Shell arrangement for a fuselage of an aircraft and fuselage for an aircraft

1. A shell arrangement for a fuselage of an aircraft, the shell arrangement comprising:

a first shell portion, which extends in a curved manner in a shell peripheral direction; and

a second shell portion, which extends in a curved manner in the shell peripheral direction;

wherein, in an overlapping portion of the shell arrangement, a first end region of the first shell portion and a second end region of the second shell portion overlap each other in the shell peripheral direction;

wherein, in the overlapping portion of the shell arrangement, a first outer face of the first shell portion and a second inner face of the second shell portion are adhesively bonded to each other by an adhesive layer;

wherein an edge of the first shell portion, at which the first end region is terminated with respect to the shell peripheral direction, extends in the overlapping portion in an undulating manner in a shell longitudinal direction, the shell longitudinal direction being oriented to extend transversely relative to the shell peripheral direction;

wherein the second shell portion has, in the second end region, an inclination that is defined by a second outer face of the second shell portion, the second outer face of the second shell portion being oriented in an opposite direction to the second inner face and shaped so as to reduce a thickness of the second shell portion in the shell peripheral direction to form an edge that terminates the second end region with respect to the shell peripheral direction; and

wherein the inclination has an inclination length that is defined in the shell peripheral direction, the inclination length being in a range between 20 percent and 60 percent of an overlapping depth, the overlapping depth being defined in the shell peripheral direction.

2. The shell arrangement according to claim 1 , wherein:

the inclination has an inclination length that is defined in the shell peripheral direction, and an inclination height, which is defined by a change of the thickness; and

a relationship between the inclination length and the inclination height is between 20:1 and 40:1.

3. The shell arrangement according to claim 1 , wherein an edge of the second shell portion, which terminates the first end region of the second shell component with respect to the shell peripheral direction, extends in the overlapping portion in an undulating manner in the shell longitudinal direction.

4. The shell arrangement according to claim 1 , wherein the edge of the first shell portion forms at least one wave in the overlapping portion, the at least one wave having a wavelength in the shell longitudinal direction and an amplitude in the shell peripheral direction.

5. The shell arrangement according to claim 1 , wherein the edge of the first shell portion extends in a form of a sine wave, in a form of waves which are composed of semi-circles, or in a form of a triangular wave.

6. The shell arrangement according to claim 1 , wherein the inclination has an inclination length, as defined in the shell peripheral direction, the inclination length being in a range between 40 percent and 50 percent of an overlapping depth, the overlapping depth being defined in the shell peripheral direction.

7. The shell arrangement according to claim 1 , wherein the inclination is defined by a convex-curved outer face of the second shell portion.

8. A fuselage for an aircraft, the fuselage comprising:

a plurality of rib frames arranged spaced apart from each other along a fuselage longitudinal axis, the plurality of rib frames being arranged so as to surround the fuselage longitudinal axis in a fuselage peripheral direction;

a plurality of longitudinal carriers, which extend along the fuselage longitudinal axis and are connected, respectively, to the rib frames; and

a shell arrangement according to claim 1 ;

wherein the first and second shell portions of the shell arrangement are connected to at least one of the plurality of rib frames and extend, in the shell longitudinal direction, along the fuselage longitudinal axis and, in the shell peripheral direction, in the fuselage peripheral direction.

9. The fuselage according to claim 8 , wherein:

the inclination has an inclination length, as defined in the shell peripheral direction, and an inclination height, which is defined by a change of the thickness; and

a relationship between the inclination length and the inclination height is between 20:1 and 40:1.

10. The fuselage according to claim 8 , wherein the inclination has an inclination length that is defined in the shell peripheral direction, the inclination length being in a range between 40 percent and 50 percent of an overlapping depth, the overlapping depth being defined in the shell peripheral direction.

11. The fuselage according to claim 8 , wherein an edge of the second shell portion, which terminates the first end region of the second shell component with respect to the shell peripheral direction, extends in the overlapping portion in an undulating manner in the shell longitudinal direction.

12. The fuselage according to claim 8 , wherein the edge of the first shell portion forms at least one wave in the overlapping portion, the at least one wave having a wavelength in the shell longitudinal direction and an amplitude in the shell peripheral direction.

13. The fuselage according to claim 8 , wherein the edge of the first shell portion extends in a form of a sine wave, in a form of waves which are composed of semi-circles, or in a form of a triangular wave.

14. The fuselage according to claim 8 , wherein the inclination is defined by a convex-curved outer face of the second shell portion.