Power distribution system for an aircraft

Patent metadata

Field	Value
Publication number	US-9236744-B2
Application number	US-201113225702-A
Country	US
Kind code	B2
Filing date	Sep 27, 2011
Priority date	Sep 17, 2010
Publication date	Jan 12, 2016
Grant date	Jan 12, 2016

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 localized voltage converters each supplied by the power distribution bus. By providing a plurality of localized 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.

First claim

What is claimed is:

1. A power distribution system for an aircraft, comprising:
a primary power distribution box configured to receive electrical power from at least one aircraft engine, and supply power to a power distribution bus at a single voltage; and
a plurality of localised voltage converters each supplied by the power distribution bus, wherein the localized voltage converters each comprise a power supply configured to provide an adjustable output voltage.

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 two or more secondary power distribution boxes, each secondary power distribution box comprising a localised voltage converter, wherein each secondary power distribution box 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.

5. A power distribution system of claim 1 , wherein the power distribution system is configured to supply electrical power at a voltage utilized by at least one of a plurality of loads included in the power distribution system.

6. 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.

7. 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.

8. 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.

9. An aircraft comprising a power distribution system for receiving electrical power from one or more aircraft engines, the power distribution system comprising:
a primary power distribution box configured to receive the electrical power from the one or more aircraft engines, and supply power to a power distribution bus at a first voltage; and
a plurality of localised voltage converters each supplied the first voltage by the power distribution bus, the localized voltage converters each comprising a power supply configured to provide an adjustable output voltage.

10. An aircraft according to claim 9 , wherein the power distribution system further comprises two or more secondary power distribution boxes, each secondary power distribution box comprising a localised voltage converter, wherein each secondary power distribution bus is configured to receive the first voltage from the power distribution box and supply power to one or more loads at a different voltage from that provided by the power distribution bus.

11. An aircraft of claim 9 , wherein the first voltage is equal to a voltage used by at least one load.

12. An aircraft according to claim 9 , wherein the plurality of localised voltage converters are configured to supply power at a second voltage and the first voltage.

13. An aircraft according to claim 9 , wherein the plurality of localised voltage converters are configured to supply power at the first voltage and a plurality of other voltages.

14. An aircraft comprising two or more power distribution systems configured to utilize electrical power from one or more aircraft engines, each power distribution system comprising:
a primary power distribution box configured to receive electrical power from the one or more aircraft engines, and supply power to one power distribution bus at a first voltage; and
a plurality of localised voltage converters each supplied the first voltage by the power distribution bus, the localized voltage converters each comprising a power supply configured to provide an adjustable output voltage.

Assignees

• Shipley Adrian
• Curwen Stephen
• Ge Aviat Systems Ltd

Inventors

• Shipley Adrian
• Curwen Stephen

Classifications

• H02J4/00 Primary

  Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B60L1/00 Primary

  Supplying electric power to auxiliary equipment of vehicles (circuit arrangements for charging batteries H02J7/00) · CPC title

• B60R16/03

  for supply of electrical power to vehicle subsystems {or for (circuit arrangements for charging batteries H02J7/00)} · CPC title

• H02J3/00

  Circuit arrangements for AC mains or AC distribution networks · CPC title