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:
Nov. 17, 2015

Filed:

Feb. 11, 2009
Applicant:

Axel Sauermann, Helmste-Deinste, DE;

Inventor:

Axel Sauermann, Helmste-Deinste, DE;

Assignee:

Airbus Operations GmbH, Hamburg, DE;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64C 1/06 (2006.01); B29B 13/02 (2006.01); B29C 65/50 (2006.01); B29C 65/00 (2006.01); B29C 65/48 (2006.01); B29K 71/00 (2006.01); B29K 101/12 (2006.01); B29K 105/06 (2006.01); B29K 307/00 (2006.01); B29L 31/30 (2006.01); B64C 1/00 (2006.01);
U.S. Cl.
CPC ...
B64C 1/069 (2013.01); B29B 13/025 (2013.01); B29C 65/4815 (2013.01); B29C 65/5042 (2013.01); B29C 66/1142 (2013.01); B29C 66/43 (2013.01); B29C 66/43441 (2013.01); B29C 66/5221 (2013.01); B29C 66/721 (2013.01); B29C 66/7212 (2013.01); B29C 65/483 (2013.01); B29C 66/54 (2013.01); B29C 66/71 (2013.01); B29C 66/73921 (2013.01); B29C 66/73941 (2013.01); B29K 2071/00 (2013.01); B29K 2101/12 (2013.01); B29K 2105/06 (2013.01); B29K 2307/00 (2013.01); B29L 2031/3082 (2013.01); B64C 2001/0072 (2013.01); Y02T 50/433 (2013.01);
Abstract

The invention relates to a method of connecting two fuselage sections () formed by a fiber-reinforced plastics material, in particular wound fuselage sections () for aircraft fuselage cells, having a multiplicity of stringers () arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (), with the formation of a transverse joint (). In order to be able in particular to join together wound CFRP fuselage sections so that simple tolerance compensation is made possible in a continuous, industrial production process, the method according to the invention comprises the following steps: aligning a first and a second fuselage section () with respect to one another, heating and adapting at least one transverse butt strap (), formed by a fiber-reinforced thermoplastic material, in such a way that tolerance compensation between differing cross-sectional geometries of the first and second fuselage sections () is made possible, or heating at least one end region () of a second fuselage section () formed by a fiber-reinforced thermoplastic material, and joining together the two fuselage sections ().


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