Structural arrangement, aircraft or spacecraft and method

1. A structural arrangement, in particular for an aircraft or spacecraft, comprising:

a box structure;

a first fibre portion which extends in a first plane;

a second fibre portion which extends in a second plane which intersects the first plane, the first and the second fibre portion being interconnected at a crossing point thereof, wherein the first fibre portion comprises a first portion on one side of the crossing point and a second portion on the other side of the crossing point, the first portion of the first fibre portion being integrated into a first portion of the box structure and the second portion of the first fibre portion being integrated into a second portion of the box structure, and wherein the second fibre portion forms, on one side of the crossing point, an inner web inside the box structure and, on the other side of the crossing point, an outer web outside the box structure;

a supporting element which is connected to the inner web; and

an attachment point for introduction of a first load into the outer web;

wherein the second fibre portion guides the first load which is introduced at the attachment point from the attachment point into the supporting element, and the first fibre portion simultaneously transfers a second load between the first and the second portion of the box structure.

2. The structural arrangement according to claim 1 , wherein the first and/or the second portion of the first fibre portion is glued into the first and/or the second portion of the box structure, and/or the inner web is integrated, in particular glued, into the supporting element, the supporting element preferably being designed as a rib, transverse web or spar and/or being connected to the box structure.

3. The structural arrangement according to claim 1 , wherein the first portion, second portion, inner and/or outer web tapers in a direction away from the crossing point.

4. The structural arrangement according to claim 1 , wherein the first and the second plane are substantially perpendicular to each other.

5. The structural arrangement according to claim 1 , wherein the first and/or the second fibre portion is embedded in a matrix.

6. A method for producing a structural arrangement, in particular the structural arrangement according to claim 1 , in particular in the aviation and aerospace industry, the method comprising:

providing a box structure;

providing a first fibre portion which extends in a first plane;

providing a second fibre portion which extends in a second plane which intersects the first plane;

interconnecting the first and the second fibre portion at a crossing point thereof;

integrating a first portion of the first fibre portion on one side of the crossing point into a first portion of the box structure and integrating a second portion of the first fibre portion on the other side of the crossing point into a second portion of the box structure, the second fibre portion forming, on one side of the crossing point, an inner web inside the box structure and, on the other side of the crossing point, an outer web outside the box structure;

connecting the inner web to a supporting element; and

providing an attachment point for introduction of a first load into the outer web, the second fibre portion guiding the first load which is introduced at the attachment point from the attachment point into the supporting element, and the first fibre portion simultaneously transferring a second load between the first and the second portion of the box structure.

7. The structural arrangement according to claim 1 , wherein the first and the second portion are part of the same fibre or different fibres.

8. The structural arrangement according to claim 7 , wherein the fibres are interwoven with other fibres in three dimensions and/or the different fibres are interwoven with other fibres in two and a half dimensions.

9. The structural arrangement according to claim 7 , wherein the different fibres are sewn together, interwoven or interlaced by fibres and/or the different fibres are adhesively bonded to each other in particular by a thermoplastic strand, a thread coated with thermoplastic material, or an adhesive tape.

10. The structural arrangement according claim 1 , wherein the attachment point is designed as an eye, metal fitting, rivet field, bonded joint and/or weld.

11. The structural arrangement according to claim 10 , wherein the eye is designed for mounting a control member, in particular a flap carriage, a lever and/or a coupling rod.

12. An aircraft or spacecraft comprising a structural arrangement according to claim 1 .

13. A vehicle according to claim 12 , wherein a control flap comprises the structural arrangement.

14. The vehicle according to claim 12 , wherein an adjusting member arranged at an aerofoil or control surface acts on an eye of the structural arrangement.

15. The vehicle according to claim 14 , wherein the adjusting member is designed as a flap carriage which is displaceably arranged at the aerofoil or control surface and is in engagement with the eye of the structural arrangement.