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.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

An apparatus for forming a flange has a laminate component and a drum supporting the laminate component. A forming tool selectively engages the laminate component. A diaphragm member extends between the drum and the laminate component and selectively engages the forming tool. Movement of the diaphragm member deforms the laminate component away from the drum about an edge of the forming tool, and the laminate component maintains a substantially uniform thickness.

A method for producing products made of composite material, including the following operating steps: placing between a first mould and at least a second mould at least one layer of composite material fibre fabric and at least a first layer of composite material fibres, wherein a layer of non-polymerized, composite material resin, substantially free of hardener, is placed between the fabric layer and the first mould; injecting resin and hardener between the first mould and the second mould to impregnate the layer and the first fibre layer with the injected resin and polymerizing the injected resin and the resin layer with the injected hardener. A semi-finished item which can be used in this method and to a product made using this method and/or with this semi-finished item.

A part made of a fiber-reinforced composite material includes a structure made from a set of fibers supported in a thermosetting resin and a peel ply across all or part of the outer surface of the structure. The part has a gradient of polymerization at the interface between the structure and the peel ply. Also, methods for making such a part and methods for bonding such parts.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation. The plurality of smart susceptor heater blankets may be supported by a deployment system that lowers the plurality of smart susceptor heater blankets toward, and raises the plurality of smart susceptor heater blankets away from, a working surface.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation.

One example provides a composite. The composites includes a core layer comprising a thermoplastic polymer and having a first and a second sides opposite to each other; a first set of two layers disposed over at least a portion of the core layer respectively on the first and the second sides, each layer of the first set including carbon fibers aligned in a first direction in a plane; and a second set of two layers disposed over at least a portion of the first set of two layers respectively on the first and the second sides, each layer of the second set including carbon fibers aligned in a second direction perpendicular to the first direction in the plane In the plane, the composite has a length and a width, the length larger than the width and parallel to the second direction.

The present invention provides: a surface-coated film which is for being integrally formed with a fiber impregnation resin; a surface-coated fiber-reinforced resin molded product; and a manufacturing method thereof. The surface-coated film has a base film B and an easily adhesive layer A provided on the base film B, wherein the base film B has a flat layer b2 and an easily molded layer b1 adjacent to the easily adhesive layer A, the thickness of the easily adhesive layer A is 30-250 nm, the thickness of the base film B is 50-500 μm, the easily molded layer b1 and the flat layer b2 satisfy both expression 1 of 3≤ratio (EHb2/EHb1) of storage elastic modulus EHb2 of flat layer b2 at 150° C. to storage elastic modulus EHb1 of easily molded layer b1 at 150° C., and expression 2 of 1,000 MPa≤storage elastic modulus ELb1 of easily molded layer b1 at 23° C.