices over a substrate. The substrate includes a thermal layer configured to transfer thermal energy across the substrate. The thermal energy is transferred from the semiconductor device to the graphene layer using one or more thermal connectors.

Abstract: Provided is a prepreg resin composition, containing: a urethane (meth)acrylate (A) that is a reaction product of polyisocyanate (a1), polyol (a2), and hydroxy alkyl (meth)acrylate (a3); a polymerization initiator (B); and a thermoplastic resin (C), as an essential component, in which the polyisocyanate (a1) is at least one polyisocyanate selected from 2,4?-diphenyl methane diisocyanate, 4,4?-diphenyl methane diisocyanate, a carbodiimide modified product of 4,4?-diphenyl methane diisocyanate, and polymethylene polyphenyl polyisocyanate. The prepreg resin composition of the invention is excellent in molding properties, and is capable of forming a molded article excellent in various physical properties such as flexibility, impact resistance, and heat resistance, and thus, can be preferably used in a prepreg and a molded article thereof.

Abstract: Systems and methods for infiltrating porous ceramic matrix composite (CMC) preforms to form CMC articles are disclosed. One method may include positioning the porous CMC preform in an opening of a die set for an infiltration system, and flowing a molten densifier over the porous CMC preform in a first flow direction to infiltrate a plurality of voids formed between each of a plurality of ply stacks of the CMC preform. The method may also include flowing the molten densifier over the porous CMC preform in a second flow direction, distinct from the first flow direction, to infiltrate the plurality of voids formed between each of the plurality of ply stacks of the CMC preform. The second flow direction may be substantially parallel to a predetermined, unidirectional material orientation of at least one ply stack of the plurality of ply stacks of the CMC preform.

Abstract: A method of fabricating a polymer composite material by mixing a polymer material with a planar material, depositing the mixture on a substrate, and stretching the resulting thin film, is described. Polymer composite materials produced using said method and ballistic resistant materials comprising said polymer composite materials are also described.

Abstract: A composite structure, including a laminate that includes a set of plies, the laminate extending between a first edge and a second edge and including a rising ramp and a falling ramp. The rising ramp includes a starting point and an upper point and the falling ramp includes the upper point and an end point. Plies are partially located over their preceding ply and alternatively extend from the first edge or the second edge and are shorter than the ply located before the preceding ply so that their ends are stepped successively until they reach the top of the ramp.

Abstract: A system, apparatus, composition and methods for producing a modular, ultra-thin, ultra-lightweight thermal camouflage, thermal signature mitigation and thermal insulation system. The thermal management system may comprise one or more composite layers or combinations of ultra-thin and ultra-lightweight non-woven stealth coated substrates. Each composite layer may be coated with specific components to create different thermal camouflage through a biomimicry application process of absorbance, reflective, protective layering, thermal signature mitigation, and/or thermal insulation system capabilities. Layers can be combined to enable dynamic stealth camouflage tunable performances of reflectivity, transmission, emissivity, or absorption in selective visible, near infrared, and infrared wavelength bands whereby each substrate has a unique EM wave propagation control or thermal signature mitigation characteristics.

Abstract: The present invention relates to a ball game racket frame with a head portion and a handle portion, wherein the ball game racket frame comprises a fiber composite with at least one multi-fiber roving that is at least partially twisted.

Abstract: A method of forming a fibre article, comprising: providing a former having a contoured forming surface; locating a fibre preform between a first diaphragm and a second diaphragm, the second diaphragm being offset from the forming surface; drawing a vacuum between the first and second diaphragms so as to hold the preform captive between the diaphragms; displacing the second diaphragm towards the former so as to bring the second diaphragm into partial contact with the former; drawing a vacuum between the second diaphragm and the former so as to bring at least a part of the second diaphragm adjoining the preform into conformity with the forming surface; and setting the preform in its configuration; wherein: the fibre preform comprises one or more substantially inextensible fibres extending linearly in a first direction; the forming surface comprises a concavity and prominences on either side of the concavity; and the step of bringing the second diaphragm into partial contact with the former comprises bringing th

