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.:
Date of Patent:
Nov. 19, 2019
Filed:
Sep. 18, 2017
Applicant:
Airbus Operations Gmbh, Hamburg, DE;
Inventors:
Assignee:
Airbus Operations GmbH, , DE;
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B32B 7/02 (2019.01); B32B 7/12 (2006.01); B32B 37/12 (2006.01); B32B 37/14 (2006.01); B32B 3/12 (2006.01); B32B 3/30 (2006.01); B32B 5/18 (2006.01); B32B 7/04 (2019.01); B32B 7/14 (2006.01); B32B 15/00 (2006.01); B32B 15/04 (2006.01); B32B 15/08 (2006.01); B32B 15/20 (2006.01); B32B 25/00 (2006.01); B32B 25/14 (2006.01); B32B 1/04 (2006.01); B32B 3/00 (2006.01); B32B 3/02 (2006.01); B32B 3/06 (2006.01); B32B 3/22 (2006.01); B32B 3/26 (2006.01); B32B 3/28 (2006.01); B32B 7/05 (2019.01); F16B 11/00 (2006.01);
U.S. Cl.
CPC ...
B32B 7/02 (2013.01); B32B 1/04 (2013.01); B32B 3/00 (2013.01); B32B 3/02 (2013.01); B32B 3/06 (2013.01); B32B 3/12 (2013.01); B32B 3/22 (2013.01); B32B 3/26 (2013.01); B32B 3/28 (2013.01); B32B 3/30 (2013.01); B32B 5/18 (2013.01); B32B 7/04 (2013.01); B32B 7/05 (2019.01); B32B 7/12 (2013.01); B32B 7/14 (2013.01); B32B 15/00 (2013.01); B32B 15/046 (2013.01); B32B 15/08 (2013.01); B32B 15/20 (2013.01); B32B 25/00 (2013.01); B32B 25/14 (2013.01); B32B 37/1292 (2013.01); B32B 37/144 (2013.01); F16B 11/006 (2013.01); B32B 2255/205 (2013.01); B32B 2255/26 (2013.01); B32B 2255/28 (2013.01); B32B 2605/00 (2013.01); B32B 2605/18 (2013.01);
Abstract
In order to provide a new and improved bonding arrangement, especially for use in an aircraft or spacecraft, which is designed to overcome problems of bonding arrangements under Mode I loading stress and which is designed or configured particularly to create a bond design which is incapable of locally loading the adhesive bond above the peel strength, a bonding arrangement is disclosed with a coating structure, which is split into a plurality of neighboring structural elements spatially separated from each other, and at least one supporting member is provided, which comprises a plurality of recesses receiving the structural elements in operating position.