US 12,319,426 B2
Aircraft propulsion system comprising a cooling system
Tomohiro Fukazu, Wako (JP)
Assigned to HONDA MOTOR CO., LTD., Tokyo (JP)
Filed by HONDA MOTOR CO., LTD., Tokyo (JP)
Filed on Dec. 13, 2022, as Appl. No. 18/079,906.
Claims priority of application No. JP2021-204693 (JP), filed on Dec. 17, 2021; and application No. JP2021-204696 (JP), filed on Dec. 17, 2021.
Prior Publication US 2023/0192310 A1, Jun. 22, 2023
Int. Cl. B64D 33/08 (2006.01); B64C 11/44 (2006.01)
CPC B64D 33/08 (2013.01) [B64C 11/44 (2013.01)] 6 Claims
OG exemplary drawing
 
1. An aircraft propulsion system comprising:
a motor configured to rotate a propeller of an electric aircraft;
an inverter device configured to control an operation of the motor;
a heat sink located radially outward of the motor, and including a plurality of fins;
a motor cooling channel located between a stator of the motor and the plurality of fins, and configured to allow a coolant to flow therethrough;
an inverter cooling channel configured to cool the inverter device by allowing the coolant to flow therethrough;
a first flow channel configured to allow the coolant to flow from the motor cooling channel to the inverter cooling channel;
a second flow channel configured to allow the coolant to flow from the inverter cooling channel to the motor cooling channel; and
a pump provided in one of the first flow channel or the second flow channel, wherein
the coolant flows from the motor cooling channel through the first flow channel, the inverter cooling channel, and the second flow channel in this order and returns to the motor cooling channel, absorbs heat from each of the motor and the inverter device, and dissipates the heat to the fins.