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.

A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

A composite moulding material (10) comprising a fibrous layer (12) and a graphene/graphitic material (14) applied to the fibrous layer (12) at one or more localised regions (R1, R2, R3, R4) over a surface (16) of the fibrous layer (12) characterised in that the graphene/graphitic material (14) 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/graphitic 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.

According to exemplary inventive practice, ceramic powder or slurry is selectively deposited at many discrete locations on each of many fiberglass fabric substrates. The sizes and/or shapes of the ceramic deposits vary among the substrates. The substrates are selectively ordered and stacked so that perpendicular through-plane alignments of respective ceramic deposits form selected three-dimensional geometric shapes. The resultant stack of substrates, characterized by many three-dimensional ceramic inclusions, is impregnated with an elastomer or an epoxy that binds the ceramic-deposited substrates together, resulting in a finished composite product. Inventive composite structures can be multifariously designed and embodied to afford selected ballistic and/or structural and/or electromagnetic qualities. Another mode of inventive practice provides for incorporation of the above-described inventive composite product as a layer in a multilayer composite system that also includes a high strain-rate-sensitivity-hardening polymer layer, a hybrid composite fabric layer, a ceramic layer, and a polymeric ballistic fabric layer.

A method for forming a composite article includes adding an upper skin at least partially over a failsafe torque tube. The failsafe torque tube includes an inner tube and an outer tube. The method also includes adding a lower skin at least partially under the failsafe torque tube. The upper skin, the lower skin, and the outer tube are made of a composite material. The method also includes co-curing the upper skin, the lower skin, and the outer tube together to produce the composite article.

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.

A composite component (130) such as a shear web for a wind turbine blade is described. The component comprises a molded laminate (44) formed from one or more fibrous layers (40) integrated by resin and defining a laminate edge (48). An edging strip (60) is located adjacent to the laminate edge (48) and is integrated with the laminate. In a particular example, the edging (60) is made from closed-cell foam. Accordingly, resin does not permeate into the bulk of the edging (60) during the molding process. After the molding process, a portion (60a) of the edging (60) is removed to reveal an exposed, substantially resin-free surface of the edging which defines a safety edge (64) of the component.

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.

A method for producing a component having locally different thicknesses includes the steps of providing a first laminate, arranging a release layer on the first laminate, providing a second laminate with a second surface correlating with the first surface of the first laminate, placing the second laminate with the second surface on the first surface so that the release section is enclosed, joining the first with the second laminate by heating and/or pressing, guiding a cutting tool along one release section correlating with the release section, and so that the separating section is included, joining the first to the second laminate by heating and/or pressing, guiding a cutting tool along one contour in the second laminate that correlates with the separating section, so that one segment of the second laminate is completely detached, and removing the detached segment so that a recess is formed in each case.