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A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial v

A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle.

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1. A propulsion system for a vertical take-off and landing ducted fan aerial vehicle, the propulsion system comprising: a fan comprising a fan impeller, wherein the fan is located within an air duct;an engine configured to rotate the fan impeller; andan electric motor, wherein the electric motor is

1. A propulsion system for a vertical take-off and landing ducted fan aerial vehicle, the propulsion system comprising: a fan comprising a fan impeller, wherein the fan is located within an air duct;an engine configured to rotate the fan impeller; andan electric motor, wherein the electric motor is connected to the fan impeller and the engine, and wherein the engine and the electric motor are configured to simultaneously rotate the fan impeller to provide power to the ducted fan aerial vehicle. 2. The propulsion system of claim 1, wherein the electric motor is a motor-generator. 3. The propulsion system of claim 1, further comprising a plurality of fan blades that define a periphery, wherein the fan impeller is connected to each fan blade of the plurality of fan blades, and wherein the electric motor is integrated into the periphery defined by the plurality of fan blades. 4. The propulsion system of claim 3, wherein the electric motor is a ring motor comprising magnetic elements and electrical windings, and wherein the electrical windings are located at the periphery of the fan blades and an interior surface of the air duct. 5. The propulsion system of claim 1, wherein the electric motor serves as an engine starter for the ducted fan aerial vehicle. 6. The propulsion system of claim 1, wherein the electric motor is configured to power the unmanned aerial vehicle when the engine fails. 7. A ducted fan aerial vehicle, comprising: an engine;a ducted fan comprising a plurality of fan blades, wherein each fan blade of the plurality of fan blades comprises an end, and the end of each fan blade of the plurality of fan blades defines a periphery; andan electric ring motor, wherein the electric ring motor is integrated into the periphery defined by the ends of the fan blades of the plurality of fan blades, and wherein the engine and the electric ring motor are configured to simultaneously rotate the plurality of fan blades of the ducted fan. 8. The propulsion system of claim 1, further comprising a shaft connected to the fan impeller, wherein the electric motor and the engine are each configured to rotate the fan impeller by rotating the shaft. 9. The propulsion system of claim 8, further comprising a clutch, wherein the clutch is configured to disengage the engine from the shaft and allow the electric motor to rotate the shaft without resistance from the engine. 10. The propulsion system of claim 8, further comprising a clutch, wherein the clutch is configured to disengage the electric motor from the shaft and allow the engine to rotate the shaft without resistance from the electric motor. 11. The propulsion system of claim 8, further comprising a chain drive that connects the electric motor and the shaft. 12. The propulsion system of claim 8, wherein the engine is mounted on the shaft between the electric motor and the fan impeller. 13. The propulsion system of claim 1, wherein the engine comprises at least one of an internal combustion engine or a turbine engine. 14. The propulsion system of claim 2, further comprising a battery, wherein the engine is configured to provide mechanical energy to the motor-generator and the motor-generator is configured to convert the mechanical energy into electrical energy to recharge the battery. 15. The propulsion system of claim 1, wherein the electric motor comprises a ring motor.