Assembly system for an automated internal assembly of an aircraft fuselage

1. An assembly system for an automated internal assembly on a

curved assembly surface of an aircraft fuselage, comprising:

two assembly rails, which are shaped in accordance with a curvature of the assembly surface of the aircraft fuselage such that the two assembly rails follow a longitudinal direction of the aircraft fuselage or a peripheral direction of the aircraft fuselage, so that the assembly rails are fastenable in the aircraft fuselage, along the longitudinal direction of the aircraft fuselage or along the peripheral direction of the aircraft fuselage, parallel to one another and parallel to the assembly surface of the aircraft fuselage;

a plurality of rigid connecting elements holding the two assembly rails and configured to be coupled to stiffening elements of the aircraft fuselage;

an assembly slide configured to slide along the assembly rails; and

a tool supported by the assembly slide and configured to perform an assembly step;

wherein the assembly slide has at least one assembly axis, along which the tool is configured such that the tool is movable relative to the assembly slide;

wherein the assembly axis is configured such that the assembly axis follows the curvature of the assembly surface of the aircraft fuselage, and

wherein the two assembly rails comprise a plurality of rail segments configured to correspond geometrically to predefined fuselage portions, and

wherein the two assembly rails are configured to be fastened to stiffening elements of the aircraft fuselage via assembly bores of the stiffening elements.

2. The assembly system according to claim 1 , wherein the at least one assembly axis is arranged perpendicular to the assembly rails.

3. The assembly system according to claim 1 , wherein the assembly slide has an alignment system configured to register a reference structure on the assembly surface of the aircraft fuselage and, on the basis thereof, to position the tool relative to the assembly surface.

4. The assembly system according to claim 1 , wherein the at least one assembly axis is configured as a rail, and wherein the tool is configured to slide relative to the assembly slide along the at least one assembly axis.

5. The assembly system according to claim 4 , wherein the at least one assembly axis comprises two assembly axes, between which the tool is supported by the assembly slide.

6. An aircraft fuselage, comprising:

a curved assembly surface;

two assembly rails fastened within the aircraft fuselage along a longitudinal direction of the aircraft fuselage or along a peripheral direction of the aircraft fuselage, parallel to one another and parallel to the curved assembly surface of the aircraft fuselage;

a plurality of rigid connecting elements holding the two assembly rails and configured to be coupled to stiffening elements of the aircraft fuselage;

an assembly slide configured to slide along the assembly rails over the curved assembly surface of the aircraft fuselage; and

a tool supported by the assembly slide and configured to perform an assembly step on the curved assembly surface of the aircraft fuselage;

wherein the assembly slide has at least one assembly axis, along which the tool is configured such that the tool is movable between the assembly rails relative to the assembly slide;

wherein the assembly axis is configured parallel to the curved assembly surface of the aircraft fuselage such that the assembly axis follows a curvature of the curved assembly surface of the aircraft fuselage, and

wherein the two assembly rails comprise a plurality of rail segments configured to correspond geometrically to predefined fuselage portions, and

wherein the two assembly rails are fastened to the stiffening elements of the aircraft fuselage via assembly bores of the stiffening elements.

7. The aircraft fuselage according to claim 6 , wherein the stiffening elements are configured as ribs.