US 12,286,234 B2
Aircraft electric propulsion system with overlapping shafts for gearbox oil distribution
Scott Graves, Felton, CA (US); and Alan D. Tepe, Fremont, CA (US)
Assigned to ARCHER AVIATION INC., San Jose, CA (US)
Filed by Archer Aviation Inc., San Jose, CA (US)
Filed on Mar. 28, 2024, as Appl. No. 18/620,505.
Application 18/620,505 is a continuation of application No. 18/302,285, filed on Apr. 18, 2023, granted, now 11,975,853.
Claims priority of provisional application 63/378,680, filed on Oct. 7, 2022.
Claims priority of provisional application 63/378,536, filed on Oct. 6, 2022.
Prior Publication US 2024/0262518 A1, Aug. 8, 2024
Int. Cl. B64D 33/08 (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 35/02 (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); 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); B64D 27/24 (2024.01); H02K 7/00 (2006.01)
CPC B64D 27/30 (2024.01) [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 33/08 (2013.01); B64D 35/02 (2013.01); 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); 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)] 19 Claims
OG exemplary drawing
 
1. An electric propulsion system for an aircraft, the electric propulsion system comprising:
at least one electrical engine configured to be mechanically connected directly or indirectly to a fuselage of the aircraft and electrically connected to an electrical power source, wherein the electrical engine comprises:
an electric motor comprising a stator and a rotor;
a main shaft having a first end and a second end;
a secondary shaft surrounding the main shaft and substantially overlapping the main shaft, wherein the secondary shaft comprises an inner surface that is tapered; and
an inverter assembly that provides alternating current to the electric motor; and
a propeller assembly connected to the second end of the main shaft,
wherein the main shaft extends away from the inverter assembly to the second end of the main shaft, wherein a rotation of the main shaft is configured to distribute a fluid through the secondary shaft.