Abstract: A fuselage structure of an aircraft includes a first fuselage section and a second fuselage section connected to the first fuselage section, the second fuselage section including at least one first fuselage vessel extending the first fuselage section in a longitudinal direction, with the first fuselage section and the first fuselage vessels comprising circumferential flanges arranged at longitudinal ends of the first fuselage section and the first fuselage vessels extending radially in the first fuselage vessels and the first fuselage section wherein fasteners extend through abutting flanges of the first fuselage section and the fuselage vessel to establish a force-fit connection between the first fuselage section and the first fuselage vessels, when assembled, and wherein the first fuselage vessel provides a storage space for at least one tank structure. Also disclosed are a method for assembling the fuselage structure and an aircraft including the fuselage structure.

Abstract: An apparatus for the forming of a lay-up of fiber composite material, in particular in the aerospace sector is provided. In this case, the apparatus has at least one forming tool, which has a surface contour corresponding to a desired geometry of the lay-up after the forming, and a tool carrier, to which the at least one forming tool is releasably fastened. From a further viewpoint, the invention makes available an apparatus with a modular structure, it then being possible for any desired forming tools to be combined with the tool carrier according to requirements. This leads in particular to less laborious handling, since it obviates the need for handling of the comparatively large tool carrier.

Abstract: The invention relates to a method for producing a fiber composite component, comprising the steps: introduction of a first body (12), consisting of fibers and a matrix material, into a mold (10), said first body (12) having a continuous first body edge (18); the first body (12) is irradiated with microwaves (28) to produce a fiber-composite component. According to the invention, the first body (12) is introduced into the mold (10) in such a way that at least parts of the first body edge (18) are brought into contact with the mold (10).

Abstract: The invention relates to a method for producing a fibre composite component, comprising the steps: introduction of a first body (12), consisting of fibres and a matrix material, into a mould (10), said first body (12) having a continuous first body edge (18); the first body (12) is irradiated with microwaves (28) to produce a fibre-composite component. According to the invention, the first body (12) is introduced into the mould (10) in such a way that at least parts of the first body edge (18) are brought into contact with the mould (10).

Abstract: An apparatus for the forming of a lay-up of fibre composite material, in particular in the aerospace sector is provided. In this case, the apparatus has at least one forming tool, which has a surface contour corresponding to a desired geometry of the lay-up after the forming, and a tool carrier, to which the at least one forming tool is releasably fastened. From a further viewpoint, the invention makes available an apparatus with a modular structure, it then being possible for any desired forming tools to be combined with the tool carrier according to requirements. This leads in particular to less laborious handling, since it obviates the need for handling of the comparatively large tool carrier.