| 摘要 |
The invention relates to a method of connecting two fuselage sections (1, 2, 21, 22) formed by a fiber-reinforced plastics material, in particular wound fuselage sections (1, 2, 21, 22) for aircraft fuselage cells, having a multiplicity of stringers (10, 11, 35, 36) arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (3, 4, 25, 26), with the formation of a transverse joint (5, 30). In order to be able in particular to join together wound CFRP fuselage sections so that simple tolerance compensation is made possible in a continuous, industrial production process, the method according to the invention comprises the following steps: aligning a first and a second fuselage section (1, 2, 21, 22) with respect to one another, heating and adapting at least one transverse butt strap (9, 23), formed by a fiber-reinforced thermoplastic material, in such a way that tolerance compensation between differing cross-sectional geometries of the first and second fuselage sections (1, 2, 21, 22) is made possible, or heating at least one end region (27) of a second fuselage section (2, 22) formed by a fiber-reinforced thermoplastic material, and joining together the two fuselage sections (1, 2, 21, 22). |
