System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same

A system for generating thrust at an aerial vehicle comprising:

• a primary electric motor comprising a motor output;
• a rotor coupled to the motor output and configured to generate a first thrust;
• an internal-combustion engine coupled to the rotor;
• an engine shroud defining a shroud inlet and a shroud outlet, and extending over the internal-combustion engine;
• a cooling fan configured to displace air through the engine shroud to cool the internal-combustion engine and output a second thrust, from the shroud outlet, to augment the first thrust;
• a nozzle coupled to the shroud outlet;
• a nozzle actuator configured to drive the nozzle over a range of orientations;
• and
• a local controller configured to:
• access a target total thrust;
• calculate a target rotor speed of the rotor based on the target total thrust and a component of a thrust output from the nozzle;
• drive the primary electric motor to selectively output torque to the rotor or regeneratively brake the rotor according to the target total thrust;
• adjust an orientation of the nozzle to direct the thrust output from the shroud outlet in one or more different orientations relative to the rotor;
• adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed;
• and
• drive the primary electric motor to selectively output torque to the rotor or regeneratively brake the rotor according to the calculated target rotor speed.