Intercostal for aircraft

1. An intercostal for an aircraft for dissipating a load from a first frame onto one or both of a second frame and a skin of the aircraft, the intercostal comprising:

a framework and a frame region;

wherein the frame region has a first flange, a second flange, an internal belt, and an external belt;

wherein the frame region is arranged to be attached to the first frame, the second frame, or the skin;

wherein the frame region encloses a framework region and wherein the framework is provided in the frame region;

wherein the first flange is provided for attachment to the first frame;

wherein the second flange is provided for attachment to the second frame; and

wherein a thrust panel, for transmitting a load onto the framework, is provided between at least one of the first and second flanges and at least one of the external belt and the internal belt.

2. The intercostal as claimed in claim 1 ,

wherein the internal belt points toward an inner side of a fuselage of the aircraft if positioned between the first and second frame;

wherein the external belt is positioned neighboring the skin of the aircraft if positioned between the first and the second frame; and

wherein the internal belt and external belt are adapted to couple the first frame and the second frame if the intercostal is positioned between the first frame and the second frame.

3. The intercostal as claimed in claim 2 ,

wherein the framework has at least one rod which is positioned between the internal belt and the external belt;

wherein the at least one rod is positioned between the internal belt and external belt in such a manner that a bending moment which is applied to at least one of the first and second frames is distributed in such a manner that a first part of the force resulting from the bending moment is conducted along the internal belt and a second part of the force resulting from the bending moment is transmitted onto the skin, if the rod is positioned between the first and the second frame neighboring the skin.

4. The intercostal as claimed in claim 3 ,

wherein the at least one rod is arranged such that a triangular geometry is formed by the framework.

5. The intercostal as claimed in claim 2 ,

wherein the external belt is tailored to be mounted essentially pressed along the external skin of the aircraft, a support of the external skin being made possible.

6. The intercostal as claimed in claim 1 ,

wherein at least one opening, which has dimensions for passage of a system line, is provided in the framework region.

7. The intercostal as claimed in claim 1 ,

wherein holes are provided in the frame region for receiving rivets.

8. The intercostal as claimed in claim 1 ,

wherein the framework is implemented such that a load on the first frame is dissipated onto the second frame and the external skin of the aircraft, the first and the second frames being coupled.

9. An aircraft comprising:

an intercostal for dissipating a load from a first frame onto one or both of a second frame and skin of the aircraft, wherein the intercostal comprises a framework and a frame region;

wherein the frame region has a first flange, a second flange, an internal belt, and an external belt;

wherein the frame region is arranged to be attached to the first frame, the second frame, or the skin;

wherein the frame region encloses a framework region and wherein the framework is provided in the frame region;

wherein the first flange is provided for attachment to the first frame;

wherein the second flange is provided for attachment to the second frame; and

wherein a thrust panel, for transmitting a load onto the framework, is provided between at least one of the first and second flanges and at least one of the external belt and the internal belt.

10. An intercostal for dissipating a load from a first frame onto one or both of a second frame and a skin of an aircraft, the intercostal comprising:

a framework formed from an internal belt, a first flange, an external belt, and a second flange;

a first rod spanning from a first portion of the framework to a second portion of the framework to separate the framework into a first intermediate space and a second intermediate space;

a thrust panel substantially filling said first intermediate space;

wherein the first flange is matable to the first frame, the second flange is matable the second frame, and the external belt is matable to the skin of the aircraft.

11. The intercostal of claim 10 , wherein the first portion of the framework is located along the internal belt and the second portion of the framework is located along the external belt.

12. The intercostal of claim 10 , wherein the first portion of the framework is located along the external belt and the second portion of the framework is located at the intersection of the internal belt and the first flange.

13. The intercostal of claim 10 , further comprising a second rod spanning from a third portion of the framework to a fourth portion of the framework to separate the framework into the first intermediate space, second intermediate space, and a third intermediate space.

14. The intercostal of claim 13 , wherein the first portion of the framework and the third portion of the framework are the same location.

15. The intercostal of claim 13 , further comprising a third rod spanning from a fifth portion of the framework to a sixth portion of the framework to separate the framework into the first intermediate space, second intermediate space, third intermediate space, and a fourth intermediate space.

16. The intercostal of claim 15 , further comprising a thrust panel filling said fourth intermediate space.

17. The intercostal of claim 15 , wherein the fourth portion of the framework and the fifth portion of the framework are the same location.

18. The intercostal of claim 10 , further comprising a reinforcement rib associated with said internal belt.

19. The intercostal of claim 10 , wherein the first rod is arranged such that a triangular geometry is created between the first rod, the internal belt, and the first flange.