SYSTEMS, METHODS, AND MECHANICAL DESIGNS FOR INVERTERS FOR EVTOL AIRCRAFT
An inverter assembly for an electrical propulsion system comprises at least one printed circuit board assembly (PCBA) having a plurality of power modules, a thermal plate comprising one or more channels, a plurality of fin arrays thermally coupled to the plurality of power modules, and a housing. The plurality of fin arrays are configured to receive a fluid from the one or more channels. The at least one printed circuit board assembly and the thermal plate are disposed within the housing.
1 .- 23 . (canceled)
24 . An inverter assembly for an electrical propulsion system, the inverter assembly comprising:
at least one printed circuit board assembly (PCBA) having a plurality of power modules;
a thermal plate comprising:
one or more channels; and
a plurality of fin arrays thermally coupled to the plurality of power modules, wherein the plurality of fin arrays are configured to receive a fluid from the one or more channels; and
a housing, wherein the at least one printed circuit board assembly and the thermal plate are disposed within the housing.
25 . The inverter assembly of claim 24 , wherein the inverter assembly has a center hole extending through the at least one printed circuit board assembly and the thermal plate.
26 . The inverter assembly of claim 25 , wherein the center hole has a central axis which is substantially parallel with a main shaft of the electric propulsion system.
27 . The inverter assembly of claim 25 , wherein the plurality of fin arrays are arranged radially outward from the center hole.
28 . The inverter assembly of claim 24 , wherein the thermal plate abuts the at least one PCBA.
29 . The inverter assembly of claim 24 , wherein the thermal plate includes an annulus.
30 . The inverter assembly of claim 29 , wherein the one or more channels are configured to receive the fluid from the annulus.
31 . The inverter assembly of claim 24 , wherein each of the plurality of fin arrays are configured to cool one of the plurality of power modules using the fluid.
32 . The inverter assembly of claim 31 , further comprising six fin arrays and six power modules, wherein each of the six fin arrays is configured to cool one of the six power modules.
33 . The inverter assembly of claim 31 , wherein the fluid comprises oil.
34 . An aircraft, comprising:
a propeller assembly;
an electrical motor assembly including at least a stator and a rotor, wherein the electrical motor assembly drives the propeller assembly through a main shaft;
an inverter assembly positioned along the main shaft, wherein the inverter assembly comprises:
at least one printed circuit board assembly (PCBA) having a plurality of power modules;
a thermal plate comprising:
one or more channels; and
a plurality of fin arrays thermally coupled to the plurality of power modules, wherein the plurality of fin arrays are configured to receive a fluid from the one or more channels; and
a housing, wherein the at least one printed circuit board assembly and the thermal plate are disposed within the housing.
35 . The aircraft of claim 34 , further comprising a heat exchanger coupled to the inverter assembly.
36 . The aircraft of claim 35 , wherein the heat exchanger is fluidically coupled with the thermal plate and configured to cool the fluid.
37 . The aircraft of claim 35 , wherein the plurality of fin arrays are arranged radially outward from a center hole.
38 . The aircraft of claim 34 , wherein the thermal plate abuts the at least one PCBA.
39 . The aircraft of claim 34 , wherein the thermal plate includes an annulus.
40 . The aircraft of claim 39 , wherein the one or more channels are configured to receive the fluid from the annulus.
41 . The aircraft of claim 34 , wherein the plurality of fin arrays are configured to cool the plurality of power modules using the fluid.
42 . The aircraft of claim 41 , wherein the fluid is oil.
43 . The aircraft of claim 34 , wherein the aircraft is a vertical take-off and landing (VTOL) aircraft.