| 摘要 |
The invention relates to a method for tolerance compensation between two fiber composite component parts (1, 3) for aircraft. In order to compensate in simplified fashion tolerances between two fiber composite component parts being joined, the method according to the invention has the steps: a) manufacturing the first fiber composite component part (1) wherein an assembly surface (2) can have tolerance deviations, b) manufacturing a tooling insert (7) from a surface geometry of the assembly surface (2) c) manufacturing the second fiber composite component part (3) by means of the tooling insert (7) wherein a surface geometry of a contact surface (9) of the second fiber composite component part (3) corresponds substantially with the surface geometry of the assembly surface (2), and d) joining the first fiber composite component part (1) to the second fiber composite component part (3) in the area of the assembly surface (2) and contact surface (9). |
