POWER DISTRIBUTION SYSTEM

• US 20120086266A1
• Filed: 09/27/2011
• Published: 04/12/2012
• Est. Priority Date: 09/17/2010
• Status: Active Grant

• Current Assignee: GE Aviation Systems Limited (GE Aerospace)
• Original Assignee: GE Aviation Systems Limited (GE Aerospace)
• Inventors: SHIPLEY, Adrian, Curwen, Stephen
• Granted Patent: US 9,236,744 B2
• Time in Patent Office: Days
• US Class Current: 307/9.1
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• 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

Abstract

A power distribution system which may be provided in an aircraft for example is described, the power distribution system comprising: a power distribution bus and a plurality of localised voltage converters each supplied by the power distribution bus. By providing a plurality of localised voltage converters, the power distribution system may use fewer, or just a single power distribution bus at a particular voltage and convert to the desired voltage at or near to each of a plurality of pieces of electrical equipment being supplied.

Claims

1. A power distribution system for an aircraft, the power distribution system comprising:

a power distribution bus and

a plurality of localised voltage converters each supplied by the power distribution bus.

2. A power distribution system according to claim 1, having only a single power distribution bus.

3. A power distribution system according to claim 1, wherein the power distribution bus is configured to operate at just one voltage.

4. A power distribution system according to claim 1, further comprising a primary power distribution box arranged to supply power to the power distribution bus at just one voltage.

5. A power distribution system according to claim 4, wherein the primary power distribution bus is configured to receive electrical power from one or more engines.

6. A power distribution system according to claim 1, further comprising two or more supplementary power distribution boxes, each supplementary power distribution box comprising a localised voltage converter, wherein each supplementary power distribution bus is configured to receive only a single voltage from the power distribution bus and supply power to one or more loads at a different voltage from that provided by the power distribution bus.

7. A power distribution system of claim 1, wherein the power distribution system is configured to supply electrical power to a plurality of loads at different voltages, wherein the power distribution bus is configured to supply electrical power at the highest voltage of the plurality of loads.

8. A power distribution system according to claim 1, wherein the plurality of localised voltage converters are configured to supply power at one other voltage as well as at the voltage of the power distribution bus.

9. A power distribution system according to claim 1, wherein the plurality of localised voltage converters are configured to supply power at two other voltages as well as at the voltage of the power distribution bus.

10. A power distribution system according to claim 1, wherein the plurality of localised voltage converters each comprise a power supply arranged to provide an adjustable output voltage.

11. A power distribution system according to claim 1, wherein the plurality of localised voltage converters comprise Switch Mode Power Supply (SMPS) transformer arrangements configured to operate at a switching frequency of 10 kHz or above.

12. An aircraft comprising a power distribution system comprising:

a power distribution bus and

a plurality of localised voltage converters each supplied by the power distribution bus.

13. An aircraft according to claim 12, wherein the power distribution bus is configured to operate at just one voltage.

14. An aircraft according to claim 12, wherein the power distribution system further comprises a primary power distribution box arranged to supply power to the power distribution bus at just one voltage.

15. An aircraft according to claim 12, wherein the power distribution system further comprises two or more supplementary power distribution boxes, each supplementary power distribution box comprising a localised voltage converter, wherein each supplementary power distribution bus is configured to receive only a single voltage from the power distribution bus and supply power to one or more loads at a different voltage from that provided by the power distribution bus.

16. An aircraft of claim 12, wherein the power distribution system is configured to supply electrical power to a plurality of loads at different voltages, wherein the power distribution bus is configured to supply electrical power at the highest voltage of the plurality of loads.

17. An aircraft according to claim 12, wherein the plurality of localised voltage converters are configured to supply power at one other voltage as well as at the voltage of the power distribution bus.

18. An aircraft according to claim 12, wherein the plurality of localised voltage converters are configured to supply power at two other voltages as well as at the voltage of the power distribution bus.

19. An aircraft according to claim 12, wherein the plurality of localised voltage converters each comprise a power supply arranged to provide an adjustable output voltage.

20. An aircraft comprising two or more power distribution systems, each power distribution system comprising:

one power distribution bus and

a plurality of localised voltage converters each supplied by the power distribution bus.