Synchronization of generator and electric motor in a hybrid electric aircraft propulsion system

A system for operating a hybrid electric aircraft propulsion system comprising:

• a processing unit;
• and
• a non-transitory computer readable medium having stored thereon programming instructions executable by a processor for:
• providing a first electric propulsor and a second electric propulsor with a first source of propulsion power from a generator configured for generating a first output of alternating current (AC) electric power, the first source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective first motor stators of the first electric propulsor and the second electric propulsor;
• providing the first electric propulsor and the second electric propulsor with a second source of propulsion power independent from the first source of propulsion power, from at least one motor inverter operatively coupled to a direct current (DC) power source, the at least one motor inverter configured to convert the DC electric power from the DC power source into a second output of AC electric power, the second source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective second motor stators of the first electric propulsor and the second electric propulsor;
• monitoring a frequency of the first electric propulsor or the second electric propulsor through the motor inverter and detecting desynchronization between a frequency of the generator and the frequency of the first electric propulsor or the second electric propulsor;
• and
• modulating the second source of propulsion power applied to a desynchronized one of the first electric propulsor and the second electric propulsor from the at least one motor inverter to synchronize the frequency of the desynchronized one of the first electric propulsor and the second electric propulsor with the frequency of the generator and maintaining, during the synchronization, a connection between the generator and the desynchronized one of the first electric propulsor and the second electric propulsor.

A hybrid electric aircraft propulsion system, the system comprising:

• a thermal engine configured for outputting rotational mechanical power;
• a generator configured for generating a first source of alternating current (AC) electric power from the rotational mechanical power;
• at least one motor inverter configured to convert DC electric power received from a DC power source to AC electric power to provide a second source of AC electric power independent from the first source of AC electric power;
• a first electric propulsor and a second electric propulsor operatively coupled to the generator to receive AC electric power therefrom through respective first motor stators and operatively coupled to the at least one motor inverter to receive AC electric power therefrom, through respective second motor stators;
• and
• a controller configured for monitoring a frequency of the first electric propulsor or the second electric propulsor through the motor inverter and detecting desynchronization between a frequency of the generator and the frequency of the first electric propulsor or the second electric propulsor, and for modulating the AC electric power applied to a desynchronized one of the first electric propulsor and the second electric propulsor from the at least one motor inverter to synchronize the frequency of the desynchronized one of the first electric propulsor and the second electric propulsor with a frequency of the generator, and maintaining, during the synchronization, a connection between the generator and the desynchronized one of the first electric propulsor and the second electric propulsor.