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.

Patent No.:

US 11649045 B1

Date of Patent:

May. 16, 2023

Filed:

Sep. 21, 2022

Power management methods for multi engine rotorcraft

Applicant:

Textron Innovations Inc., Providence, RI (US);

Inventor:

William Mathisen Gons, Dallas, TX (US);

Assignee:

Textron Innovations Inc., Providence, RI (US);

Attorney:

Lawrence Youst PLLC

Primary Examiner:

Christopher D Hutchens

Int. Cl.

CPC ...

B64C 27/12 (2006.01); B64D 31/00 (2006.01); F02C 6/20 (2006.01); F02C 9/56 (2006.01); F02C 9/44 (2006.01); F02C 9/48 (2006.01); F02C 9/42 (2006.01); B64D 27/14 (2006.01); B64D 31/06 (2006.01); F02C 9/28 (2006.01); B64C 27/06 (2006.01); B64D 27/24 (2006.01); B64D 27/02 (2006.01); B64D 35/08 (2006.01);

U.S. Cl.

CPC ...

B64C 27/12 (2013.01); B64D 27/14 (2013.01); B64D 31/00 (2013.01); B64D 31/06 (2013.01); F02C 6/206 (2013.01); F02C 9/28 (2013.01); F02C 9/42 (2013.01); F02C 9/44 (2013.01); F02C 9/48 (2013.01); F02C 9/56 (2013.01); B64C 27/06 (2013.01); B64D 27/24 (2013.01); B64D 35/08 (2013.01); B64D 2027/026 (2013.01); F05D 2220/329 (2013.01); F05D 2270/13 (2013.01); F05D 2270/44 (2013.01);

Abstract

A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.

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