The present invention relates to a wind turbine blade mould comprising a first mould part and a second mould part, where said first mould surface is configured for moulding a pressure side shell of a wind turbine blade, where said second mould surface is configured for moulding a suction side shell of a wind turbine blade, and where the wind turbine blade mould and thus also a wind turbine blade moulded in said mould comprise a first end, a second end, a pressure side shell, a suction side shell, and further comprise a leading edge area and a trailing edge area. The present invention also relates to a wind turbine blade and a manufacturing method for producing a wind turbine blade using a wind turbine mould as mentioned above.

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 system for manufacturing a composite assembly includes a first mandrel, a second mandrel, a first wrap plate, and a second wrap plate. The first wrap plate and the second wrap plate are positionable in side-by-side relation for receiving a wrap material stack. The first wrap plate and/or the second wrap plate are translatable to a wrap plate open position defining a wrap plate gap between the first and second wrap plate surface edge for receiving a bladder. The second mandrel is translatable to a mandrel open position defining a mandrel gap between the first and second mandrel surface edge. The wrap plate gap and the mandrel gap are configured to receive the wrap material stack formed around a bladder. The first and second wrap plate are configured to fold a first and second material stack base portion into overlapping relation with each other on the bladder top.

A fiber-reinforced resin composite configured to be to be used for a vehicle body structure has a cylindrical shape and a longitudinal direction. The fiber-reinforced resin composite includes first fibers and second fibers. The first fibers are disposed along an axial direction of the cylindrical shape. The second fibers are wound over an entire circumferential surface along a direction intersecting the axial direction of the cylindrical shape. The number of the first fibers per unit area in a tensile surface that is to mainly receive tensile stress upon a collision of a vehicle body is larger than the number of the first fibers per unit area in a compressive surface that is to mainly receive compressive stress upon the collision of the vehicle body.

Method and device for manufacturing a profile member of composite material, the cross-section of which has three branches, including the steps of: —moving together two opposite edges of a panel (2) of sheet material in such a manner that these two opposite edges are juxtapositioned in one juxtapositioning direction; translating a pair of jaws (20) in a direction perpendicular to the juxta-positioning direction in such a manner that the pair of jaws (20) is positioned on either side of the opposite juxtapositioned edges, this translational movement of the pair of jaws (20) being carried out in the direction of a base (25); —simultaneously pressing the sheet material between the two jaws (20), on the one hand, and between the jaws (20) and the base (25), on the other hand; —finishing the profile member of composite material by hardening with a matrix with which the sheet material is impregnated.

A form for a vehicle component including a commingled fiber bundle laid out in a two-dimensional base layer that defines a shape of the form, a successive layer formed with the commingled fiber bundle in contact with the two-dimensional layer, and at least one of electrical conductive wiring, sensor, light emitting diode (LED), antenna, radio frequency identification chip, or a printed circuit board stitched to the successive layer. The comingled fiber bundle is composed of a reinforcement fiber being glass fibers, aramid fibers, carbon fibers, or a combination thereof.

A structure of case body selects a material of PET fibers or PET fibers with PP fibers to prepare a non-woven fabric layer block which is processed by baking and cold molding to form a case body. The case body is formed by combining a left shell and a right shell which are manufactured separately, and then combined into a case body with an accommodation space inside. The left shell is divided into a left top wall, a left sidewall and a left bottom wall which are continuously extended and molded. The right shell is divided into a right top wall, a right sidewall and a right bottom wall which are continuously extended and molded. The left and right top walls and the left and right bottom walls have a weight per unit area of 1200-2000 g/m.sup.2. The left and right sidewalls have a weight per unit area of 600-1200 g/m.sup.2.

Described is a method for producing a sandwich composite component and a sandwich composite component with a pressed two- or three-dimensional shape, having at least one structured core layer made of thermoplastic material which has two opposite core layer surfaces, each bonded to a thermoplastic cover layer. A sandwich composite component is also described.

Systems and methods are provided for hardening wing panel preforms. One embodiment is a method for fabricating a wing panel for an aircraft. The method includes loading a wing skin preform onto a contour of an Outer Mold Line (OML) tool, applying stringer preforms to troughs of an Inner Mold Line (IML) tool, aligning the OML tool with the IML tool, and assembling the IML, tool and the OML tool into a cartridge that molds a wing panel preform comprising the wing skin preform and the stringer preforms. The method further includes inserting the cartridge into a press, and hardening the wing panel preform into a composite part while the cartridge resides in the press.

The present invention relates to a method for manufacturing a wind turbine blade shell part made of a fibre-reinforced composite structure, including steps of mounting a plurality of fastening devices on a mounting plate to form a root end assembly, the mounting plate comprising one or more first openings for evacuating air; arranging the root end assembly over a mould surface of a mould; arranging an air-tight cover member so as to form a mould cavity; evacuating air from the mould cavity via at least the one or more first openings of the mounting plate; and supplying a polymer into the mould cavity and allowing the polymer to cure so as to form the composite structure. A root end assembly for use in the method is also provided.