The present invention concerns a multilayer element comprising a reinforcing material suitable for producing composite parts combined on at least one of the faces of same with a support layer characterized in that the reinforcing material and the support layer are combined by means of electrostatic forces, and a method for preparing such a material and a method for producing a composite part produced from at least one reinforcing material obtained from such an element, after having removed the support layer.

A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

A production method for a fiber-reinforced thermoplastic resin composite material, the method using a crosshead die (1) that has a maximum aperture height of 1 mm or more, wherein reinforcing fibers are supplied in a reinforcing fiber bundle to the crosshead die (1), the reinforcing fibers are conjugated with a melted thermoplastic resin, and the conjugate is brought into contact with a pressurization surface that is at or below the solidification temperature of the thermoplastic resin, is pressurized, and is shaped to have a thickness that is 50% or less of the aperture height.

A fixing device for fixating a segment of a wind turbine blade to a mold in which the blade segment is manufactured, wherein the blade segment has a fixating portion. The fixing device comprises: a first portion for removably fixating the blade segment at its fixating portion to the mold; and a second portion for fixating the fixing device to the mold.

A method of manufacturing a moulded article from first and second moulding compounds includes attaching a first moulding component to a carrier tool, placing the carrier tool and the attached first moulding component in a mould, applying a first moulding process, removing the carrier tool, placing a second moulding component in the mould, and applying a second moulding process to shape the first and second moulding components and bond the first moulding component to the second moulding component. A moulded article is also disclosed.

A method is described for producing a fiber-reinforced plastic substrate that simultaneously satisfies three points of joinability, mechanical characteristics, and productivity, the method including the following components [A], [B], and [C], wherein at least the following drawing step, first impregnating step, second impregnating step, and take-up step are continuously and sequentially performed while the component [A] is caused to run:

[A] a reinforcing fiber
[B] a thermoplastic resin
[C] a thermosetting resin <drawing step> step of drawing a continuous reinforcing fiber sheet containing the component [A]; <first impregnating step> step of impregnating either the component [B] or the component [C] from one surface of the continuous reinforcing fiber sheet to obtain a fiber-reinforced plastic intermediate in which either the component [B] or the component [C] is disposed on a first surface; <second impregnating step> step of impregnating the other of the component [B] or the component [C] from a second surface opposite to the first surface to obtain a fiber-reinforced plastic substrate; and <take-up step> step of taking up the fiber-reinforced plastic substrate.

To provide a production method with which a molded article excelling in surface appearance can be produced. The method for producing a molded article containing a thermoplastic resin and reinforcing fibers having a number-average fiber length of 1 mm or longer, wherein the method includes molding a material containing a thermoplastic resin and reinforcing fibers having a number-average fiber length of less than 30 mm using a first closed mold, and then molding only the molded material once again using a second closed mold.

Processes for forming composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

A thermoplastic composite material comprising, a fiber bundle having a polypropylene emulsion impregnated therein and having a plurality of reinforcing fibers lined up in a predetermined direction, and satisfies the following conditions (1) to (4); and a formed body: (1) A void content of the thermoplastic composite material is 3% or less, (2) A fiber volume fraction of the thermoplastic composite material is 40% or more and 70% or less, (3) A bending strength of a laminated body, in which a plurality of layers of the thermoplastic composite material has been laminated so that the reinforcing fibers would be lined up in one direction, when bent in the fiber-axis direction and measured in conformity to JIS K7074, is 250 MPa or more, and a bending elastic modulus of the laminated body is 90 GPa or more, and
(4) A variation coefficient of the bending strength, when measured at N=5 or more and calculated in conformity to JIS K7074, is within 7%.

An apparatus and process for forming material, the apparatus or process comprising at least one forming unit, each said forming unit having at least one forming opening to receive a feed of material to be formed, the at least one of said forming opening(s) comprises opposing or at least one forming surfaces, at least one of said opposing forming surfaces being dynamically controllable into a pre-determined shape or profile to impart a resultant shape or profile of a pre-determined formation upon the feed of material passing through said forming opening of a said forming unit.