System and methods for implementing regional air transit network using hybrid-electric aircraft

A powertrain for an aircraft, comprising:

• at least one energy storage unit;
• a distribution bus coupled to the at least one energy storage unit and configured to be coupled to at least one range extending generator;
• at least one range extending generator coupled to the distribution bus;
• a powertrain optimization and control system (POCS), communicatively coupled to at least the at least one range extending generator and the at least one energy storage unit, the POCS configured to control a first amount of electricity supplied to the distribution bus by the at least one range extending generator and a second amount of electricity supplied to the distribution bus by the at least one energy storage unit, wherein:
• for each of the at least one energy storage unit and the at least one range extending generator, the POCS receives at least one electrical signal representing first state and performance information for the at least one energy storage unit and second state and performance information for the at least one range extending generator;
• and
• the POCS controls the first amount of the onboard generated energy provided by the at least one range extending generator and the second amount of the onboard stored energy provided by the at least one energy storage unit based at least in part on the first state and performance information for the at least one energy storage unit and the second state and performance information for the at least one range extending generator;
• and
• at least one electric propulsor coupled to the distribution bus to supply thrust to the aircraft using electricity drawn from the distribution bus.

A powertrain for an aircraft, comprising;

• at least one energy storage unit;
• a distribution bus coupled to the at least one energy storage unit and configured to be coupled to at least one range extending generator;
• at least one range extending generator coupled to the distribution bus;
• a powertrain optimization and control system (POCS), communicatively coupled to at least the at least one range extending generator and the at least one energy storage unit, the POCS configured to control a first amount of electricity supplied to the distribution bus by the at least one range extending generator and a second amount of electricity supplied to the distribution bus by the at least one energy storage unit, wherein:
• for each of the at least one energy storage unit and the at least one range extending generator, the POCS receives at least one electrical signal representing a first amount of energy onboard in the at least one energy storage unit and an amount of fuel onboard the aircraft that can be used by the at least one range extending generator to generate an amount of electrical energy representing a second amount of energy onboard;
• and
• the POCS determines how to draw selectively on the second amount of energy onboard over a planned flight of the aircraft based at least in part on the first amount of energy onboard;
• and
• at least one electric propulsor coupled to the distribution bus to supply thrust to the aircraft using electricity drawn from the distribution bus.

An aircraft, comprising:

• at least one energy storage unit;
• a distribution bus coupled to the at least one energy storage unit and configured to be coupled to at least one range extending generator;
• at least one range extending generator coupled to the distribution bus;
• at least one electric propulsor coupled to the distribution bus to supply thrust to the aircraft using electricity draw from the distribution bus, the at least one electric propulsor including:
• a flow duct,
• an electric motor, and
• a fan disk having variable pitch fan blades having a minimum pitch angle and a maximum pitch angle, the electric motor coupled to the fan disk, the electric motor and the fan disk disposed within the flow duct;
• at least one powertrain controller to operate the fan disk to drive the electric motor to provide air braking for the aircraft;
• a modular platform including the at least one distribution bus, electrical wiring, a plurality of electrical interfaces, at least one electric motor, and at least one power converter;
• and
• the plurality of electrical interfaces facilitate electrical connection and disconnection of at least one of (i) the at least one energy storage unit, (ii) the at least one range extending generator, (iii) the at least one electric motor, or (iv) the at least one power converter to and from the at least one distribution bus, wherein:
• the modular platform further includes a plurality of mechanical interfaces to facilitate mechanical connection and disconnection of the of at least one of (i) the at least one energy storage unit, (ii) the at least one range extending generator, (iii) the at least one electric motor, or (iv) the at least one power converter to and from the aircraft,
• an airframe, wherein:
• the at least one energy storage unit includes a plurality of energy storage units;
• the airframe includes a first plurality of accessible bays to facilitate installation, storage, and removal of at least some of the plurality of energy storage units;
• and
• respective ones of the first plurality of accessible bays include a first number of the plurality of electrical interfaces and a second number of the plurality of mechanical interfaces to facilitate electrical and mechanical connection and disconnection of the at least some of the plurality of energy storage units stored in the respective ones of the first plurality of bays to and from the at least one distribution bus and the aircraft.