A reinforced composite assembly includes a first sheet made of carbon fiber and having a first perimeter, a second sheet made of a non-carbon fiber material and having a second perimeter, wherein the second sheet is disposed atop the first sheet within the first perimeter, and a metallic plate having a third perimeter, wherein the metallic plate is disposed atop the second sheet within the second perimeter. The metallic plate has a plurality of holes formed therein about a perimeter of the metallic plate and defining a plurality of respective bridge portions between each of the holes and an adjacent outer edge of the metallic plate, and/or a plurality of extensions extending outward from a main portion of the metallic plate. A first arrangement of thread stitching secures each of the bridge portions and extensions to the second sheet or to the first and second sheets.

The invention relates to a method of manufacturing a composite component with continuous fibre reinforcement and having a reinforced hole. The hole is reinforced by incorporation of at least one reinforcing element (1) into a layered arrangement of continuous fibres. The reinforcing element comprises a circumferential member (2) with a through-going first hole (9) and a plurality of continuous element fibres (3). The at least one reinforcing element (1) is arranged in an overlapping and/or sandwiching engagement with the layered arrangement so that the first hole is arranged within and aligned with a second hole (8) to be reinforced. Hereby an externally force applied to the reinforced hole during use of the component is distributed over a larger region of the material around the hole. Thereby the component can be joined to another part e.g. by a bolted connection which allows for disassembly that would not have been possible if they were joined by adhesive joining.

An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

Provided is a technology for imparting a design having a higher degree of freedom than in the related art to a composite material product including a woven fabric, which is formed of a thread made of a specific fiber (carbon fiber, glass fiber, aramid fiber), and a resin. As a first step, a specific fiber cloth (100), which is the woven fabric formed of the thread made of a specific fiber, and a backing sheet (200) formed of a thermoplastic resin are stacked. Subsequently, embroidery is performed with an embroidery thread (300) to form a design on a front surface of the specific fiber cloth (100). The embroidery thread (300) is made of the specific fiber, and penetrates through the specific fiber cloth (100) and the backing sheet (200). Then, the specific fiber cloth (100) and the backing sheet (200) are sandwiched between resin sheets (400) each formed of a thermoplastic resin, and the whole is cured by an RFI method.

Devices, systems, and methods of improving paste flow during the manufacture of wind turbine blades are provided. When the first turbine blade half is aligned with the second turbine blade half, a gap is formed between the first shell and the bond cap. The assembly includes a first mold half corresponding to the first turbine blade half and a second mold half corresponding to the second turbine blade half. When the first mold is aligned with the second mold, a second gap is formed. A first barrier is disposed within the first gap and a second barrier disposed within the second gap thereby fluidly sealing a volume defined by the first gap and the second gap to direct adhesive paste flow along the blade span between the adjoining leading and trailing edges.

There is provided an automated lamination system for embedding printed electronic element(s) in a composite structure. The automated lamination system includes a supply of composite prepreg material, a layup tool assembly, and a modified automated lamination apparatus laying up layer(s) of the composite prepreg material on the layup tool assembly, to form the composite structure. The modified automated lamination apparatus includes a section preparation pre-printing apparatus preparing section(s) on a top surface of a top layer of the layer(s), to obtain prepared section(s), and includes a non-contact direct write printing apparatus mechanically coupled to the section preparation pre-printing apparatus, and includes one or more supplies of electronic element materials, printed with the non-contact direct write printing apparatus, on each of the prepared section(s), to obtain the printed electronic element(s), that are embedded in the composite structure. The automated lamination system further includes a control system and a power system.

The invention relates to a device comprising: a first layer (11) of a thermoformable material that is inelastically deformable in a thermoforming temperature range, a second layer (1) of a viscoelastic material that is elastically deformable in a temperature range including a use temperature range of the device and the thermoforming temperature range, and wherein: the use temperature range is lower than the thermoforming temperature range, the first layer is bonded to the second layer, the thermoformable material is elastically deformable and more rigid than the viscoelastic material in the use temperature range, the thermoformable material is less rigid than the viscoelastic material in the thermoforming temperature range.

A building panel has a deep drawn transparent film having an inner face and a structure having solar cells on the inner face of the deep-drawn film. The structure has an inner face turned away from the film and an outer face on or closely juxtaposed with the inner face of the film. A reinforcement layer constituted as a mass of foamed granular particles is spread over the inner face of the structure in direct contact with the inner face of the structure without the interposition of an adhesive and is heat cured to the film.

A bladder mandrel package, used to manufacture a composite structure, includes a mandrel and a wrap ply, surrounding the mandrel to form a wrapped mandrel. The bladder mandrel package also includes a first radius filler, coupled to the wrap ply at a first radius of the wrapped mandrel, and a second radius filler coupled to the wrap ply at a second radius of the wrapped mandrel. The mandrel, the wrap ply, the first radius filler, and the second radius filler are consolidated to from the bladder mandrel package.

Disclosed are reinforced structures. The structures are comprised of reinforced elements that have continuous fibers embedded in a matrix material. The reinforced elements are combined in a matrix material to form a desired shape of reinforced structure.