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:
Jul. 23, 2024

Filed:

Feb. 21, 2019
Applicant:

The Boeing Company, Chicago, IL (US);

Inventors:

Roger D. Bernhardt, St. Charles, MO (US);

Donald V. Drouin, Jr., O'Fallon, IL (US);

Assignee:

The Boeing Company, Arlington, VA (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B60L 50/60 (2019.01); B64C 1/12 (2006.01); B64C 3/18 (2006.01); B64C 3/20 (2006.01); H01G 9/035 (2006.01); H01G 9/04 (2006.01); H01M 10/0525 (2010.01); H01M 50/213 (2021.01); H01M 50/24 (2021.01); H01M 50/249 (2021.01);
U.S. Cl.
CPC ...
B60L 50/66 (2019.02); B64C 1/12 (2013.01); B64C 3/185 (2013.01); B64C 3/20 (2013.01); H01M 10/0525 (2013.01); H01M 50/24 (2021.01); H01M 50/249 (2021.01); B60L 2200/10 (2013.01); H01G 9/035 (2013.01); H01G 9/04 (2013.01); H01M 50/213 (2021.01); H01M 2220/20 (2013.01);
Abstract

Structurally integrated energy supply systems for aircraft and methods of forming the structurally integrated energy supply systems. The structurally integrated energy supply systems include an aircraft structural component, a cell array, and a plurality of energy-producing inserts. The aircraft structural component at least partially defines an interior region. The cell array includes a plurality of cell walls that defies a plurality of elongate cell volumes and is positioned within the interior region. Each energy-producing insert in the plurality of energy-producing inserts is positioned within a corresponding elongate cell volume in the plurality of elongate cell volumes and is configured to produce a corresponding insert electric current. The cell array provides structural load distribution to the aircraft structural component via the plurality of cell walls and contributes to a structural stiffness of the aircraft structural component.


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