The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Apr. 28, 2020

Filed:

Aug. 28, 2015
Applicant:

Airbus Operations Gmbh, Hamburg, DE;

Inventors:

Domenico Furfari, Hamburg, DE;

Nikolaus Ohrloff, Hamburg, DE;

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64F 5/10 (2017.01); B64C 1/26 (2006.01); B64C 1/12 (2006.01); C21D 10/00 (2006.01); F16B 5/04 (2006.01); B21J 15/14 (2006.01); C21D 7/08 (2006.01); F16B 17/00 (2006.01);
U.S. Cl.
CPC ...
B64F 5/10 (2017.01); B21J 15/142 (2013.01); B64C 1/12 (2013.01); B64C 1/26 (2013.01); C21D 7/08 (2013.01); C21D 10/00 (2013.01); C21D 10/005 (2013.01); F16B 5/04 (2013.01); F16B 17/008 (2013.01);
Abstract

A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes inducing compressive residual stresses in a first area of the first joint region for preventing cracks by applying parallel crack retarding regions formed as stripes in the first area, drilling fastener holes in the first and second areas of the first. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint.


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