A method of manufacture of a composite moulding material (1100) comprising a fibrous layer (1102) and a graphene/graphitic dispersion (1104) applied to the fibrous layer (1102) at one or more localised regions (1106) over a surface (1108) of the fibrous layer(1102) in which the graphene/graphitic dispersion (1104) is comprised of graphene nanoplates, graphene oxide nanoplates, reduced graphene oxide nanoplates, bilayer graphene nanoplates, bilayer graphene oxide nanoplates, bilayer reduced graphene oxide nanoplates, few-layer graphene nanoplates, few-layer graphene oxide nanoplates, few-layer reduced graphene oxide nanoplates, graphene/graphite nanoplates of 6 to 14 layers of carbon atoms, graphite flakes with nanoscale dimensions and 40 or less layers of carbon atoms, graphite flakes with nanoscale dimensions and 25 to 30 layers of carbon atoms, graphite flakes with nanoscale dimensions and 25 to 35 layers of carbon atoms, graphite flakes with nanoscale dimensions and 20 to 35 layers of carbon atoms, or graphite flakes with nanoscale dimensions and 20 to 40 layers of carbon atoms, in which the dispersion (1104) is applied to the fibrous layer (1102) using at least one valvejet print head (1112).

The invention relates to a method for producing a composite material component, comprising the following steps: providing a negative mold, fine machining of the negative mold, applying at least one functional layer by means of thermal spraying to the negative mold, applying at least one fiber-reinforced plastic layer with a curable matrix material, curing the matrix material, and detaching the composite material component from the negative mold.

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

The application discloses a high-whiteness MGO substrate, a preparation method thereof and a decorative board having the substrate. The high-whiteness MGO substrate includes a surface layer and a substrate, wherein the substrate is prepared from a forming agent, a lightweight filler, a modifier and water in parts by mass as follows: 40-49 parts of light burned magnesium oxide powder, 18-25 parts of magnesium sulfate heptahydrate, 16-25 parts of a polyvinyl alcohol solution, 16-20 parts of a plant powder, and 0.5-2 parts of a modifier; the modifier being obtained by mixing citric acid, phosphoric acid, and sodium sulfate in a mass ratio of 10:3:6.

An aircraft water tank is provided. With an aircraft water tank being suspended by a fuselage via bushes, a load applied to each of the bushes is transferred from the bush and an attachment hole to a metal plate. The load transferred to metal plate is transferred to a total of four prepreg projection portions at a section of a thick wall portion of the metal plate and transferred to a total of eight prepreg projection portions at a section of a thin wall portion.

A method produces a fiber-reinforced body component for a motor vehicle. The body component has at least one opening, in particular one door opening or one window opening. The method includes at least the following steps: providing the body component; applying a reinforcing element made of fiber composite material having reinforcing fibers embedded in a matrix, in order to stiffen the body component, the matrix being in an uncured state, and the reinforcing element being applied to an opening frame of the opening, which opening frame is formed by the body component.

Proposed is manufacturing method for a hybrid tube, the method including the step of deriving an optimal ratio between a metal tube and a composite material layer when manufacturing the hybrid tube in which the composite material layer is formed on an outer circumferential surface of the metal tube in order to reduce the weight of an existing metal tube such as a cylinder tube of a hydraulic cylinder. In manufacturing a hybrid tube, it is possible to derive an optimal ratio between heterogeneous materials that can achieve weight reduction while satisfying a target buckling load, thereby making it possible to reduce the weight of tubes of metal materials and apparatuses related to such tubes.

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

In one embodiment, an artificial turf system includes an existing artificial turf, an elastic layer and a new artificial turf. The existing artificial turf includes a plurality of existing artificial turf fibres and existing infill granules. The existing infill granules lie between the existing artificial turf fibers and form an existing infill layer on top of a carrier structure. The elastic layer is formed by a hardened binder. At least a lower portion of the elastic layer overlaps with and penetrates at least an upper portion of the existing infill layer. The new artificial turf includes a plurality of new artificial turf fibres.