Reinforced vehicle structural part and vehicle

Patent metadata

Field	Value
Publication number	US-10035577-B2
Application number	US-201314078595-A
Country	US
Kind code	B2
Filing date	Nov 13, 2013
Priority date	Nov 15, 2012
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

A vehicle structure component reinforced by means of an area, a vehicle including such a vehicle structure component, and a corresponding method to reinforce a vehicle structure component are proposed. The area includes a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction being vertically aligned to the first direction, wherein the ratio of the compressive stress in the first direction and the compressive or tensile residual stress lies between −0.2 and +1.0. Hence, the propagation direction of cracks in such areas is diverted, faster pressure equalization takes place, and further crack propagation is inhibited.

First claim

The invention claimed is:

1. An aircraft structural part comprising:
a first area in which there is a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction perpendicular to the first direction;
wherein the first area is configured for deflecting a propagation direction of cracks from an initial propagation direction thereby resulting in U-shaped or L-shaped cracks so as to protect a second area of the aircraft structural part from cracks, and
wherein a ratio of the compressive residual stress in the first direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +1.0.

2. The aircraft structural part according to claim 1 , wherein the compressive residual tension in the first direction and the compressive or tensile residual tension in the second direction are produced by laser shock peening.

3. The aircraft structural part according to claim 1 , wherein the first area extends from a first surface region of the aircraft structural part into the aircraft structural part over 30% to 100% of the material thickness.

4. The aircraft structural part according to claim 1 , wherein the first area is configured in the shape of a strip.

5. The aircraft structural part according to claim 4 , wherein the first area is configured in the shape of a straight strip.

6. The aircraft structural part according to claim 4 , wherein the first area is configured in the shape of a strip comprising at least one curve.

7. The aircraft structural part according to claim 4 , wherein the strip has a width of 50 mm to 10 mm.

8. The aircraft structural part according to claim 1 , configured to absorb a tensile load which is caused by the driving operation of an aircraft comprising the aircraft structural part;
wherein the compressive residual stress in the first direction comprises a component in the direction of the tensile load which component is configured to reduce the tensile load.

9. The aircraft structural part according to claim 1 , comprising:
a second area in which there is a compressive residual stress in a third direction and a compressive or tensile residual stress in a fourth direction perpendicular to the third direction;
wherein the ratio of the compressive residual stress in the third direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +1.0.

10. The aircraft structural part according to claim 9 , wherein the first area and the second area are of the same shape and have longitudinal extensions which are arranged parallel with respect to each other.

11. The aircraft structural part according to claim 10 , wherein the first area and the second area are at a distance of 50 cm to 10 cm from one another.

12. The aircraft structural part according to claim 9 , wherein the longitudinal extensions of the first area and the second area are not arranged mutually parallel.

13. An aircraft comprising an aircraft structural part comprising:
a first area in which there is a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction perpendicular to the first direction;
wherein the first area is configured for deflecting a propagation direction of cracks from an initial propagation direction thereby resulting in U-shaped or L-shaped cracks so as to protect a second area of the aircraft structural part from cracks, and
wherein a ratio of the compressive residual stress in the first direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +1.0.

14. The aircraft structural part according to claim 1 , wherein the ratio of the compressive residual stress in the first direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +0.8.

15. The aircraft structural part according to claim 1 , wherein the ratio of the compressive residual stress in the first direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +0.6.

16. The aircraft structural part according to claim 1 , wherein the ratio of the compressive residual stress in the first direction and the compressive or tensile residual stress in the second direction lies between −0.2 and +0.4.

Assignees

• Airbus Operations Gmbh
• Eads Deutschland Gmbh

Inventors

• Furfari Domenico
• Hombergsmeier Elke

Classifications

• C21D7/06

  by shot-peening or the like · CPC title

• B64C2001/0081

  from metallic materials · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• C21D10/005

  by laser shock processing · CPC title

• Y10T29/49622

  Vehicular structural member making · CPC title