A structural component, in particular for an aircraft, spacecraft or rocket, has a ply of fiber reinforced polymer; a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Systems and method for fabricating a metal core truss panel with seamlessly embedded features in accordance with embodiments of the invention are illustrated. One embodiment includes a method for producing a metal core truss panel composite, the method including fabricating a sacrificial core truss panel including a plurality of interconnected truss members and at least one embedded feature, and plating the sacrificial core truss panel with a layer of metal forming a metal core truss panel including a plurality of interconnected metal truss members and at least one seamlessly embedded metal feature.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

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.

The invention proposes a method for manufacturing a grille for a cascade type thrust reverser, of a jet engine, said method including the following steps: a) manufacturing a first component comprising long fibres, pre-impregnated by a thermoplastic or thermosetting resin; b) manufacturing, together with step a), a series of second components each including discontinuous fibres, pre-impregnated by a thermoplastic or thermosetting resin, step b) being carried out such that the second components are, on the one hand, arranged to transversally with respect to a longitudinal direction of the first component on at least one side of the first component and, on the other hand, spaced from one another according to this longitudinal direction, so as to form a comb-shaped structure, wherein the second components are consolidated to the first component.

A method of manufacturing a cured composite structure includes placing a radius filler element into a radius cavity extending along a length of a composite base member formed of dry fiber material comprised of reinforcing fibers. The radius filler element is formed of a radius filler material. The method also includes infusing resin into the dry fiber material, and chemically reacting the resin with the radius filler material to create a mixture of resin and radius filler material along side surface interfaces between the radius filler element and the composite base member. The method additionally includes curing or solidifying the resin, and allowing solvent in the resin to evaporate causing hardening of the mixture and bonding of the radius filler element to the composite base member, and resulting in a cured composite structure.

A method of fabricating a formed structure with expandable polymeric shell microspheres. A first plurality of polymeric shell microspheres are heated from an unexpanded state to an expanded state to form a plurality of expanded microspheres. The plurality of expanded microspheres are mixed with an epoxy resin and a second plurality of unexpanded polymeric shell microspheres. The mixture is formed in a shape to create a preform. The preform is wrapped with fiber tape to create a wrapped preform. The wrapped preform is placed in a mold. The mold is heated and the second plurality of unexpanded microspheres expand from an unexpanded state to an expanded state. The mold is cooled and the formed structure is removed from the mold.

Provided are composite feedstock strips for additive manufacturing and methods of forming such strips. A composite feedstock strip may include continuous unidirectional fibers extending parallel to each other and to the principal axis of the strip. This fiber continuity yields superior mechanical properties, such as the tensile strength along strip's principal axis. Composite feedstock strips may be fabricated by slitting a composite laminate in a direction parallel to the fibers. In some embodiments, the cross-sectional shape of the slit strips may be changed by reattributing material at least on the surface of the strips and/or by coating the slit strips with another material. This cross-sectional shape change may be performed without disturbing the continuous fibers within the strips. The cross-sectional distribution of fibers within the strips may be uneven with higher concentration of fibers near the principal axis of the strips, for example, to assist with additive manufacturing.

A component is provided that includes a multi-layer body configured with a thermoplastic layer, a thermoset layer and a scrim at an interface between the thermoplastic layer and the thermoset layer. The thermoplastic layer includes a plurality of reinforcement particles within a thermoplastic matrix. The thermoset layer is configured from or otherwise includes a thermoset matrix.

A process for manufacturing a composite material component including a fiber reinforcement based on carbon fibers densified by a matrix, includes successively producing a fiber structure by multilayer three-dimensional weaving, placing the fiber structure in a closed mold, and injecting a resin into the mold, and wherein, during the weaving of the fiber structure, the process further includes spraying carbon nanoparticles onto the carbon fibers.