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:
Feb. 27, 2018

Filed:

Aug. 26, 2014
Applicant:

Airbus Operations Gmbh, Hamburg, DE;

Inventors:

Pierre C. Zahlen, Stade, DE;

Johannes Born, Bremen, DE;

Lars Meyer, Hamburg, DE;

Gregor Baumbach, Hamburg, DE;

Claus Hanske, Hamburg, DE;

Jens Prowe, Hamburg, DE;

Johan Oentoro, Hamburg, DE;

M. Ichwan Zuardy, Hamburg, DE;

Wouter Brok, Pölitz, DE;

Martin Metten, Seevetal, DE;

Assignee:

Airbus Operations GmbH, Hamburg, DE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B32B 3/24 (2006.01); B32B 3/26 (2006.01); B32B 5/18 (2006.01); B32B 5/24 (2006.01); B32B 5/26 (2006.01); B32B 5/28 (2006.01); B32B 7/04 (2006.01); B60J 1/00 (2006.01); B64C 1/14 (2006.01); B29C 70/02 (2006.01); B32B 3/08 (2006.01); B32B 37/16 (2006.01); B32B 37/30 (2006.01); B32B 37/12 (2006.01); B32B 38/04 (2006.01); B29C 70/30 (2006.01); B29L 7/00 (2006.01); B32B 3/02 (2006.01); B29C 70/54 (2006.01); B29L 9/00 (2006.01); B29L 31/30 (2006.01); B29L 31/00 (2006.01); B64C 1/12 (2006.01); B64C 1/00 (2006.01);
U.S. Cl.
CPC ...
B64C 1/1484 (2013.01); B29C 70/026 (2013.01); B32B 3/08 (2013.01); B32B 3/263 (2013.01); B32B 3/266 (2013.01); B32B 5/18 (2013.01); B32B 5/245 (2013.01); B32B 7/04 (2013.01); B32B 37/16 (2013.01); B32B 37/30 (2013.01); B64C 1/1492 (2013.01); B29C 70/023 (2013.01); B29C 70/30 (2013.01); B29C 70/545 (2013.01); B29C 2793/0018 (2013.01); B29C 2793/0081 (2013.01); B29L 2007/002 (2013.01); B29L 2009/00 (2013.01); B29L 2031/005 (2013.01); B29L 2031/30 (2013.01); B29L 2031/3082 (2013.01); B32B 3/02 (2013.01); B32B 5/26 (2013.01); B32B 5/28 (2013.01); B32B 38/04 (2013.01); B32B 2250/03 (2013.01); B32B 2250/24 (2013.01); B32B 2250/40 (2013.01); B32B 2250/44 (2013.01); B32B 2260/00 (2013.01); B32B 2266/08 (2013.01); B32B 2305/022 (2013.01); B32B 2305/07 (2013.01); B32B 2605/00 (2013.01); B32B 2605/006 (2013.01); B32B 2605/18 (2013.01); B60J 1/00 (2013.01); B60J 1/004 (2013.01); B60J 1/006 (2013.01); B64C 1/12 (2013.01); B64C 1/14 (2013.01); B64C 2001/0072 (2013.01); Y02T 50/433 (2013.01); Y10T 428/239 (2015.01); Y10T 428/24322 (2015.01); Y10T 428/24521 (2015.01);
Abstract

The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core.


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