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. 20, 2020

Filed:

Apr. 24, 2018
Applicant:

The Boeing Company, Chicago, IL (US);

Inventors:

Lennard T. Baron, Lake Stevens, WA (US);

Todd W. Schulze, Everett, WA (US);

Theodore N. Rydell, Bothell, WA (US);

Timothy W. Purcell, Edmonds, WA (US);

Patrick J. Mulvaney, Everett, WA (US);

Assignee:

The Boeing Company, Chicago, IL (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 17/10 (2006.01); F02M 37/00 (2006.01); B64D 37/04 (2006.01); B64C 3/34 (2006.01); B65D 90/44 (2006.01); B60K 15/077 (2006.01);
U.S. Cl.
CPC ...
B64C 17/10 (2013.01); B64C 3/34 (2013.01); B64D 37/04 (2013.01); F02M 37/0094 (2013.01); B60K 15/077 (2013.01); B65D 90/44 (2013.01);
Abstract

There is provided a center fuel tank assembly for an aircraft. The assembly includes a center fuel tank disposed in a central part of the aircraft. The assembly further includes one or more fuel barrier members partitioning the center fuel tank into two or more separate volume sections comprising two or more separate sub-tanks arranged in a fore-to-aft alignment to form a partitioned center fuel tank. The assembly further includes a fuel flow control assembly coupled to each of the two or more separate sub-tanks, each fuel flow control assembly operating independently. A sequential fuel burn of fuel in the two or more separate sub-tanks is made in a fore-to-aft sequence while the aircraft is in flight, to assist in shifting aftward a center of gravity (CG) of the aircraft, to reduce aircraft drag.


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