A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

A method for producing an aircraft fuselage for simplifying and accelerating the production of the aircraft fuselage. The method includes providing a fuselage structure which surrounds an interior space and has an inner side facing the interior space, providing an insulating panel for insulating the fuselage structure, wherein the insulating panel has an inner surface and an outer surface, providing a film which is provided with electric strip conductors, fastening the film to the inner surface of the insulating panel, and attaching the insulating panel to the inner side of the fuselage structure.

A method for producing an aircraft fuselage for simplifying and accelerating the production of the aircraft fuselage. The method includes providing a fuselage structure which surrounds an interior space and has an inner side facing the interior space, providing an insulating panel for insulating the fuselage structure, wherein the insulating panel has an inner surface and an outer surface, providing a film which is provided with electric strip conductors, fastening the film to the inner surface of the insulating panel, and attaching the insulating panel to the inner side of the fuselage structure.

A method of assembling a structure in aircraft or spacecraft production wherein two components to be joined together at a joint are provided, each component comprising a joining region. Sealant is applied to one of the component joining regions. An arrangement is formed by positioning the components relative to each other, whereby an uncured layer of the sealant is formed between associated joining regions. The associated joining regions are clamped against each other using a clamping device, and a clamped state is maintained until the layer of sealant has cured to a pre-defined degree, the clamping device being installable on and transportable along with the arrangement. After the layer of sealant has cured to the pre-defined degree, drilling at a plurality of fastening positions is performed to obtain a hole of final dimension at each fastening position, and installation of a final fastener at each fastening position is performed.

A method of assembling a structure in aircraft or spacecraft production wherein two components to be joined together at a joint are provided, each component comprising a joining region. Sealant is applied to one of the component joining regions. An arrangement is formed by positioning the components relative to each other, whereby an uncured layer of the sealant is formed between associated joining regions. The associated joining regions are clamped against each other using a clamping device, and a clamped state is maintained until the layer of sealant has cured to a pre-defined degree, the clamping device being installable on and transportable along with the arrangement. After the layer of sealant has cured to the pre-defined degree, drilling at a plurality of fastening positions is performed to obtain a hole of final dimension at each fastening position, and installation of a final fastener at each fastening position is performed.

A cryogenic storage tank including a first metallic end piece having a first structured connection area on its outer surface, a second metallic end piece having a second structured connection area on its outer surface, a hollow body extending between the first structured connection area and the second structured area. The hollow body is formed of a fiber reinforced polymer-based composite, a first metallic clamp having a third structured connection area and a second metallic clamp having a fourth structured connection area. The hollow body is arranged between and in intimate contact with the first structured connection area of the first metallic end piece and with the third structured connection area of the first metallic clamp and is arranged between and in intimate contact with the second structured connection area of the second metallic end piece and with the fourth structured connection area of the second metallic clamp.

A flexible element for lining an edge of an aeronautical seat shell, made up of an assembly of at least two elongate, flexible and planar cut pieces, secured together by respective longitudinal boundaries so that the assembly has a three-dimensional shape matching with an edge of an aeronautical seat shell.

A method for manufacturing such a lining element, as well as a method for setting up such a lining element over an aeronautical seat shell.

A flexible element for lining an edge of an aeronautical seat shell, made up of an assembly of at least two elongate, flexible and planar cut pieces, secured together by respective longitudinal boundaries so that the assembly has a three-dimensional shape matching with an edge of an aeronautical seat shell.

A method for manufacturing such a lining element, as well as a method for setting up such a lining element over an aeronautical seat shell.

A method for forming a fiber-reinforced thermoplastic part may comprise the steps of locating a lightning strike protection layer on a mold surface of a mold tool, locating a thermoplastic layer over the mold tool, heating the thermoplastic layer to a pliable forming temperature, conforming the thermoplastic layer to a mold surface of the mold tool, and depositing a plurality of fiber strips over the thermoplastic layer.

A processing device processes a frame-shaped workpiece which extends in a prescribed extension direction, and includes, integrally, a plate-shaped web surface portion, a plate-shaped first flange portion that bends and extends from one end of the web surface portion, and a plate-shaped second flange portion which bends from the other end of the web surface portion and extends in the opposite direction to the first flange portion. The processing device includes a shaping device which conveys the workpiece in the extension direction, and an exit side pinch roll device provided further downstream, in the workpiece conveying flow direction, than the shaping device. The exit side pinch roll device includes a first roll which presses a central region of an upper surface side of the web surface portion, and a second roll which presses a central region of a lower surface side of the web surface portion.