The invention relates to a method for producing a fiber-reinforced, polymeric continuous profiled element (1), wherein the continuous profiled element (1), having preferably at least one hollow chamber (2, 2), comprises a core profile (10) which can be produced by means of a pultrusion process, and wherein during the pultrusion process at least one continuous strand having reinforcement fibers (5) is integrated into the polymer matrix (4) of the core profile (10). According to the invention, the curing of the core profile (10) is carried out by means of a dual-cure method.

A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

A honeycomb core, formed from a plurality of polygonal cells arranged in an array. Each polygonal cell has lateral cell walls, the lateral cell walls of each polygonal cell forming a polygonal ring, the lateral cell walls being composed of a sheet material, the sheet material being a symmetric three-layer or five-layer thermoplastic co-extruded sheet material having an inner central or core layer and outer layers. The symmetric three-layer or five-layer thermoplastic co-extruded sheet material provides improved mechanical properties compared to a simple sheet material.

The present invention is directed to a 3D printed mold for creating three dimensional pulp products from a fibrous pulp slurry. Transverse filaments are integrated into an infill structure with an open-cell pattern. The transverse filaments form channels through the interior matrix of the mold. The open cell infill pattern and channels allow for the movement of vacuumed materials through the interior matrix of the 3D printed mold when vacuum pressure is applied. The product surface of the mold comprises an array of beads formed from the over-extrusion of melted material at the ends of the transverse filaments. The beaded array narrows the opening of the channels created by the transverse filaments, preventing the fibers from entering the matrix of the mold and clogging the flow of materials. This causes the fibers to aggregate on the product surface of the mold, forming the three dimensional pulp product.

A ventilated structural panel comprising a first sheet, having a long axis defining a length and a perpendicular short axis defining a width, a plurality of spacing structural elements, fixedly attached to the first sheet such that the yield strength of the panel is greater than the individual yield strength of the first sheet, and the plurality of spacing structural elements being formed such that a plurality of unobstructed pathways are created for air to move from at least one edge of the panel to at least one of an opposite and an adjacent edge of the panel, wherein the first sheet is the only sheet in the panel.

A manufacturing system to form a honeycomb core and a method of forming the same includes a sheet of fibrous material is fed into a perforation assembly. The sheet of fibrous material is perforated via the perforation assembly to form holes through the sheet of fibrous material. The sheet of fibrous material is cut to form layers. The layers are stacked on top of each other such that the holes of the layers align with each other and strips of adhesive bond the respective layers together to form a perforated stack. A coating is applied to the sheet of fibrous material at the holes. The perforated stack is expanded to form a honeycomb panel. The honeycomb panel is dipped in a solution, and the coating repels the solution. The solution adheres to the honeycomb panel except at the holes where the coating is applied to form the honeycomb core.