US 12,351,325 B2
Systems, methods, and mechanical designs for inverters for eVTOL aircraft
Alan D. Tepe, Fremont, CA (US); and Michael Zwiers, Hudsonville, MI (US)
Assigned to Archer Aviation Inc., San Jose, CA (US)
Filed by Archer Aviation Inc., San Jose, CA (US)
Filed on Jul. 1, 2024, as Appl. No. 18/761,099.
Application 18/761,099 is a continuation of application No. 18/622,647, filed on Mar. 29, 2024, granted, now 12,122,527.
Application 18/622,647 is a continuation of application No. 18/306,275, filed on Apr. 25, 2023, granted, now 11,975,854, issued on May 7, 2024.
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 2024/0351694 A1, Oct. 24, 2024
Int. Cl. B64D 27/24 (2024.01); B60L 15/06 (2006.01); B60L 15/38 (2006.01); B64C 27/54 (2006.01); B64C 29/00 (2006.01); B64D 27/34 (2024.01); B64D 33/08 (2006.01); B64D 35/02 (2006.01); F16B 2/06 (2006.01); F16H 57/08 (2006.01); G01P 3/487 (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 (2006.01); 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)
CPC B64D 27/24 (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 27/34 (2024.01); B64D 33/08 (2013.01); B64D 35/02 (2013.01); F16B 2/06 (2013.01); F16H 57/08 (2013.01); G01P 3/487 (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)] 20 Claims
OG exemplary drawing
 
1. An inverter assembly that converts direct current (DC) power to alternate current (AC) power for an electrical propulsion system, the inverter assembly comprising:
at least one printed circuit board assembly (PCBA);
a capacitor assembly including:
at least one capacitor; and
a capacitor housing having at least one busbar; and
a housing, wherein the capacitor assembly and the at least one PCBA are positioned inside the housing, wherein the inverter assembly has a center hole extending through the capacitor assembly and the at least one printed circuit board assembly, the center hole having a central axis which is substantially parallel with a main shaft of the electric propulsion system.