Abstract: Provided is an automobile door (600) including: an exterior material (110); a first impact absorbing member (122); and a second impact absorbing member (124), in which the first impact absorbing member (122) is disposed to traverse the exterior material (110) so as to extend between both end portion regions in a vehicle height direction, the first impact absorbing member (122) is disposed on a vehicle interior side from the second impact absorbing member (124), the second impact absorbing member (124) is disposed to traverse the exterior material (110) so as to extend between both end portion regions in a vehicle length direction, the second impact absorbing member (124) is disposed adjacent to an inner surface of the exterior material (110), and at a portion excluding both of the end portion regions in the vehicle height direction, both of the end portion regions in the vehicle length direction, and an intersection portion, bending rigidity in a vehicle width direction of a cross section perpendicular to an

Abstract: A method for producing a fiber reinforced plastic can suppress with which wrinkling or bridging in a convex surface or a concave surface having a large curvature at the same time even if the fiber reinforced plastic has a complicated three-dimensional shape. Such methods for producing a fiber reinforced plastic may involve shaping a prepreg sheet in which continuous fibers are impregnated with a resin material into a three-dimensional shape to produce a fiber reinforced plastic (a); wherein at least a portion of the continuous fibers in an area (X) of the prepreg sheet corresponding to an area (X?) in which the fiber reinforced plastic (a) is shear-deformed is bent in an in-plane direction in advance.

Abstract: An electrically heatable laminated automotive glazing unit including an exterior glass sheet that is curved and tempered and a thin glass interior sheet that is also tempered, these sheets being joined by means of a thermoplastic interlayer sheet. The glazing unit is configured to receive mechanical moving and/or fastening means and a portion of the exterior sheet is not covered by the thin interior sheet. The glazing unit is fastened in the zone not covered by the thin sheet, and the glazing unit includes at least one electrically heatable zone comprising (i) a substantially transparent, electrically conductive coating layer and (ii) spaced busbars adapted to supply electrical voltage across the substantially transparent, electrically conductive coating layer. The spaced busbars are placed in the portion of the exterior sheet which is not covered by the thin interior sheet.

Abstract: A construction of commercial aircraft interior monument employs carbon fiber Spread Tow Fabric (STF) as face sheets (skins) surrounding a paper honeycomb or foam core to produce flat pressed panels of high strength and desirable thickness. Each individual panel is joined with other panels to construct a modular rectangular cubic able to be modularly coupled with additional structures to form the aircraft monument. The use individual STF panels offer a desirable weight and footprint of a fabricated structure as a whole. Also usable in conjunction with other composite reinforcements, the individual STF panels produce hybrid lay-ups for both pressed flat panel and tooled composite moldings offering a high strength to weight ratio of the overall monument.

Abstract: An electronic element mounting substrate includes a first substrate that has a first main surface, has a rectangular shape, and has a mounting portion for an electronic element on the first main surface, and a second substrate that is located on a second main surface opposite to the first main surface, is made of a carbon material, has a rectangular shape, has a third main surface facing the second main surface and a fourth main surface opposite to the third main surface, in which the third main surface or the fourth main surface has heat conduction in a longitudinal direction greater than heat conduction in a direction perpendicular to the longitudinal direction, and that has a recessed portion on the fourth main surface.

Abstract: A fabric of nanofibers that includes an adhesive is described. The nanofibers can be twisted or both twisted and coiled prior to formation into a fabric. The adhesive can be selectively applied to or infiltrated within portions of the nanofibers comprising the nanofiber fabric. The adhesive enables connection of the nanofiber fabric to an underlying substrate, even in cases in which the underlying substrate has a three-dimensional topography, while the selective location of the adhesive on the fabric limits the contact area between the adhesive and the nanofibers of the nanofiber fabric. This limited contact area can help preserve the beneficial properties of the nanofibers (e.g., thermal conductivity, electrical conductivity, infra-red (IR) radiation transparency) that otherwise might be degraded by the presence of adhesive.

Abstract: A fibrous texture in the form of a web includes a first portion extending in a longitudinal direction between a proximal part and an intermediate part. One or more layers of warp threads or strands present on the side of an inner face of the fibrous texture include threads or strands of glass fibers, the threads or strands of the other layers of warp threads or strands including threads or strands of carbon fibers. The fibrous texture further includes a second portion extending in the longitudinal direction between the intermediate part and a distal part of the fibrous texture. One or more of the plurality of layers of warp threads or strands present on the side of an outer face of the fibrous texture include threads or strands of glass fibers. The warp threads or strands are continuous over the entire length of the fibrous texture.

