A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

In a method for manufacturing a high-pressure tank, a fiber bundle impregnated with a thermosetting resin base material is wound around an outer surface of a liner in a state where tension is applied to the fiber bundle in a filament winding step. The filament winding step includes a pressure-bonding step and a cutting step. In the pressure-bonding step, a terminal end portion which is a winding end of the fiber bundle is thermocompression-bonded to an outer peripheral portion of the fiber bundle wound around the liner. In the cutting step, a surplus portion of the fiber bundle is cut by a cutting tool.

A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.

A method of manufacturing a plurality of reinforcing element preforms, involving the steps of: positioning reinforcing elements on the external surface of a die; assembling the reinforcing elements thus positioned with one another so as to form a textile sleeve with a longitudinal axis and surrounding the die; moving the sleeve longitudinally toward a multi-cavity mandrel having an elongate overall shape, the multi-cavity mandrel having on its external surface a plurality of longitudinal cavities which are distributed, when viewed in cross section, around the periphery of the external surface; forming the sleeve on the plurality of peripheral cavities so that the sleeve conforms to the shape of the multi-cavity mandrel and thus adopts the shape of a set of reinforcing element preforms.

A method produces a seat cover for a vehicle seat made of a form-fit knit part. The form-fit knit part has continuous fibers and reinforcing fibers, and each of the reinforcing fibers is made of a core fiber and a cladding fiber coaxially sheathing the core fiber. The form-fit knit part is first produced using a knitting machine, and the seat cover is subsequently produced from the form-fit knit part using an ironing machine. The ironing machine has at least one lower mold in the shape of the vehicle seat, and the core fiber has a higher melting point than the cladding fiber.

A tension member with at least one loop made from fiber-reinforced plastic, which tension member has a plurality of fibers that run substantially parallel to each other, so that the loop is formed by the plurality of fibers, wherein a first group of fibers is turned over along the loop in a first turning direction, while a second group of fibers is turned over along the loop in a second turning direction, which is opposed to the first turning direction. Some of the turned-over fibers of both groups end in a different distance from the vertex of the loop than others of the turned-over fibers, so that a cross-section of the tension member that results from the respective number of fibers that run approximately parallel to each other outside the turning-over area of the fibers approximately continuously decreases until it reaches the cross-section size of the tension member.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

The application relates to a method for producing a hollow support from a fiber composite material, to a core designed as a hollow body, to the use of said core, and to the use of said hollow support made from fiber composite material.

A structural body manufacturing method includes a first step of forming a cylindrical laminate body LM by winding a plurality of sheets including reinforcing fibers and an uncured thermosetting resin around a mandrel MD, a second step of compressing an entire circumference of the laminate body with a tape TP, a third step of heating the laminate body to a state prior to when the thermosetting resin is completely cured, a fourth step of extracting the mandrel from the laminate body, a fifth step of placing the laminate body around which the tape is wound in a molding die UD, LD, pressurizing the laminate body, and heating the laminate body until the thermosetting resin is completely cured, and a sixth step of removing the laminate body from the molding die and peeling off the tape.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.