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:
Jan. 16, 2018

Filed:

Nov. 23, 2016
Applicant:

The Boeing Company, Chicago, IL (US);

Inventors:

Sergey D. Barmichev, Kirkland, WA (US);

David W. Kirkbride, Allyn, WA (US);

Mithra M. K. V. Sankrithi, Lake Forest Park, WA (US);

Assignee:

The Boeing Company, Chicago, IL (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64D 27/02 (2006.01); B64C 25/04 (2006.01); B64C 3/32 (2006.01); B64D 27/26 (2006.01); B64D 29/02 (2006.01); B64D 29/04 (2006.01); B64C 25/34 (2006.01); B64D 27/00 (2006.01);
U.S. Cl.
CPC ...
B64D 27/26 (2013.01); B64C 3/32 (2013.01); B64C 25/04 (2013.01); B64C 25/34 (2013.01); B64D 27/02 (2013.01); B64D 29/02 (2013.01); B64D 29/04 (2013.01); B64D 2027/005 (2013.01); B64D 2027/262 (2013.01); B64D 2027/264 (2013.01); Y02T 50/66 (2013.01);
Abstract

An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.


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