Hybrid electric propulsion system and method of operation

A method for operating a hybrid electric aircraft propulsion system, the method comprising:

• generating a first source of alternating current (AC) electric power from a generator and providing the AC electric power from the generator to a first electric propulsor, wherein the first source of AC electric power is generated from a first generator stator of the generator, and the second source of AC electric power selectively from a second generator stator of the generator, and wherein the first source of AC electric power is selectively provided to the first electric propulsor and a third electric propulsor;
• generating a second source of AC electric power from the generator;
• converting the second source of AC electric power into direct current (DC) electric power at a generator inverter;
• reconverting the DC electric power into the second source of AC electric power at a first motor inverter;
• selectively providing the second source of AC electric power to a second electric propulsor and the first electric propulsor from the first motor inverter;
• providing, from the generator inverter, the DC electric power to a second motor inverter;
• reconverting the DC electric power into the second source of AC electric power at the second motor inverter;
• and
• providing the second source of AC electric power to a fourth electric propulsor from the second motor inverter.

An aircraft comprising a hybrid electric aircraft propulsion system, the system comprising:

• a thermal engine;
• a generator coupled to the thermal engine, wherein the generator comprises a first generator stator for powering the first electric propulsor and second generator stator for powering the second electric propulsor;
• a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom;
• a second electric propulsor;
• a third electric propulsor operatively connected to the first stator generator to receive AC electric power therefrom;
• a fourth electric propulsor;
• a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power;
• a first motor inverter operatively connected to the generator inverter and to the second electric propulsor and configured to receive the DC electric power and provide the second electric propulsor with AC electric power;
• and
• a second motor inverter connected between the generator inverter and the fourth electric propulsor to convert DC electric power to AC electric power and provide the AC electric power to the fourth electric propulsor;
• wherein the first generator stator is selectively connected to one of the first electric propulsor and the third electric propulsor.