Inverter circuits and electrical propulsion systems for eVTOL aircraft

1. A propulsion system for an aircraft, comprising:

an electrical motor configured to drive one or more propellers of the aircraft; and

a capacitor configured to stabilize a direct current (DC) bus voltage;

a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage on a first bus of the first inverter circuit to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, based on a first pulse width modulation (PWM) vector; and

a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage on a second bus of the second inverter circuit to AC voltages to drive a second set of stator windings of the electrical motor, based on a second PWM vector, wherein:

the first PWM vector and the second PWM vector are substantially equal and opposite vectors; and

the first set of stator wings and the second set of stator wings are shifted by substantially 180 degrees.

2. The propulsion system of claim 1 , wherein the first inverter circuit is controlled using a center aligned space vector modulation.

3. The propulsion system of claim 2 , wherein the second inverter circuit is controlled using an inverted center aligned space vector modulation.

4. The propulsion system of claim 1 , wherein the first inverter circuit is configured to output a first set of three-phase AC voltages and the second inverter circuit is configured to output a second set of three-phase AC voltages.

5. The propulsion system of claim 4 , wherein a phase of the first set of three-phase AC voltages and a corresponding phase of the second set of three-phase AC voltages are two interleaved phases with a phase-shift of substantially 180 degrees.

6. The propulsion system of claim 1 , further comprising:

a DC common-mode filter coupled to the capacitor and configured to reduce common mode signals at a DC-side of the first inverter circuit and the second inverter circuit.

7. The propulsion system of claim 1 , further comprising:

one or more AC common-mode chokes coupled to an AC-side of the first inverter circuit or the second inverter circuit to reduce common mode signals.

8. A method for controlling a propulsion system for an aircraft, comprising:

stabilizing, by a capacitor, a direct current (DC) bus voltage;

converting, by a first inverter circuit coupled to the capacitor, the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of an electrical motor according to a first pulse width modulation (PWM) vector;

converting, by a second inverter circuit coupled to the capacitor, the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector, wherein:

the first PWM vector and the second PWM vector are substantially equal and opposite vectors; and

the first set of stator windings and the second set of stator windings are shifted by substantially 180 degrees; and

driving one or more propellers of the aircraft by the electrical motor.

9. The method of claim 8 , further comprising:

controlling the first inverter circuit using a center aligned space vector modulation.

10. The method of claim 9 , further comprising:

controlling the second inverter circuit using an inverted center aligned space vector modulation.

11. The method of claim 8 , further comprising:

output a first set of three-phase AC voltages by the first inverter circuit to drive the first set of stator windings; and

output a second set of three-phase AC voltages by the second inverter circuit to drive the second set of stator windings.

12. The method of claim 11 , wherein a phase of the first set of three-phase AC voltages and a corresponding phase of the second set of three-phase AC voltages are two interleaved phases with a phase-shift of substantially 180 degrees.

13. The method of claim 8 , further comprising:

reducing, by a DC common-mode filter coupled to the capacitor, common mode signals at a DC-side of the first inverter circuit and the second inverter circuit.

14. The method of claim 8 , further comprising:

reducing, by one or more AC common-mode chokes coupled to an AC-side of the first inverter circuit or the second inverter circuit, common mode signals at the AC-side of the first inverter circuit and the second inverter circuit.

15. An integrated circuit, comprising circuitry for performing a method for controlling a propulsion system for an aircraft, the circuitry is configured to:

control a first inverter circuit coupled to a capacitor, to convert a DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of an electrical motor according to a first pulse width modulation (PWM) vector; and

control a second inverter circuit coupled to the capacitor, to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector, wherein:

the first PWM vector and the second PWM vector are substantially equal and opposite vectors to drive one or more propellers of the aircraft by the electrical motor; and

the first set of stator windings and the second set of stator windings are shifted by substantially 180 degrees.

16. The integrated circuit of claim 15 , wherein the circuitry is further configured to control the first inverter circuit using a center aligned space vector modulation.

17. The integrated circuit of claim 16 , wherein the circuitry is further configured to control the second inverter circuit using an inverted center aligned space vector modulation.

18. The integrated circuit of claim 15 , wherein the circuitry is further configured to:

control the first inverter circuit to output a first set of three-phase AC voltages by the first inverter circuit to drive the first set of stator windings; and

control the second inverter circuit to output a second set of three-phase AC voltages by the second inverter circuit to drive the second set of stator windings.

19. The integrated circuit of claim 18 , wherein a phase of the first set of three-phase AC voltages and a corresponding phase of the second set of three-phase AC voltages are two interleaved phases with a phase-shift of substantially 180 degrees.

20. The integrated circuit of claim 15 , wherein a DC common-mode filter is coupled to the capacitor and configured to reduce common mode signals at a DC-side of the first inverter circuit and the second inverter circuit.

21. The integrated circuit of claim 15 , wherein one or more AC common-mode chokes are coupled to an AC-side of the first inverter circuit or the second inverter circuit to reduce common mode signals.