A composite blade is formed by laying up composite material layers in which reinforcement fibers are impregnated with resin in a thickness direction of the blade. The composite blade includes a blade root on a base end side, an airfoil on a tip side, a first lay-up in which some composite material layers are laid up in the blade root so as to space parts of the composite material layers to form spacing parts and to extend from the distal toward the base end side in the thickness direction, and second lay-ups in which some composite material layers are laid up in the spacing parts so as to be lined up in the thickness direction. Among the second lay-ups, a second lay-up closer to a center side than to an outer side in the thickness direction is a larger distance from a proximal position to a top position.

Embodiments are directed to systems and methods for manufacturing composite assemblies comprising laying up composite plies on molds for two or more uncured components, joining the molds for the two or more uncured components to form a tubular body, and curing the joined components simultaneously to create a single composite assembly. The single composite assembly may form a spar for an aerodynamic component. The method may further comprise forming at least one axial edge having a sloped shape on the uncured components and mating the sloped axial edges together when joining the uncured components. The molds for the two or more uncured components may comprise female tools or both female tools and male tools. The two or more cured composite assemblies may comprise one or more of carbon and fiberglass composite materials.

The present invention is intended to provide automated lamination method and device that can efficiently perform automated lamination by using a thin-layer tape. A thin-layer tape automated lamination device 1 includes a provisional formation unit 2 configured to form lamination tapes having thicknesses different from each other by laminating a plurality of thin-layer tapes each having a thickness of 5 m to 80 m, and a lamination-shaping unit 3 configured to laminate and shape each formed lamination tape in a lamination region of a basal body surface.

A method for manufacturing a thermoplastic composite product includes: providing a first and second thermoplastic composite component made from a consolidated stack of thermoplastic composite plies, said first and second component having a first and second ply drop off, respectively. The first and second components are positioned such that the first ply drop off and the second ply drop off are aligned, and the first and second components are fixedly connected by means of heating. The stacks of plies for the first and second components are constructed by stacking the plies in a stacking direction wherein the plies are arranged such that plies at a different position along the stacking direction are laterally offset relative to each other for the purpose of forming the first ply drop off and the second ply drop off, respectively, before consolidating.

A rim portion of a composite wheel comprises a shaped annulus formed about a central axis of rotation of the composite wheel and having a circumferential axis extending circumferentially about the central axis and around the rim portion, said rim portion having a fibre layup comprising a stacked laminate formed from alternating layers of: a hoop tow layer comprising elongate fibre tow in which the fibres are substantially aligned with the circumferential axis of the rim portion, the hoop tow layer being formed from at least one annularly wound elongate fibre tow; and a bias ply layer comprising at least one fibre ply in which the fibres are substantially orientated at an angle of + or to the circumferential axis of the rim portion, wherein is from 26 to 40.

A vehicle crossmember is made from continuous fiber-reinforced polymeric material without the need for metallic structural reinforcements. The crossmember includes more than one fiber-reinforced material composition, including different amounts and/or types of fiber reinforcements along different lengthwise portions of a crossbar of the crossmember. Attachment points and stiffening ribs can be overmolded onto surfaces of the crossbar before assembling two halves of the crossbar together to form the crossmember.

A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

A belt for suspending and/or driving an elevator car includes a tension member extending along a length of the belt, the tension member including a plurality of fibers bonded in a first polymer matrix, the plurality of fibers extending parallel to and discontinuous along a length of the belt and arranged with one or more lengthwise extending gaps between lengthwise adjacent fibers. A jacket substantially retains the tension member. A method of forming a tension member for an elevator system belt includes arranging a plurality of fibers into a fiber bundle. The plurality of fibers extend parallel to a length of the belt and have one or more lengthwise extending gaps between lengthwise extending fibers. The plurality of fibers is bonded to a first polymer matrix.

A vehicle roof stiffener includes at least one fiber reinforced polymer (FRP) portion and at least one metal or metal alloy portion. The FRP portion includes at least one transition structure including a metal or a metal alloy. At least some of the fibers of the FRP portion are embedded in the transition structure. The metal or metal alloy portion is secured to the transition structure of the FRP portion. In an example vehicle roof stiffener, the metal portion extends parallel to a longitudinal axis of a vehicle, and the FRP portion extends transverse to the longitudinal axis. The example vehicle roof stiffener may include a front FRP portion, a rear FRP portion, and two metal side portions. The metal side portions and the FRP portions may be joined by welding the transition structures to the metal portions.

A containment assembly for a machine having a rotor radially bounded at least in part by the containment assembly. The containment assembly may comprise and inner casing member formed from a composite material, a containment liner bonded to a radially inner surface of the inner casing member, an outer casing member formed from a composite material and positioned radially outward of the inner casing member, and a containment core embedded between the inner and outer casing members.