A method for manufacturing a fuselage component for an aircraft includes building up, on a surface of a two-dimensional shell part composed of a fibre composite material, stiffening profiles crossing at an intersection from a plurality of layers, superimposed on one another in a thickness direction, which are each formed by applying filaments, which each comprise a fibre bundle embedded in a thermoplastic material. Stabilising layers, within which the filaments extend beyond the intersection, are formed from the filaments in each of the stiffening profiles. A fuselage component and an aircraft, which comprises at least one such fuselage component, are furthermore described.

A headrest assembly includes a lattice matrix having a plurality of three-dimensional (3D) cells. Each 3D cell of includes a node and a plurality of links outwardly extending from the node. The lattice matrix includes a plurality of sections including a first section having a first overall elastic modulus, a second section positioned adjacent to the first section and having a second overall elastic modulus that is higher than the first overall elastic modulus of the first section, and a third section positioned adjacent to the second section and having a third overall elastic modulus that is higher than the second overall elastic modulus of the second section. The lattice matrix is integrally constructed using an additive manufacturing technique, wherein the 3D cells of each section are provided in various patterns and cured to varying degrees to provide the varying overall elastic moduli of each section of the lattice matrix.

A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

A molding device for producing a shell element reinforced with supporting elements and composed of fiber composite material, including a mold part with a mold surface including a cavity for receiving a supporting element of the shell element, and a mold core to be arranged in the cavity and to support the supporting element on the shell element when the supporting element of the shell element is arranged in the cavity. The molding device enables prevention of the mold cores from falling out in an uncontrolled manner when the shell element is removed from the mold as the mold core includes a holding device to engage with the supporting element of the shell element to be produced located in the cavity and to hold the mold core on the supporting element when the shell element to be produced is released from the mold part.

Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.

Methods of forming a curvature into a composite stiffener and a forming tool are presented. The composite stiffener is positioned in a forming region created by a base assembly and an upper assembly. A first airflow is applied through the material of the base assembly. A second airflow is applied through the material of the upper assembly. A plurality of brackets of the upper assembly is moved relative to each other to change a curvature of the forming region along a length of the forming region to form the curvature into the composite stiffener.

Systems and methods are provided for compacting laminates. One embodiment is a method for compacting a laminate onto a surface of a forming tool. The method includes placing the laminate onto the forming tool, disposing a compaction device over the laminate, gripping the compaction device to the forming tool, compacting the laminate with a pressure foot of the compaction device, and removing the compaction device from the forming tool.

The present invention generally relates to a system and method for using a volatile organic compound (VOC) free low radiant flux LED UV curable composition, and more particularly to unique and novel uses of the composition such as one or two or more of a fire retardant, clear coat, composite material, resin, top coat, improved holdout coating, a sealant coat, and combinations of the same.

A method for manufacturing two soundproof panels of an aircraft nacelle including a duct. The manufacturing method includes a step of supplying a mold having, on a single face, a cavity for each soundproof panel, a step of producing, in the bottom of each cavity, an inner skin for being oriented towards the duct, and a curing step during which the elements present in the mold are cured in the mold. Such a method makes it possible to produce the two soundproof panels in the same mold, thus reducing the gaps between them after they have been positioned.

A method for manufacturing a vehicle steering wheel, the steering wheel comprising: —a rim, —an outer sheath formed by at least one strip attached around at least one part of the rim, —at least one device passing through the outer sheath, the method comprising at least the following steps: —positioning the strip around the rim, —attaching the strip to the rim in order to form the outer sheath, —forming an opening in the outer sheath facing an internal part of the device, —folding portions of the outer sheath towards the inside of the rim.