HYBRID POWER FOR DUCTED FAN UNMANNED AERIAL SYSTEMS

• US 20100147993A1
• Filed: 12/12/2008
• Published: 06/17/2010
• Est. Priority Date: 12/12/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: O'Brien, Patrick L., Annati, Richard E.
• Granted Patent: US 8,128,019 B2
• Time in Patent Office: Days
• US Class Current: 244/12.200
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 60/50 with landing legs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

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.

Claims

1. A propulsion system for a vertical take-off and landing ducted fan aerial vehicle, comprising:

an engine; and

an electric motor, wherein the electric motor is connected to a fan impeller on the ducted fan aerial vehicle and the engine, the electric motor comprising a motor drive and a battery;

wherein the engine and the electric motor each 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, wherein the ducted fan aerial vehicle completes a mission profile, the mission profile comprising take off, ascent, cruise, hover, descent, and landing.

4. The propulsion system of claim 3, the engine further comprising a design point, wherein the design point is the power and speed at which the engine produces peak efficiency.

5. The propulsion system of claim 4, wherein the engine is operated at its design point throughout the entire mission profile.

6. The propulsion system of claim 1, the ducted fan aerial vehicle further comprising a duct and a plurality of fan blades, wherein the fan impeller is connected to each of the plurality of fan blades and wherein the duct comprises an interior surface.

7. The propulsion system of claim 6, wherein the electric motor is integrated into the periphery of the fan blades.

8. The propulsion system of claim 6, wherein the electric motor is a ring motor comprising magnetic elements and electrical windings, wherein the electrical windings are located at the periphery of the fan blades and the interior surface of the duct.

9. The propulsion system of claim 1, wherein the electric motor serves as the engine starter.

10. The propulsion system of claim 1, wherein the electric motor powers the unmanned aerial vehicle when the engine fails.

11. An unmanned aerial vehicle comprising:

a shrouded propulsive fan, the shrouded propulsive fan comprising a fan impeller;

an engine, wherein the engine provides propulsion power to the unmanned aerial vehicle;

a motor-generator, wherein the motor-generator comprises a motor portion; and

a shaft, wherein the shaft is connected to the engine, the motor-generator, and the fan impeller;

wherein the motor portion of the motor generator provides power to the unmanned aerial vehicle in addition to the propulsion power provided by the engine.

12. The vehicle of claim 11, wherein the engine is a turbine engine.

13. The vehicle of claim 11, wherein the additional power is used during takeoff of the unmanned aerial vehicle.

14. The vehicle of claim 11, further comprising a density altitude operating range.

15. The vehicle of claim 14, wherein the additional power is used to expand the density altitude operating range of the vehicle.

16. The vehicle of claim 11, further comprising a payload capacity.

17. The vehicle of claim 16, wherein the additional power is used to expand the payload capacity of the vehicle.

18. The vehicle of claim 11, wherein the electric motor is connected to the shaft with a chain drive.

19. The vehicle of claim 11, wherein the engine is mounted on the shaft in between the electric motor and the fan impeller.

20. A ducted fan aerial vehicle, comprising:

an engine;

a plurality of fan blades, wherein each of the plurality of fan blades comprises an end, wherein each end comprises a periphery; and

an electric motor-generator, wherein the electric motor-generator is integrated into the periphery of at least one of the ends of the plurality of fan blades;

wherein the engine and the electric motor-generator each provide power to the ducted fan vehicle.