Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft

• US 20120209456A1
• Filed: 02/15/2012
• Published: 08/16/2012
• Est. Priority Date: 02/15/2011
• Status: Abandoned Application

• Current Assignee: The United States of America As Represented By The Secretary of Agriculture
• Original Assignee: US Department of The Air Force (U.S. Department Of Defense)
• Inventors: Harmon, Frederick G., Hiserote, Ryan M., Rippl, Matthew D., Ausserer, Joseph K.
• Application Number:
  US13/396,760
• Publication Number:
  US 20120209456A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 35/08 characterised by the transmission being driven by a plurality of power plants
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/20 Transmission of mechanical power to rotors or propellers
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

Claims

1. An unmanned air vehicle, comprising:

an airframe; and

a parallel hybrid-electric propulsion system mounted on the airframe, the parallel hybrid-electric propulsion system including;

an internal combustion engine;

an electric motor;

a hybrid controller, the hybrid controller configured to control both the internal combustion engine and the electric motor; and

a mechanical link; and

a propeller connected to the mechanical link,

wherein the mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller.

2. The unmanned air vehicle of claim 1, wherein the mechanical link is an electromagnetic clutch.

3. The unmanned air vehicle of claim 1, wherein the mechanical link is a one-way bearing.

4. The unmanned air vehicle of claim 1, wherein the mechanical link is a centrifugal clutch.

5. The unmanned air vehicle of claim 1, wherein the parallel hybrid-electric propulsion system further includes:

a battery pack, the battery pack electrically connected to the electric motor and configured to provide electric power to the electric motor.

6. The unmanned air vehicle of claim 5, wherein the parallel hybrid-electric propulsion system further includes:

an electric starter, the electric starter coupled to the internal combustion engine and configured to start the internal combustion engine,

wherein the electric starter is electrically connected to the battery pack, and

wherein the battery pack is further configured to provide electric power to the electric starter.

7. The unmanned air vehicle of claim 1, further comprising:

a mechanical starter coupled to the internal combustion engine and configured to start the internal combustion engine.

8. An unmanned air vehicle, comprising:

an airframe; and

a parallel hybrid-electric propulsion system mounted on the airframe, the parallel hybrid-electric propulsion system including;

an internal combustion engine having a first drive shaft;

an electric motor having a second drive shaft; and

a hybrid controller, the hybrid controller configured to control both the internal combustion engine and the electric motor; and

a propeller connected to the first drive shaft,

wherein the first drive shaft is coupled to the second drive shaft by a belt.

9. The unmanned air vehicle of claim 8, wherein the first drive shaft includes an electromagnetic clutch.

10. The unmanned air vehicle of claim 8, wherein the first drive shaft includes a one-way bearing.

11. The unmanned air vehicle of claim 8, wherein the first drive shaft includes a centrifugal clutch.

12. The unmanned air vehicle of claim 8, wherein the parallel hybrid-electric propulsion system further includes:

a battery pack having at least one battery, the battery pack electrically connected to the electric motor and configured to provide electric power to the electric motor.

13. The unmanned air vehicle of claim 12, wherein the parallel hybrid-electric propulsion system further includes:

an electric starter, the electric starter coupled to the internal combustion engine and configured to start the internal combustion engine,

wherein the electric starter is electrically connected to the battery pack, and

wherein the battery pack is further configured to provide electric power to the electric starter.

14. The unmanned air vehicle of claim 12, wherein the electric motor, when not being provided with electric power from the battery pack, is configured to generate electric power when the second drive shaft is driven through the belt from the first drive shaft, and further configured to charge the at least one battery of the battery pack.

15. The unmanned air vehicle of claim 8, further comprising:

a mechanical starter coupled to the internal combustion engine and configured to start the internal combustion engine.

16. An unmanned air vehicle, comprising:

an airframe; and

a parallel hybrid-electric propulsion system mounted on the airframe, the parallel hybrid-electric propulsion system including;

an internal combustion engine;

a first propeller, wherein the internal combustion engine drives the first propeller;

an electric motor;

a second propeller, wherein the electric motor drives the second propeller; and

a hybrid controller configured to control both the internal combustion engine and the electric motor,

wherein the internal combustion engine is decoupled from the electric motor.

17. The unmanned air vehicle of claim 16, wherein the parallel hybrid-electric propulsion system further includes:

a battery pack having at least one battery, the battery pack electrically connected to the electric motor and configured to provide electric power to the electric motor.

18. The unmanned air vehicle of claim 17, wherein the parallel hybrid-electric propulsion system further includes:

an electric starter, the electric starter coupled to the internal combustion engine and configured to start the internal combustion engine,

wherein the electric starter is electrically connected to the battery pack, and

wherein the battery pack is further configured to provide electric power to the electric starter.

19. The unmanned air vehicle of claim 17, wherein the electric motor, when not being provided with electric power from the battery pack, is configured to generate electric power from a rotation of the second propeller, and further configured to charge the at least one battery of the battery pack.

20. The unmanned air vehicle of claim 16, further comprising:

a mechanical starter coupled to the internal combustion engine and configured to start the internal combustion engine.