Aircraft ground support vehicle

• US 9,666,889 B2
• Filed: 03/19/2015
• Issued: 05/30/2017
• Est. Priority Date: 03/25/2014
• Status: Active Grant

• Current Assignee: Parker Intangibles LLC (Parker-Hannifin Corporation)
• Original Assignee: Parker-Hannifin Corporation
• Inventors: Loignon, Michel, Brierley, Scott
• Primary Examiner(s): Phan, Hau
• Application Number:
  US14/662,543
• Publication Number:
  US 20150274323A1
• Time in Patent Office: 803 Days
• CPC Class Codes: B60L 1/003 to auxiliary motors, e.g. for pumps, compressors
• CPC Class Codes: B60L 1/006 to power outlets
• CPC Class Codes: B60L 2200/40 Working vehicles
• CPC Class Codes: B60L 2220/46 Wheel motors, i.e. motor connected to only one wheel
• CPC Class Codes: B60L 2260/28 Four wheel or all wheel drive
• CPC Class Codes: B60L 50/52 characterised by DC-motors
• CPC Class Codes: B60L 58/40 for controlling a combination of batteries and fuel cells
• CPC Class Codes: B64F 1/225 Vehicles specially adapted therefor, e.g. aircraft tow tractors
• CPC Class Codes: H01M 2250/20 Fuel cells in motive systems, e.g. vehicle, ship, plane
• CPC Class Codes: H01M 8/04776 at auxiliary devices, e.g. reformer, compressor, burner
• CPC Class Codes: H01M 8/04925 Power, energy, capacity or load
• CPC Class Codes: H01M 8/0494 of fuel cell stacks
• CPC Class Codes: H01M 8/04947 of auxiliary devices, e.g. batteries, capacitors
• CPC Class Codes: Y02E 60/50 Fuel cells
• CPC Class Codes: Y02P 90/60 Electric or hybrid propulsion means for production processes
• CPC Class Codes: Y02T 10/70 Energy storage systems for electromobility, e.g. batteries
• CPC Class Codes: Y02T 90/16 Information or communication technologies improving the operation of electric vehicles
• CPC Class Codes: Y02T 90/40 Application of hydrogen technology to transportation, e.g. using fuel cells

Abstract

Provided is a power management system of an aircraft ground support vehicle. The power management system includes a power production control module in communication with a fuel cell system of the aircraft ground support vehicle to control production of electrical power by the fuel cell system. The fuel cell system may be configured as a sole source of power to directly power a traction system of the aircraft ground support vehicle and to provide electrical power to an auxiliary power output of the aircraft ground support vehicle. The power management system further includes a power distribution control module in communication with the fuel cell system to control distribution of the electrical power between the traction system and the auxiliary power output. The aircraft ground support vehicle may include a chassis, the traction system, the auxiliary power output, the fuel cell system, and the power management system.

Claims

1. A power management system of an aircraft ground support vehicle, comprising:

a power production control module in communication with a fuel cell system of the aircraft ground support vehicle to control production of electrical power by the fuel cell system, the fuel cell system configured as a sole source of power to directly power a traction system of the aircraft ground support vehicle and an auxiliary power output of the aircraft ground support vehicle; and

a power distribution control module in communication with the fuel cell system to control distribution of the electrical power between the traction system and the auxiliary power output.

2. An aircraft ground support vehicle, comprising:

the power management system of claim 1;

a chassis;

the traction system mounted to the chassis and configured to drive the aircraft ground support vehicle;

the auxiliary power output configured to couple to the auxiliary power input of an aircraft; and

the fuel cell system fixedly mounted to the chassis and configured as the sole source of power to directly power the traction system and provide electrical power to the auxiliary power output.

3. The aircraft ground support vehicle of claim 2, wherein the power management system is configured to simultaneously distribute the electrical power produced by the fuel cell system between the traction system and the auxiliary power output.

4. The aircraft ground support vehicle of claim 2, wherein the power management system comprises a power production control module configured to control production of electrical power by the fuel cell system in response to one or more power control input signals received from an operator input or from the auxiliary power output.

5. The aircraft ground support vehicle of claim 2, wherein the power management system comprises a power distribution control module configured to distribute the electrical power produced by the fuel cell system to the traction system and to the auxiliary power output in response to one or more power control input signals received from an operator input or from the auxiliary power output.

6. The aircraft ground support vehicle of claim 2, wherein the fuel cell system comprises fuel cells combined in series and in parallel circuits.

7. The aircraft ground support vehicle of claim 2, further comprising a fuel source configured to supply fuel to the fuel cell system.

8. The aircraft ground support vehicle of claim 7, wherein the fuel source comprises a reformer configured to convert a hydrocarbon reactant to a fuel for use by the fuel cell system, the power management system further configured to control production of the fuel by the reformer.

9. The aircraft ground support vehicle of claim 2, wherein the auxiliary power output is configured to vary a voltage of electrical power output therefrom.

10. The aircraft ground support vehicle of claim 2, further comprising a reclamation system configured to capture waste products from the fuel cell system.

11. The aircraft ground support vehicle of claim 2, wherein the traction system comprises one or more wheels mounted to the chassis and one or more electric motors configured to drive the one or more wheels.

12. The power management system of claim 1, wherein the power management system is configured to simultaneously distribute the electrical power produced by the fuel cell system between the traction system and the auxiliary power output.

13. The power management system of claim 1, wherein the power production control module is configured to control production of electrical power by the fuel cell system in response to one or more power control input signals received from an operator input or from the auxiliary power output.

14. The power management system of claim 1, wherein the power distribution control module is configured to distribute the electrical power produced by the fuel cell system to the traction system and to the auxiliary power output in response to one or more power control input signals received from an operator input or from the auxiliary power output.

15. The power management system of claim 1, wherein the power production control module is in communication with a fuel source of the aircraft ground support vehicle, the fuel source comprising a reformer configured to convert a hydrocarbon reactant to a fuel for use by the fuel cell system, and wherein the power production control module is configured to control production of the fuel by the reformer.

16. A method of managing electrical power of an aircraft ground support vehicle, comprising:

producing electrical power with a fuel cell system of the aircraft ground support vehicle, the fuel cell system configured as a sole source of electrical power to directly power a traction system of the aircraft ground support vehicle and an auxiliary power output of the aircraft ground support vehicle; and

distributing the electrical power between the traction system and the auxiliary power output.

17. The method of claim 16, wherein the electrical power produced by the fuel cell system is simultaneously distributed between the traction system and the auxiliary power output.

18. The method of claim 16, wherein the production of electrical power by the fuel cell system is controlled in response to one or more power control input signals received from an operator input or from the auxiliary power output.

19. The method of claim 16, wherein the distribution of the electrical power produced by the fuel cell system to the traction system and to the auxiliary power output is controlled in response to one or more power control input signals received from an operator input or from the auxiliary power output.

20. The method of claim 16, further comprising converting a hydrocarbon reactant to a fuel for use by the fuel cell system using a reformer of the aircraft ground support vehicle.