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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 12473074 B1

PDFFull Text
Date of Patent:
Nov. 18, 2025

Filed:

Jan. 10, 2025

Aircraft propulsion system including pump gear driven by planetary gearbox assembly

Applicant:

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

Inventors:

Scott Graves, Felton, CA (US);

Alan D. Tepe, Fremont, 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 take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

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