Aircraft universal power converter

Patent metadata

Field	Value
Publication number	US-10476379-B2
Application number	US-201615359400-A
Country	US
Kind code	B2
Filing date	Nov 22, 2016
Priority date	Jul 18, 2013
Publication date	Nov 12, 2019
Grant date	Nov 12, 2019

Abstract

A power supply system suitable for use by an aircraft is disclosed. The power system converts power from an unregulated DC power source to multiple AC and DC voltage outputs. The power supply system comprises an interleaved buck converter, and interleaved full-bridge converter, an interleaved inverter, and a control system. In one configuration, the interleaved inverter uses high-voltage DC generated by the interleaved four-bridge converter as its power input to generate a high-voltage AC output.

First claim

The invention claimed is:

1. An aircraft power supply system comprising:
a plurality of system control signals;
a low-voltage DC power bus configured to distribute low-voltage DC power to the aircraft;
a high-voltage DC power bus configured to distribute high-voltage DC power to the aircraft;
a high-voltage AC power bus configured to distribute high-voltage AC power to the aircraft;
an unregulated DC power source;
an interleaved buck converter configured to use power of the unregulated DC power source to generate a regulated low-voltage DC output for provision to the low-voltage DC power bus;
an interleaved full-bridge converter configured to use power of the unregulated DC power source to generate a high-voltage DC output for provision to the high-voltage DC power bus;
an interleaved inverter configured to use power of the unregulated DC power source to generate a high-voltage AC output on the high-voltage AC power bus; and
a control system configured to control the interleaved buck converter, the interleaved full-bridge converter, and the interleaved inverter, in response to the plurality of system control signals.

2. The aircraft power supply system of claim 1 , wherein the interleaved full-bridge converter is further configured to provide the high-voltage DC output as a power source for the interleaved inverter.

3. The aircraft power supply system of claim 1 , wherein the control system comprises:
a first controller configured to control the interleaved buck converter;
a second controller configured to control the interleaved full-bridge converter;
a third controller configured to control the interleaved inverter; and
a supervisory controller responsive to the plurality of system control signals to control operation of the first, second, and third controllers.

4. The aircraft power supply system of claim 1 , wherein the unregulated DC power source comprises a fuel cell.

5. The aircraft power supply system of claim 4 , wherein the fuel cell provides unregulated DC output power to an EMI filter.

6. The aircraft power supply system of claim 5 , wherein the EMI filter is common to both the interleaved buck converter and the interleaved full-bridge converter.

7. The aircraft power supply system of claim 1 , wherein the interleaved buck converter, the interleaved full-bridge converter, and the interleaved inverter are configured as a unitary unit that is localized in an aft portion of the aircraft, a forward portion of the aircraft, or a mid-portion of the aircraft.

8. The aircraft power supply system of claim 1 , wherein the control system is further configured to operate the interleaved full-bridge converter to turn the high-voltage DC output on and off.

9. The aircraft power supply system of claim 1 , wherein the interleaved buck converter comprises:
a plurality of parallel connected buck converters providing a corresponding plurality of voltage phases numbering X to an output capacitor; and
wherein the control system drives the plurality of buck converters so that the plurality of voltage phases are interleaved at 360/X degrees with respect to one another.

10. The aircraft power supply system of claim 1 , wherein the interleaved full-bridge converter comprises:
a plurality of full-bridge cells configured to receive respective PWM control signals, wherein each full-bridge cell generates a respective phase voltage for rectification by a respective rectification circuit,
a first filter circuit, wherein a first pair of the full-bridge cells are connected in parallel with the first filter circuit; and
a second filter circuit, wherein a second pair of the full-bridge cells are connected in parallel with the second filter circuit, wherein the first and second filters are connected in series with one another and have a common node.

11. The aircraft power supply system of claim 1 , wherein the interleaved inverter comprises a three-phase, four-leg interleaved inverter.

12. The aircraft power supply system of claim 1 , wherein the low-voltage DC power bus provides a voltage of 32 V DC to the aircraft, the high-voltage DC power bus provides a voltage of +/−270 V DC and/or 540 V DC 800 V DC to the aircraft, and the high-voltage AC power bus provides a voltage of 230 or 115 V AC to the aircraft.

13. A control system for a power supply comprising:
a first controller configured to control an interleaved buck converter;
a second controller configured to control an interleaved full-bridge converter;
a third controller configured to control an interleaved inverter; and
a supervisory controller configured to control operation of the first, second, and third controllers in response to a plurality of control signals.

14. The control system of claim 13 , wherein the supervisory controller is configured to direct the interleaved full-bridge converter to discontinue generation of high-voltage AC in a first operational mode and to direct the interleaved full-bridge converter to generate high-voltage AC in a second operational mode.

15. The control system of claim 13 , wherein:
the interleaved buck converter is configured to use power of an unregulated DC power source to generate a regulated low-voltage DC output for provision to a low-voltage DC power bus;
the interleaved full-bridge converter is configured to use power of the unregulated DC power source to generate a high-voltage DC output for provision to a high-voltage DC power bus; and
the interleaved inverter is configured to use power of the unregulated DC power source to generate a high-voltage AC output on a high-voltage AC power bus.

16. The control system of claim 13 , wherein the first controller is configured to generate PWM control signals to control the interleaved buck converter.

17. The control system of claim 13 , wherein the second controller is configured to generate PWM control signals to control the interleaved full-bridge converter.

18. The control system of claim 13 , wherein the third controller is configured to generate PWM control signals to control the interleaved inverter.

19. A method for generating a plurality of regulated supply voltages, the method comprising:
generating regulated low-voltage DC using power provided by a DC power source, wherein the regulated low-voltage DC is generated using an interleaved buck converter, and the DC power source is an unregulated DC power source;
generating regulated high-voltage AC using power provided by the DC power source, wherein the regulated high-voltage AC is generated using an interleaved inverter;
generating regulated high-voltage DC using power provided by the DC power source, wherein the regulated high-voltage DC is generated using an interleaved full-bridge converter; and
controlling the interleaved buck converter, the interleaved full-bridge converter, and the interleaved inverter in response to a plurality of system control signals.

20. The method of claim 19 , wherein the DC power source comprises a fuel cell.

Assignees

• Boeing Co

Inventors

• Karimi Kamiar
• Liu Shengyi
• Wang Duanyang
• De Leon Francisco
• Tang Qingquan
• Gu Dazhong
• Czarkowski Dariusz
• Colak Kerim
• Bojarski Mariusz

Classifications

• H03H7/427

  Common-mode filters (H02J3/01 and H02M1/126 takes precedence) · CPC title

• H02M3/33546

  with automatic control of the output voltage or current (H02M3/33561 takes precedence) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02M3/1584

  with a plurality of power processing stages connected in parallel · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title