Longitudinal seam-structure assembly of aircraft fuselage
View Patent ↗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.
1. 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;
wherein the attachment means comprises a first hydraulic or pneumatic clamping cylinder and a form block; and
wherein a region of the first rib is squeezed in between the first hydraulic or pneumatic clamping cylinder and the form block by interaction of the first hydraulic or pneumatic clamping cylinder with the form block, such that both the first hydraulic or pneumatic element and the form block directly contact the region of the first rib and so that the rib clamping device is attached to the first rib.
2. The rib clamping device of claim 1 ,
wherein the fastening means comprises a second hydraulic or pneumatic clamping cylinder and a pressure stamp;
wherein the pressure stamp can be pressed by the second hydraulic or pneumatic clamping cylinder for fastening the first and the second shell to each other; and
wherein the first group of first drill holes is transferred using a crack stopper as a jig.
3. The rib clamping device of claim 1 , wherein furthermore the fastening means is designed to fasten an outside drilling jig to a pressure stamp by way of the first group of first drill holes so that then a second group of second drill holes in the first and the second shell can be produced in a region of overlap of the first and the second shell.
4. The rib clamping device of claim 1 , wherein by attaching the rib clamping device and fastening the first and the second shell a non-positive and frictionally-engaged connection between the first end of the first rib, the second end of a second rib, the first shell and the second shell is established.
5. The rib clamping device of claim 1 , further comprising a pressure measuring device for measuring the pressure exerted by the rib clamping device on the first and the second shell.
6. The use of a rib clamping device of claim 1 for the longitudinal seam-structure assembly of an aircraft fuselage.