Longitudinal seam-structure assembly of aircraft fuselage
AssigneeAirbus Deutschland GmbH
InventorHarald Schueler
Life of this patent
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Abstract
When assembling longitudinal seams, the shells in the region of overlap are moved together over lining-up drill holes, the shells are fastened and subsequently the pilot holes are transferred. Thereafter, these pilot holes are deburred, which involves temporary moving apart of the shells. According to one embodiment of the present invention a rib clamping device is stated that can be used for the longitudinal seam-structure assembly of an aircraft fuselage and that comprises attachment means and fastening means for non-positive and frictionally-engaged fastening of the shells. There is thus no longer any need to temporarily move the components apart.
Claims10
A rib clamping device for longitudinal seam-structure assembly of an aircraft fuselage, wherein the rib clamping device comprises:
- attachment means for attaching the rib clamping device to a first rib of the aircraft fuselage;
- fastening means for non-positive and frictionally-engaged fastening of a first shell and a second shell of the aircraft fuselage such that a first group of first drill holes can be produced in the first shell without any stress.
Dependencies are inferred from the claim text.