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:
Aug. 02, 2022

Filed:

Sep. 19, 2019
Applicant:

United Technologies Corporation, Farmington, CT (US);

Inventors:

Zubair Ahmed Baig, South Windsor, CT (US);

Sorin Bengea, Leuven, BE;

Gary L. Miles, Stillman Valley, IL (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 33/00 (2006.01); B64D 31/00 (2006.01); H02J 9/06 (2006.01); H02J 4/00 (2006.01);
U.S. Cl.
CPC ...
B64D 33/00 (2013.01); B64D 31/00 (2013.01); H02J 4/00 (2013.01); H02J 9/061 (2013.01);
Abstract

A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.


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