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:
Mar. 05, 2019

Filed:

Jul. 22, 2016
Applicant:

Airbus Operations Gmbh, Hamburg, DE;

Inventors:

Paul Jorn, Hamburg, DE;

Karim Grase, Hamburg, DE;

Assignee:

Airbus Operations GmbH, Hamburg, DE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 1/10 (2006.01); B32B 7/08 (2019.01); B32B 1/00 (2006.01); B32B 3/28 (2006.01); B32B 5/18 (2006.01); B64C 1/06 (2006.01); B32B 5/02 (2006.01); B32B 5/24 (2006.01); B32B 3/06 (2006.01); B32B 3/26 (2006.01); B64C 1/00 (2006.01);
U.S. Cl.
CPC ...
B64C 1/10 (2013.01); B32B 1/00 (2013.01); B32B 3/06 (2013.01); B32B 3/263 (2013.01); B32B 3/28 (2013.01); B32B 5/02 (2013.01); B32B 5/18 (2013.01); B32B 5/245 (2013.01); B32B 7/08 (2013.01); B64C 1/069 (2013.01); B32B 2250/03 (2013.01); B32B 2260/021 (2013.01); B32B 2260/023 (2013.01); B32B 2260/046 (2013.01); B32B 2262/101 (2013.01); B32B 2262/106 (2013.01); B32B 2266/0242 (2013.01); B32B 2307/558 (2013.01); B32B 2307/56 (2013.01); B32B 2605/18 (2013.01); B32B 2607/00 (2013.01); B64C 2001/0072 (2013.01);
Abstract

A pressure bulkhead () for an aircraft fuselage () having a sandwich structure () which defines a central axis () and which extends between a circumferential edge area (), wherein the sandwich structure () includes an inner cover layer (), an outer cover layer (), and a core layer (), which extends between the inner and outer cover layers () and connects them. The object of providing a pressure bulkhead () for an aircraft fuselage () which, even in the case of larger fuselage diameters, can particularly effectively absorb the occurring pressure forces and which can also be built with minimal weight, is achieved in that, between the inner and the outer cover layers (), in addition to the core layer (), a support structure () is provided, which is connected to the cover layers () and which extends from the inner cover layer () to the outer cover layer (), and in that the support structure () comprises at least one layer () which, viewed in a cross section () parallel to the central axis (), extends from a first section () of the edge area () to an opposite second section () of the edge area ().


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