Abstract: Laminated glazings with embedded wire circuits, have many uses. But, due to the higher cost of manufacture, they are not widely used. This invention provides a process to reduce the cost of production for embedded wire laminated glazing. Rather than embedding the wire one interlayer at a time, several circuits are produced on the same sheet, cut out and then inserted into the interlayer of each separate laminate during assembly, reducing the direct labor and capital investment required.

Abstract: A morphing airfoil includes a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. A plurality of standoff mounts are attached to an inner surface of anisotropic skin. The standoff mounts include through apertures for receiving a flexible stringer. The anisotropic skin is attached to underlying structure through the flexible stringers. The flexible stringers interface with actuated position control ribs and passive compliant support ribs. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift and drag distributions along a span of the airfoil without separate control surfaces.

Abstract: Forming systems and methods for drape forming a composite charge are disclosed herein. The forming systems include a forming die having a forming surface configured to receive the composite charge and a collapsible support having a support surface. The forming surface has a forming surface edge that extends along a length of the forming surface, and the support surface has a die-proximate support surface edge that extends along the length of the support surface. The forming surface edge and the die-proximate support surface edge define a gap therebetween. A shape of the die-proximate support surface edge corresponds to a shape of the forming surface edge such that a gap width of the gap is at least substantially constant along a length of the gap. The collapsible support is configured to transition from an extended conformation to a collapsed conformation. The methods include methods of utilizing the systems.

Abstract: A panel for machinery enclosure, particularly for turbomachine enclosures. More specifically, a multilayered panel including several different layers each performing a specific function. In particular, the multilayered panel is capable to provide high levels of jet fire and fire/blast protection together with high performances in term of noise abatement with a lighter structure with respect to the panels of the prior art.

Abstract: A cooking appliance, as provided herein, may include a cabinet, a magnetron, an induction heating coil, and a one-way field filter. The cabinet may define a cooking chamber. The magnetron may be mounted within the cabinet in communication with the cooking chamber to direct a microwave thereto. The induction heating coil may be mounted within the cabinet to direct a magnetic field thereto. The one-way field filter may be disposed within the cabinet between the induction heating coil and the cooking chamber to restrict passage of the microwave therethrough while permitting the magnetic field. The one-way filter may include a lower layer and an upper layer. The lower layer may include a plurality of parallel conductive bands extending in a first direction. The upper layer may be disposed above the lower layer. The upper layer may include a plurality of parallel conductive bands extending in the second direction.

Abstract: A rotorcraft main rotor system, including a yoke, a rotor blade, and a grip assembly attaching the rotor blade to the yoke. The grip assembly includes a grip body formed from a contiguous laminated composite and has a substantially constant thickness, where the grip body has an upper extension, a lower extension and a connecting portion connected between an inboard end of the upper extension and an inboard end of the lower extension. An inside surface of the upper extension faces, and is substantially parallel to, an inside surface of the lower extension, and the upper extension has first features and the lower extension has second features that are aligned with the first features, where the first features and second features each include at least one of an edge contour, attachment holes, or first protective elements.

Abstract: This invention relates to a pressure vessel comprising a hollow body comprising endless fibers embedded in a thermoplastic polymer, in which the thermoplastic polymer comprises one or more polyamides containing one or more aliphatic monomeric units, wherein the one or more polyamides have a CH2-ratio of at least 5.5 and less than 10, calculated by ? identifying the number of different aliphatic monomeric units in the one or more polyamides; ? determining the number of CH2 groups per aliphatic monomeric unit for each of these different aliphatic monomeric units; ? calculating the sum of the so determined numbers of CH2 groups; ? dividing said sum by the number of different aliphatic monomeric units in the one or more polyamides; taking into account only the aliphatic monomeric units present in the one or more polyamides in an amount of at least 10 wt % with respect to the total weight of the one or more polyamides.

Abstract: Disclosed is a sub-laminate module for use in forming a composite laminate structure. The sub-laminate module comprises: a first ply set containing a first ply layer oriented at a first angle and a second ply layer oriented at a second angle, the second angle being equal and opposite the first angle; a second ply set containing a third ply layer oriented at a third angle and a fourth ply layer oriented at a fourth angle, the fourth angle being equal and opposite the third angle; and an acute angle defined by a difference between the first angle and the third angle, wherein the second ply layer is positioned adjacent the third ply layer and the second and third ply layers are both positioned intermediate the first and fourth ply layers, so as to define a double-double helix arrangement. Associated composite laminate structures and methods are also disclosed.