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:
Oct. 18, 2016

Filed:

Sep. 30, 2014
Applicant:

Airbus Operations (Sas), Toulouse, FR;

Inventors:

Francois Peyruseigt, Toulouse, FR;

Thierry Gaches, Castelnau d'Estrefonds, FR;

Mathieu Kaleta, Toulouse, FR;

Nicolas Voyer, Toulouse, FR;

Delphine Chamaillard, Toulouse, FR;

Assignee:

Airbus Operations (SAS), Toulouse, FR;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 29/06 (2006.01); B64D 29/00 (2006.01); B64C 1/00 (2006.01); B64D 27/26 (2006.01); B64D 29/02 (2006.01); B64C 7/02 (2006.01);
U.S. Cl.
CPC ...
B64D 29/00 (2013.01); B64C 1/0009 (2013.01); B64C 7/02 (2013.01); B64D 27/26 (2013.01); B64D 29/02 (2013.01); B64D 29/06 (2013.01);
Abstract

An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.


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