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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 12486021 B1

PDFFull Text
Date of Patent:
Dec. 02, 2025

Filed:

Jun. 07, 2023

Electric propulsion system for an aircraft including a motor located between a gearbox assembly and a propeller

Applicant:

Archer Aviation Inc., San Jose, CA (US);

Inventors:

Scott Graves, Felton, CA (US);

Alan D. Tepe, Fremont, CA (US);

Robert Wayne Moore, Auburn, CA (US);

Assignee:

Archer Aviation Inc., San Jose, CA (US);

Attorney:

Finnegan, Henderson, Farabow, Garrett & Dunner, LLP

Primary Examiner:

Brady W Frazier

Int. Cl.
CPC ...
B64C 11/02 (2006.01); B60L 15/06 (2006.01); B60L 15/38 (2006.01); B64C 27/54 (2006.01); B64C 29/00 (2006.01); B64D 27/30 (2024.01); B64D 27/31 (2024.01); B64D 27/34 (2024.01); B64D 27/359 (2024.01); B64D 31/18 (2024.01); B64D 33/08 (2006.01); B64D 35/021 (2024.01); B64D 35/026 (2024.01); F16B 2/06 (2006.01); F16H 57/08 (2006.01); H02K 1/27 (2022.01); H02K 1/32 (2006.01); H02K 5/124 (2006.01); H02K 5/20 (2006.01); H02K 7/08 (2006.01); H02K 7/116 (2006.01); H02K 9/19 (2006.01); H02K 11/33 (2016.01); H02K 15/03 (2025.01); H02K 15/035 (2025.01); H02K 15/40 (2025.01); H02M 7/5395 (2006.01); H02P 21/00 (2016.01); H02P 25/16 (2006.01); H02P 27/06 (2006.01); H02P 27/08 (2006.01); H02K 7/00 (2006.01);
U.S. Cl.
CPC ...
B64C 11/02 (2013.01); B60L 15/06 (2013.01); B60L 15/38 (2013.01); B64C 27/54 (2013.01); B64C 29/0008 (2013.01); B64C 29/0033 (2013.01); B64D 27/30 (2024.01); B64D 27/31 (2024.01); B64D 27/34 (2024.01); B64D 27/359 (2024.01); B64D 31/18 (2024.01); B64D 33/08 (2013.01); B64D 35/021 (2024.01); B64D 35/026 (2024.01); F16B 2/06 (2013.01); F16H 57/08 (2013.01); H02K 1/27 (2013.01); H02K 1/32 (2013.01); H02K 5/124 (2013.01); H02K 5/203 (2021.01); H02K 7/08 (2013.01); H02K 7/116 (2013.01); H02K 9/19 (2013.01); H02K 11/33 (2016.01); H02K 15/03 (2013.01); H02K 15/035 (2025.01); H02K 15/40 (2025.01); H02M 7/5395 (2013.01); H02P 21/50 (2016.02); H02P 25/16 (2013.01); H02P 27/06 (2013.01); H02P 27/08 (2013.01); B60L 2200/10 (2013.01); B60L 2210/40 (2013.01); H02K 7/006 (2013.01); H02K 2215/00 (2021.08);
Abstract

An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.

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