Aerospace electrical power DC subsystem configuration using multi-functional DC/DC converter

• US 20080100135A1
• Filed: 10/30/2006
• Published: 05/01/2008
• Est. Priority Date: 10/30/2006
• Status: Active Grant

• Current Assignee: Honeywell International Inc., Orange S.A.
• Original Assignee: Honeywell International Inc.
• Inventors: Dangeti, Srinivasa B., Lazarovich, David, Rusan, Ileana
• Granted Patent: US 7,701,082 B2
• Time in Patent Office: Days
• US Class Current: 307/9.1
• CPC Class Codes: H02J 5/00 Circuit arrangements for transfer of electric power between ac networks and dc networks H02J3/36 takes precedence
• CPC Class Codes: H02J 7/02 for charging batteries from ac mains by converters
• CPC Class Codes: H02J 7/34 Parallel operation in networks using both storage and other dc sources, e.g. providing buffering H02J7/14 takes precedence
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

An apparatus for regulating voltage and aerospace electrical power systems are implemented. A multi-functional apparatus for regulating voltage, according to one embodiment, comprises: a DC to DC converter (315), wherein the DC to DC converter (315) is controlled to operate in a first direction to receive a DC voltage from a first bus (329) and to output a first regulated DC voltage adjusted to charge a battery (307), wherein the first bus (329) receives power from a second bus (201), and is controlled to operate in a second direction to receive a battery DC voltage from the battery (307) and to output a second regulated DC voltage to the first bus (329) to power a load (231) independently or in combination with the second bus (201).

Claims

1. A multi-functional apparatus for regulating voltage, said apparatus comprising:

a DC to DC converter, wherein said DC to DC converter

is controlled to operate in a first direction to receive a DC voltage from a first bus and to output a first regulated DC voltage adjusted to charge a battery, wherein said first bus receives power from a second bus, and

is controlled to operate in a second direction to receive a battery DC voltage from said battery and to output a second regulated DC voltage to said first bus, to power a load independently or in combination with said second bus.

2. The apparatus according to claim 1, wherein said load is an auxiliary power unit operationally connected to said second bus.

3. The apparatus according to claim 1, wherein said first regulated DC voltage powers a constant DC voltage bus connected to said battery.

4. The apparatus according to claim 1, wherein said second bus is an aircraft AC bus connected to said first bus through a rectifier.

5. The apparatus according to claim 1, wherein said first bus is a power bus of an aerospace power system with at least one electrical load connected thereto.

6. The apparatus according to claim 1, wherein said multi-functional apparatus for regulating voltage is included in an aerospace electrical power DC system.

7. The apparatus according to claim 1, wherein

said second bus is an aircraft AC bus connected to said first bus through an AC/DC rectifier system, and

said load is an auxiliary power unit operationally connected to said first bus by a DC/AC converter.

8. The apparatus according to claim 1, wherein said first regulated DC voltage is maintained within a compliant range of said battery.

9. The apparatus according to claim 1, wherein said second regulated DC voltage is maintained within a compliant range of said first bus.

10. An aerospace electrical power DC system, said system comprising:

a battery;

a bi-directional DC to DC converter operating in a first direction and in a second direction, wherein

in said first direction, said DC to DC converter receives a DC voltage from an AC power bus through a rectification system operationally connected to said AC power bus, and outputs a first regulated DC voltage to a constant voltage bus to charge a battery, and

in said second direction, said DC to DC converter receives a battery DC voltage from said battery and outputs a second regulated DC voltage for starting a load independently or in combination with said AC power bus.

11. The system according to claim 10, wherein said load is an auxiliary power unit operationally connected to said AC power bus.

12. The system according to claim 10, wherein said constant voltage bus is an aircraft main power 28 Vdc bus.

13. The system according to claim 10, wherein

said AC power bus is connected to said DC to DC converter through an AC/DC rectifier system, and

said load is an auxiliary power unit operationally connected to said DC to DC converter by a DC/AC converter system.

14. The system according to claim 10, wherein said bi-directional DC to DC converter is controlled to compensate for environmental conditions such as temperature.

15. The system according to claim 10, wherein said second regulated DC voltage is maintained within a compliant range of said load.

16. An aerospace DC power supply system, said aerospace DC power supply system utilizing a single DC to DC converter to

supply a constant DC power bus using rectified power from an aircraft AC bus, and charge a battery continuously connected to said constant DC power bus,

wherein said system further utilizes said single DC to DC converter to start an auxiliary power unit using said battery, upon experiencing a condition that power from said aircraft AC bus is insufficient or not available to start said auxiliary power unit.

17. The system according to claim 16, wherein said single DC to DC converter maintains a regulated DC voltage to charge said battery within a compliant range of said battery.

18. The system according to claim 16, wherein said single DC to DC converter maintains a regulated DC voltage to start said auxiliary power unit within a compliant range of said auxiliary power unit.

19. The system according to claim 16, wherein said system

utilizes said single DC to DC converter to start said auxiliary power unit using said battery and in combination with power from said aircraft AC bus.

20. The system according to claim 16, wherein said DC to DC converter is controlled to compensate for environmental conditions such as temperature.