Dual function aircraft

Patent metadata

Field	Value
Publication number	US-10934008-B2
Application number	US-201715429934-A
Country	US
Kind code	B2
Filing date	Feb 10, 2017
Priority date	Feb 10, 2017
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.

First claim

What is claimed is:

1. An aircraft comprising:
an electric power source comprising a combustion engine and an electric generator, the electric generator powered by the combustion engine;
a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor; and
an electrical outlet receiving an unconverted output power from the electric generator and configured for connection with an outside power sink, the electrical outlet and the propulsion assembly selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly;
wherein the propulsion assembly utilizes a maximum flight power during flight operations of the aircraft, wherein the electric generator is configured to generate a maximum output power, and wherein the maximum output power is greater than the maximum flight power.

2. The aircraft of claim 1 , wherein the electric power source is configured to generate a maximum output power, and wherein the aircraft is configured to provide substantially the maximum output power to the electrical outlet when the electric generator is in electrical communication with the electrical outlet.

3. The aircraft of claim 1 , wherein the combustion engine is a turboshaft engine.

4. The aircraft of claim 1 , wherein the electric power source is configured to generate at least about 1 megawatt.

5. The aircraft of claim 1 , further comprising:
an electric power bus, wherein the electric power source is selectively in electrical communication with the propulsion assembly and the electrical outlet through the electric power bus.

6. The aircraft of claim 5 , wherein the electric power bus comprises a switch for selectively electrically connecting the propulsion assembly and the electrical outlet to the electric power source.

7. The aircraft of claim 1 , wherein the aircraft is an unmanned aerial vehicle.

8. The aircraft of claim 1 , wherein the aircraft is configured for vertical takeoff and landing.

9. The aircraft of claim 1 , wherein the propulsion assembly further comprises a plurality of propulsors and a respective plurality of electric motors.

10. The aircraft of claim 1 , wherein the maximum output power is at least about ten percent greater than the maximum flight power.

11. The aircraft of claim 1 , wherein the aircraft is configured to provide substantially the maximum output power to the outside power sink through the electrical outlet when the electric power source is in electrical communication with the electrical outlet.

12. The aircraft of claim 1 , wherein the maximum flight power is a peak amount of power required by the propulsion system, and wherein the electric generator is sized to generate the maximum output power.

13. A method for operating an aircraft including an electric power source having a combustion engine and an electric generator powered by the combustion engine, a propulsion assembly, and an electrical outlet, the method comprising:
operating the aircraft in a flight mode such that the aircraft provides electric power from the electric power source to the propulsion assembly and the propulsion assembly provides thrust for the aircraft; and
operating the aircraft in a power generation mode such that the aircraft provides electric power from the electric power source to the electrical outlet;
wherein the propulsion assembly utilizes a maximum flight power during flight operations of the aircraft, wherein the electric generator is configured to generate a maximum output power of at least about 1 megawatt, and wherein the maximum output power is greater than the maximum flight power.

14. The method of claim 13 , wherein operating the aircraft and the flight operating mode includes providing the propulsion assembly a first amount of power, wherein operating the aircraft in the power generation mode comprises providing the electrical outlet a second amount of power, and wherein the first and second amounts of power are each at least about one megawatt.

15. The method of claim 13 , wherein the aircraft is grounded during the power generation operating mode.

16. The method of claim 13 , wherein operating the aircraft in the flight mode includes performing a vertical takeoff and/or landing.

17. The method of claim 13 , wherein operating the aircraft in the flight mode comprises flying the aircraft to a destination and determining an amount of fuel required to fly the aircraft to the destination, and wherein operating the aircraft in the power generation mode comprises ceasing operating the aircraft in the power generation mode when a remaining amount of fuel is within a predetermined threshold of the determined amount of fuel required to fly to the destination.

18. The method of claim 13 , wherein operating the aircraft and the flight operating mode includes providing the propulsion assembly a first amount of power, wherein operating the aircraft in the power generation mode comprises providing the electrical outlet a second amount of power, and wherein the second amount of power is greater than the first amount of power.

19. The method of claim 18 , wherein the second amount of power is at least about ten percent greater than the first amount of power.

20. An aircraft comprising:
an electric power source comprising a combustion engine and an electric generator, the electric generator powered by the combustion engine;
a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor; and
an electrical outlet configured for connection with an outside power sink, wherein the electrical outlet receives power directly from the electric generator.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Crabtree Glenn David
• Barone Dominic

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64U2101/10

  for generating power to be supplied to a remote station, e.g. UAVs with solar panels · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title