logo

For the Inventor, By the Inventor

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 11860622 B1

PDFFull Text
Date of Patent:
Jan. 02, 2024

Filed:

Oct. 12, 2021

Hybrid gyrodyne aircraft

Applicant:

Aergility Corporation, Dunnellon, FL (US);

Inventors:

James E. Vander Mey, Dunnellon, FL (US);

Lawrence Winston Yonge, III, Summerfield, FL (US);

Assignee:

Aergility Corporation, Dunnellon, FL (US);

Attorney:

Young Basile Hanlon & MacFarlane, P.C.

Primary Examiner:

Philip J Bonzell

Int. Cl.
CPC ...
B64C 27/10 (2023.01); G05D 1/08 (2006.01); B64C 11/50 (2006.01); B64C 27/02 (2006.01); B64C 27/12 (2006.01); B64C 27/22 (2006.01); B64C 27/26 (2006.01); B64D 31/00 (2006.01); B64C 27/00 (2006.01); B64C 27/14 (2006.01); B64D 27/24 (2006.01); H02K 1/27 (2022.01); B64C 11/48 (2006.01); B64C 27/82 (2006.01);
U.S. Cl.
CPC ...
G05D 1/0858 (2013.01); B64C 11/50 (2013.01); B64C 27/006 (2013.01); B64C 27/02 (2013.01); B64C 27/021 (2013.01); B64C 27/025 (2013.01); B64C 27/027 (2013.01); B64C 27/028 (2013.01); B64C 27/10 (2013.01); B64C 27/12 (2013.01); B64C 27/14 (2013.01); B64C 27/22 (2013.01); B64C 27/26 (2013.01); B64D 31/00 (2013.01); B64C 11/48 (2013.01); B64C 2027/8236 (2013.01); B64D 27/24 (2013.01); H02K 1/27 (2013.01);
Abstract

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thnist to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

Find Patent Forward Citations

Loading…