Aircraft fuselage structure and method for producing it

1. An aircraft fuselage structure comprising:

frames running in a circumferential direction of the fuselage;

stringers running in a longitudinal direction of the fuselage; and

a skin which is arranged on the frames and the stringers and outwardly seals the aircraft fuselage in a compression-proof manner;

wherein the aircraft fuselage structure comprises:

a plurality of prefabricated integral units which each run in the circumferential direction of a fuselage segment, and

a plurality of skin elements comprising stringers and a skin, and wherein each of the integral units further comprises at least:

a frame; and

a plurality of force-transmission combs for connection to the skin elements,

wherein the plurality of skin elements are fixed to the plurality of prefabricated integral units in a frictional and/or interlocking manner via the plurality of force-transmission combs,

wherein the force-transmission combs formed on the integral units are directly connected to the skin elements, and

wherein a plurality of glass-fiber and aluminum composite tabs are provided at a plurality of connecting points of the skin elements and the plurality of force-transmission combs, and wherein the plurality of glass-fiber and aluminum composite tabs are capable of compensating for different thermal coefficients of expansion of light metal alloys and fiber-reinforced plastics.

2. The aircraft fuselage structure according to claim 1 , wherein the integral units are each prefabricated in one piece.

3. The aircraft fuselage structure according to claim 1 , wherein the integral units each have a main body running in the plane of a fuselage segment and forming the frame, and connecting elements which protrude therefrom and are adapted for connection to skin elements comprising stringers and skin.

4. The aircraft fuselage structure according to claim 1 , wherein the integral units run in an annularly closed manner over the entire circumference of a fuselage segment.

5. The aircraft fuselage structure according to claim 1 , wherein the integral units contain a hold cross member.

6. The aircraft fuselage structure according to claim 1 , wherein the integral units contain a hatrack stiffening means.

7. The aircraft fuselage structure according to claim 1 , wherein the integral units contain a main deck cross member.

8. The aircraft fuselage structure according to claim 5 , wherein the integral units contain supporting elements for the cross members.

9. The aircraft fuselage structure according to claim 1 , wherein the integral units are produced from fiber-reinforced plastic.

10. The aircraft fuselage structure according to claim 9 , wherein the integral units are produced from carbon-fiber-reinforced plastic.

11. The aircraft fuselage structure according to claim 1 , wherein the aircraft fuselage structure is assembled from a plurality of prefabricated integral units and a plurality of prefabricated skin elements connected together.

12. The aircraft fuselage structure according to claim 11 , wherein the connecting elements are formed by a force-transmission comb comprising teeth protruding from the main body of the integral unit to which the skin elements are fixed.

13. A method for producing an aircraft fuselage structure with frames running in the circumferential direction, stringers running in the longitudinal direction and a skin which is arranged thereon and outwardly seals the aircraft fuselage in a compression-proof manner, the method comprising the following steps:

producing one-piece integral units each comprising at least a frame of a fuselage segment, and a plurality of force-transmission combs for connection to skin elements;

producing the skin elements comprising at least a skin and stringers;

arranging the integral units on an installation apparatus;

providing a plurality of glass-fiber and aluminum composite tabs, at a plurality of connecting points of the skin elements and the plurality of force-transmission combs; and

mounting and connecting the skin elements to the integral units in a frictional and/or interlocking manner via the plurality of force-transmission combs such that the force-transmission combs formed on the integral units are directly connected to the skin elements; and

wherein the glass-fiber and aluminum composite tabs are capable of compensating for different thermal coefficients of expansion of light metal alloys and fiber-reinforced plastics.

14. The method according to claim 13 , wherein frame angle brackets formed on the integral units are riveted to the skin elements.

15. The method according to claim 13 , wherein the skin elements are completed with stringers, and window frames and door frames, prior to installation.