Primary panel and motor controller integration for aircraft power distribution system

• US 7,922,117 B2
• Filed: 08/30/2004
• Issued: 04/12/2011
• Est. Priority Date: 08/30/2004
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Carter, Eric A., Wavering, Jeffrey T., Maier, Josef
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US10/929,318
• Publication Number:
  US 20060044722A1
• Time in Patent Office: 2,416 Days
• Field of Search: 244/1.R, 244/57, 244/58, 244/118.1, 244/118.5
• US Class Current: 244/58
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 4/00 Circuit arrangements for mains or distribution networks not specified as ac or dc
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An electric power generation and distribution system includes a primary distribution panel, which preferably operates at 230 VAC, and a High Voltage Direct Current (HVDC) panel in direct electrical communication therewith. The HVDC panels power motor controllers which drive electric motors residing in the center or aft sections of the aircraft. As many of the large electrical loads are located in the aft section of the aircraft, an aft electronics bay is located adjacent the aircraft wing roots to house the primary distribution panels and the HVDC panels.

Claims

1. An aircraft electric power generation and distribution system comprising:

a primary distribution panel; and

a High Voltage Direct Current (HVDC) panel mounted to and in electrical communication with said primary distribution panel.

2. The system as recited in claim 1, wherein said primary distribution panel operates at 230 VAC.

3. The system as recited in claim 2, wherein said primary distribution panel communicates with an engine driven generator.

4. The system as recited in claim 1, wherein said HVDC panel includes a multiple of motor controllers.

5. The system as recited in claim 4, further comprising an electric motor in electrical communication with each of said multiple of motor controllers.

6. The system as recited in claim 1, further comprising a secondary power panel in electrical communication with said primary distribution panel over a wire interconnect, said secondary panel located remotely from said primary distribution panel.

7. The system as recited in claim 6, wherein said secondary panel is located forward of said primary distribution panel.

8. The system as recited in claim 7, wherein said secondary panel is located adjacent an aircraft cockpit.

9. The system as recited in claim 1, wherein said primary distribution panel is in electrical communication with said HVDC panel through a busbar interconnect.

10. The system as recited in claim 1, wherein said primary distribution panel is in electrical communication with said HVDC panel through a fault free zone.

16. The system as recited in claim 1, further comprising a second primary distribution panel including a second HVDC panel mounted to said second primary distribution panel.

17. The system as recited in claim 16, wherein said primary distribution panel and said second primary distribution panel are mounted adjacent respective opposite wing roots of the aircraft.

11. An aircraft electric power generation and distribution system comprising:

a generator driven by an engine

an aft electronics bay;

a primary distribution panel located within said aft electronics bay, said primary distribution panel in electrical communication with said generator and operated at 230 VAC;

a High Voltage Direct Current (HVDC) panel mounted to and in electrical communication with said primary distribution panel through a busbar interconnect;

a forward electronics bay; and

a secondary panel located within said forward electronics bay, said secondary panel in electrical communication with said primary distribution panel.

12. The system as recited in claim 11, wherein said forward electronics bay is located adjacent an aircraft cockpit.

13. The system as recited in claim 11, wherein said aft electronics bay is located adjacent an aircraft wing root.

14. The system as recited in claim 11, wherein said HVDC panel includes a multiple of motor controllers.

15. The system as recited in claim 14, further comprising an electric motor in electrical communication with each of said multiple of motor controllers.

18. The system as recited in claim 11, comprising a second primary distribution panel having a second HVDC panel mounted to said second primary distribution panel, wherein said primary distribution panel and said second primary distribution panel are mounted within said aft electronics bay adjacent respective opposite wing roots of the aircraft.

19. The system as recited in claim 11, wherein said primary distribution panel is in electrical communication with said HVDC panel through a fault free zone.