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.

Abstract: The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.

Abstract: The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.

Abstract: The invention relates to a method for joining an uncured stringer to a structural component of an aircraft or spacecraft. The uncured stringer is supplied with at least one joining section and at least one web section. A rapidly curing low-temperature auxiliary material is deposited on web flanks of the at least one web section, which are to be supported. The at least one joining section of the uncured stringer is fitted to the structural component. Curing of the auxiliary material then takes place at a first curing temperature in order to form cured supporting elements for the web flanks of the at least one web section, which are to be supported. Curing of the uncured stringer is undertaken at a second curing temperature which is greater than the first precuring/curing temperature, and then the deposited and cured auxiliary material is removed.

Abstract: The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement necessary for the joining is produced in two parts. In a first step, each precured stringer is covered in advance with a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Respective vacuum film strips are subsequently arranged on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.