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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.

Patent No.:

US 10301003 B1

PDFFull Text
Date of Patent:
May. 28, 2019

Filed:

Apr. 28, 2016

Method for connecting fiber-reinforced structural components

Applicant:

Airbus Operations Gmbh, Hamburg, DE;

Inventors:

Paul J Jörn, Hamburg, DE;

Markus Müller, Friedrichshafen, DE;

Assignee:

AIRBUS OPERATIONS GMBH, Hamburg, DE;

Attorney:

Lorenz & Kopf LLP

Primary Examiner:

Jermie E Cozart

Int. Cl.
CPC ...
B29C 65/00 (2006.01); B29C 65/56 (2006.01); B29C 65/60 (2006.01); B64C 1/06 (2006.01); B64F 5/10 (2017.01); B64C 1/00 (2006.01); B29K 301/00 (2006.01); B29K 305/00 (2006.01); B29K 307/04 (2006.01); B29K 309/02 (2006.01);
U.S. Cl.
CPC ...
B64C 1/064 (2013.01); B29C 65/562 (2013.01); B29C 65/604 (2013.01); B29C 66/0242 (2013.01); B29C 66/02242 (2013.01); B29C 66/1122 (2013.01); B29C 66/21 (2013.01); B29C 66/41 (2013.01); B29C 66/72141 (2013.01); B29C 66/73921 (2013.01); B64C 1/061 (2013.01); B64C 1/066 (2013.01); B64F 5/10 (2017.01); B29C 65/60 (2013.01); B29C 66/7212 (2013.01); B64C 2001/0072 (2013.01); Y02T 50/43 (2013.01); Y02T 50/46 (2013.01); Y10T 29/49801 (2015.01); Y10T 29/49865 (2015.01); Y10T 29/49963 (2015.01); Y10T 29/49964 (2015.01);
Abstract

This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.

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