Structural element, method for manufacturing a structural element and use of a structural element for an aircraft hull

1. A structural element, comprising:

a carrier element made of metal consisting of at least one skin panel and at least one stiffening element secured to the at least one skin panel;

a reinforcing element embedded in the carrier element is made of a first material having a first strength value such that the reinforcing element reinforces the carrier element; and

a sheathing element comprising fibers being made of a second material, different than the first material, the second material having a second strength value less than the first strength value, wherein the reinforcing element is enveloped by the sheathing element and is embedded in the carrier element, such that crack initiation in the reinforcing element is reduced.

2. The structural element of claim 1 , wherein the carrier element is a stringer element or a frame element for an aircraft.

3. The structural element of claim 1 , wherein the carrier element is a skin panel with a stringer element, a stringer element and a frame element or a frame element secured thereto.

4. The structural element of claim 3 , wherein the skin panel is integrally provided with the a stringer element, a stringer element and a frame element or a frame element secured thereto.

5. The structural element of claim 3 , wherein the carrier element is a skin panel with a stringer element, a stringer element and a frame element, or a frame element screwed, riveted or adhesively bonded thereto.

6. The structural element of claim 1 , wherein the sheathing element has a thickness of at least 0.05 mm.

7. The structural element of claim 1 , wherein the reinforcing element includes a metal material.

8. The structural element of claim 1 , wherein the carrier element is made using a metal different than the first material of the reinforcing element.

9. The structural element of claim 8 , wherein the first material of the reinforcing element comprises a metal alloy.

10. The structural element of claim 1 , wherein the sheathing element includes a polymeric material.

11. The structural element of claim 1 , wherein the sheathing element includes an organic material.

12. The structural element of claim 1 , wherein the sheathing element includes a metal alloy.

13. The structural element of claim 1 , wherein the fibers have a length of at least 20 mm.

14. The structural element of claim 1 , wherein the fibers are unidirectionally aligned.

15. The structural element of claim 1 , wherein the fibers are braided.

16. The structural element of claim 1 , wherein the reinforcing element is secured to the carrier element by welding.

17. An aircraft hull comprising the structural element of claim 1 .

18. A method for manufacturing a structural element comprising a carrier element, a reinforcing element for reinforcing the carrier element and a sheathing element, wherein the carrier element is made of metal, consisting of at least one skin panel and at least one stiffening element secured to the at least one skin panel, the method comprising:

enveloping the reinforcing element with the sheathing element;

embedding the reinforcing element and the sheathing element into the carrier element;

making the reinforcing element on the one hand and the sheathing element on the other hand out of different materials, the sheathing element comprising fibers; and

selecting strength values of the material of the sheathing element less than strength values of the material of the reinforcing element, such that crack initiation in the reinforcing element is reduced.

19. The method of claim 18 , wherein the carrier element is made of metal by forming the carrier element as an extruded profile.

20. The method of claim 18 , wherein the carrier element is made of metal by milling from a solid body.