Assembly apparatus for the assembly of a fuselage section

1. An assembly apparatus for supporting a fuselage section of an aircraft or spacecraft in an adjustable assembly position, comprising:

at least one stiffening bow for detachably stiffening the fuselage section; and

a rotational support capable of rotatably supporting said stiffening bow;

wherein said stiffening bow comprises a fastening side along at least a portion of a cross-sectional contour of the fuselage section;

wherein the fastening side corresponds to a peripheral cross-sectional contour of the fuselage section and comprises a plurality of pressing elements capable of pressing against the cross-sectional contour of the fuselage section by a plurality of plastic discs; and

wherein said pressing elements are adjustable in at least one of a radial or a circumferential direction.

2. The assembly apparatus according to claim 1 , wherein at least one of a pressing force and a height of the plurality of pressing elements is adjustable.

3. The assembly apparatus according to claim 1 , wherein the rotational support comprises at least one of a plurality of rollers for supporting said stiffening bow, and wherein said stiffening bow further comprises a rolling surface for rolling on the at least one of the plurality of rollers.

4. The assembly apparatus according to claim 3 , wherein the rolling surface is curved substantially in the form of a portion of a lateral surface of at least one of a cylinder and cone.

5. The assembly apparatus according to claim 3 , further comprising a rotary drive for driving the at least one of the plurality of rollers.

6. The assembly apparatus according to claim 3 , wherein at least one of the rolling surface and the at least one roller surface comprise a serration.

7. The assembly apparatus according to claim 5 , further comprising:

an angle-of-rotation determining device capable of continuously determining an angle of rotation of the fuselage section, and

a control device for activating the rotary drive in such a way that the angle of rotation of the fuselage section coincides with an assembly-position angle of rotation corresponding to the assembly position.

8. The assembly apparatus according to claim 1 , further comprising at least one working platform capable of being arranged at least one of inside and outside of the fuselage between 1 and 2 m lower than the height of an axis of rotation of the fuselage section.

9. A method for the assembly of a fuselage section of an aircraft or spacecraft, the method comprising:

prescribing a first assembly position of the fuselage section;

stiffening the fuselage section using a detachable stiffening bow;

rotatably supporting the stiffening bow; and

turning the stiffening bow in such a way that the fuselage section rotates into the first assembly position;

wherein said stiffening bow comprises a fastening side along at least a portion of a cross-sectional contour of the fuselage section;

wherein the fastening side corresponds to a peripheral cross-sectional contour of the fuselage section, and comprises a plurality of pressing elements capable of pressing against the cross-sectional contour of the fuselage section by means of a plurality of plastic discs; and

wherein said pressing elements are adjustable in at least one of a radial, and in a circumferential direction.

10. The method according to claim 9 , wherein the stiffening bow is supported on rollers and the turning of the stiffening bow is performed by rolling of a rolling surface of the stiffening bow on the rollers.

11. The method according to claim 9 , further comprising attaching a first frame element in the fuselage section after the turning into the first assembly position.

12. The method according to claim 9 , further comprising:

prescribing a second assembly position of the fuselage section;

turning the stiffening bow in such a way that the fuselage section rotates into the second assembly position; and

attaching a second frame element in the fuselage section after the turning into the second assembly position.

13. The method according to claim 9 , further comprising detaching the stiffening bow from the fuselage section.