An elongate tubular shaft body having a stack of wrapped layers of fibrous reinforcement in a resin matrix, a portion of the stack of wrapped layers circumferentially surrounding a first surface part of a fibrous layer has a non-constant width which varies non-linearly with a change in radius of an inner elongate circumferential surface in the portion, and wherein the fibrous reinforcement has fibres that are, along the length of the elongate tubular body, constantly oriented with respect to a cylindrical coordinate system about the longitudinal axis of the elongate tubular body, the fibre orientation in any said portion being independent of the geometry of the inner and outer elongate circumferential surfaces of that portion.

A method of manufacturing stiffened structural panel for an aircraft including a main sheet made of composite material with unidirectional fibers, and a stiffening structure secured to the main sheet and made of a composite material comprising a resin and chopped fibers, the stiffening structure including on the one hand a base adhering to one of the two lateral faces of the main sheet, and a network of stiffeners in the form of a grid projecting from the base. The method includes a step of compression molding the stiffening structure from a block formed of a prepolymer reinforced with chopped fibers.

A method of producing a high-pressure tank including a liner and a reinforcement layer made of fiber-reinforced resin includes a process of forming at least a domed member included in the reinforcement layer. The process includes placing first fiber bundles to form a part of a protruding portion and a part of a domed main body, and placing second fiber bundles to cover the first fiber bundles. The first fiber bundles are placed, such that a fiber direction of the first fiber bundles in the protruding portion follows an axial direction of the protruding portion, and resin with which the fiber bundles are impregnated is solidified while the first fiber bundles are being placed. The second fiber bundles are placed, such that the fiber direction of the second fiber bundles intersects with the fiber direction of the first fiber bundles.

A substantially flat-plate-shaped laminated base material has at least a layer-shaped body α and a layer-shaped body β are layered or disposed side by side, the layer-shaped body α having one or more cut prepregs A in which reinforcing fibers oriented in one direction are impregnated with a resin composition, the volume fraction of fiber is 45-65%, and at least a portion of the reinforcing fibers are segmented into a fiber length of 10-300 mm by a plurality of cuts, and the layer-shaped body β having one or more base materials B in which reinforcing fibers having a fiber length in the range of 10-300 mm are impregnated with a resin composition.

A composite fiber for use in additive manufacturing such as fused filament fabrication is described along with methods of its construction and use. The composite fiber includes a single continuous fiber (e.g., a continuous carbon roving) and a polymer (e.g., a high glass transition polymer) in intimate contact. The composite fiber is formed through immersion of the continuous fiber in a series of two or more solutions that together include monomer(s), catalysts, or other materials for generating the polymer as the continuous fiber moves through the solutions.

A method for manufacturing a fiber-reinforced composite material molded article of the present invention includes a step of causing a reinforcing fiber base material to undergo deformation with use of a mold, the reinforcing fiber base material including: reinforcing fibers which are unidirectionally oriented; and a matrix resin composition. The reinforcing fiber base material has a cut in a zone which is to undergo shear deformation and/or compressive deformation, the cut being substantially parallel to an orientation direction of the reinforcing fibers, and has substantially no cut that cuts through a fiber.

A hot drape-forming method for shaping fibrous preforms and prepreg plies into complex geometries. For shaping fibrous preforms, the hot drape-forming method includes: a) dividing the total number of preforms into a plurality of sub-preforms (S1, S2, S3); and b) consecutively shaping each sub-preform (S1, S2, S3) by applying vacuum pressure and heat, wherein the shaping of all sub-preforms (S1, S2, S3) are carried out in the same tool housing (10) over the same molding surface. The resulting shaped preform (S1, S2, S3) is ready for resin infusion. The same method can also be used to shape resin-impregnated prepreg plies.

Multi-body interpenetrating lattices comprise two or more lattices that interlace or interpenetrate through the same volume without any direct physical connection to each other, wherein energy transfer is controlled by surface interactions. As a result, multifunctional or composite-like responses can be achieved by additive manufacturing of the interpenetrating lattices, even with only a single print material, with programmable interface-dominated properties. As a result, the interpenetrating lattices can have unique mechanical properties, including improved toughness, multi-stable/negative stiffness, and electromechanical coupling.

To improve the range of application of manufacturing methods for fiber-reinforced polymer or metal hybrid composite components, and preferably to enable the introduction of fiber bundles into a larger number of geometries, such as branches, merging points and intersections, a production method for producing a component including a composite material with a fiber reinforcement which is formed from fiber bundles and resin is disclosed. A component body with tube-like cavities is initially provided. Curable resin is introduced into the cavities. A pulling apparatus for the fiber bundles is also inserted into at least one of the cavities. The pulling apparatus includes at least one pulling member suitable for pulling the fiber bundles and transmitting compressive force. As a result of pulling of the pulling member, the fiber bundles are pulled into the cavities.

A method is disclosed for additively manufacturing a composite structure. The method may include directing a continuous reinforcement into a print head, and coating the continuous reinforcement with a first matrix component inside of the print head. The method may further include coating the continuous reinforcement with a second matrix component, discharging the continuous reinforcement through a nozzle of the print head, and moving the print head in multiple dimensions during the discharging. The first and second matrix components interact to cause hardening of a matrix around the continuous reinforcement.