Reinforcing element for a structural profile, structural arrangement, aircraft or spacecraft and method for producing a structural arrangement

Patent metadata

Field	Value
Publication number	US-11518488-B2
Application number	US-201916579999-A
Country	US
Kind code	B2
Filing date	Sep 24, 2019
Priority date	Oct 22, 2018
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

First claim

The invention claimed is:

1. A structural arrangement, comprising:
a round, oval or elliptical structural profile; and
a reinforcing element which locally surrounds the structural profile, wherein the reinforcing element comprises:
a fiber structure having a hollow-cylindrical, helically wound mesh of fiber strands and forming an inner shell surface formed to receive the structural profile; and
a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material

wherein the matrix material of the reinforcing element is shrunk for an application of a tensile stress and in this manner is frictionally connected to the structural profile,
wherein the reinforcing element has a receiver which is coupled to the fiber structure and which is formed to transmit axial loads onto the fiber structure.

2. The structural arrangement according to claim 1 , wherein the structural profile comprises a round, oval or elliptical structural tube.

3. The structural arrangement according to claim 1 , wherein the mesh of fiber strands is embedded jointly into the matrix material, or wherein each fiber strand is embedded individually into the matrix material and thus forms a composite thread, wherein the mesh is formed as a mesh of composite threads.

4. The structural arrangement according to claim 1 , wherein the round, oval or elliptical structural profile comprises a structural tube.

5. The structural arrangement according to claim 1 , wherein the reinforcing element is formed and arranged for stiffening the structural profile.

6. The structural arrangement according to claim 5 , wherein the reinforcing element is formed and arranged for local bending stiffening of the structural profile.

7. The structural arrangement according to claim 1 , wherein the receiver is provided coupled in a firmly bonded manner via the matrix material to the fiber structure.

8. The structural arrangement according to claim 7 , wherein the receiver is embedded in the matrix material or welded thereto.

9. The structural arrangement according to claim 1 , wherein the fiber structure is configured such that the mesh of fiber strands axially lengthens and radially contracts during axial tensile loading so that a frictional connection with the structural profile is automatically strengthened.

10. An aircraft or spacecraft, with a structural arrangement according to claim 1 , wherein the structural profile is formed as a structural tube bound on a primary structure of the aircraft or spacecraft for binding at least one component on the primary structure.

11. The aircraft or spacecraft according to claim 10 , wherein the structural tube is arranged axially on a fuselage structure of the aircraft or spacecraft.

12. The aircraft or spacecraft according to claim 10 , wherein at least one of the at least one component is bound via the reinforcing element on the structural tube or the structural tube is bound via the reinforcing element on the primary structure.

13. The aircraft or spacecraft according to claim 10 , wherein the fiber structure is configured for dimensionally stable transmission of conventional flight loads by a frictional connection applied with the shrinking of the matrix material to the structural tube.

14. The aircraft or spacecraft according to claim 10 , wherein the fiber structure is configured for shape-changing transmission of axial overloads, to the structural profile by axial lengthening and radial contraction.

15. The aircraft or spacecraft according to claim 14 , wherein said axial overloads comprise crash loads.

16. A method for producing the structural arrangement according to claim 1 , comprising the steps:
arranging the unshrunk reinforcing element on the structural profile in such a manner that the inner shell surface locally surrounds the structural profile;
performing a tolerance equalization by displacing the reinforcing element along the structural profile into a final position: and
heating the reinforcing element for fastening the inner shell surface to the structural profile by shrinking the matrix material.

17. The method according to claim 16 , wherein the reinforcing element is formed for binding a component on the structural profile, wherein performing the tolerance equalization comprises coupling the component to the reinforcing element and a final positioning of the component in its installation position so that the component is bound on the structural profile by heating the reinforcing element in the installation position.

Assignees

• Airbus Operations Gmbh

Inventors

• Benthien Hermann
• Soeffker Axel

Classifications

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G1/22

  Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles · CPC title

• F16L57/00

  Protection of pipes or objects of similar shape against external or internal damage or wear ({protection under water F16L1/123;} supporting of pipes inside other pipes or sleeves F16L7/00; used in connection with end fittings of hoses F16L35/00; protection of pipes or pipe fittings against corrosion or incrustation F16L58/00; protection thereof during transport B65D59/00) · CPC title

• B64C2001/0054

  Fuselage structures substantially made from particular materials · CPC title

• B64D11/04

  Galleys · CPC title