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

• US 7,701,082 B2
• Filed: 10/30/2006
• Issued: 04/20/2010
• Est. Priority Date: 10/30/2006
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc., Orange S.A.
• Original Assignee: Honeywell International Inc.
• Inventors: Lazarovich, David, Rusan, Ileana, Dangeti, Srinivasa R.
• Primary Examiner(s): Paladini; Albert W
• Assistant Examiner(s): KAPLAN, HAL IRA
• Application Number:
  US11/589,196
• Publication Number:
  US 20080100135A1
• Time in Patent Office: 1,268 Days
• Field of Search: 307/46, 307/19, 307/21, 307/22, 307/26, 307/45, 307/82, 244/53.A, 244/58, 244/60
• US Class Current: 307/22
• 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 converting and regulating voltage in an aircraft, said apparatus comprising:

a starter converter for starting an auxiliary power unit (APU) via the supply of an AC voltage and frequency wave;

an AC to DC converter of the starter converter being connected to extract power from an AC bus at a first voltage, the AC bus at the first voltage supplying AC power to various AC loads on the aircraft;

the starter converter having a DC bus connection therein;

the AC to DC converter connected to extract power from the AC bus of the aircraft and deliver DC power to the DC bus connection;

an APU start unit receiving DC power from the DC bus connection,

the DC bus connection receiving power from

a bi-directional DC to DC converter, connected to extract power from or deliver power to the DC bus connection of the starter converter,

wherein said DC to DC converter

is controlled to operate in a first direction to receive a DC power from the DC bus connection of the starter converter and to output DC power at a first regulated DC voltage adjusted to charge a battery, and

is controlled to operate in a second direction to receive DC power at a battery DC voltage from said battery and to output DC power at a second regulated DC voltage to the DC bus connection of the starter converter, to power the starter converter independently or in combination with the AC bus of the aircraft.

2. The apparatus according to claim 1 wherein:

the starter converter comprises a rectifier; and

wherein the aircraft AC bus is operationally connected to the DC bus connection of the starter converter through the rectifier.

3. The apparatus according to claim 1,

wherein the rectifier is part of an AC/DC rectifier system, and

the APU is operationally connected to the DC bus connection of the starter converter by a DC/AC converter in the APU start unit.

4. An aircraft electrical power DC system, said system comprising:

a battery; and

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 DC power from a DC bus, the DC bus receiving power from an AC to DC converter in an APU starter converter operationally connected to an AC power bus, wherein the AC power bus supplies AC power to various AC loads on the aircraft, 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 DC power at a battery DC voltage from said battery and outputs DC power at a second regulated DC voltage, via the DC bus, to an APU start unit having a DC to AC converter therein, for starting an APU independently or in combination with said AC power bus.

5. The system according to claim 4, wherein said constant voltage bus is an aircraft main power 28 Vdc bus.

6. The system according to claim 4, wherein said bi-directional DC to DC converter is controlled to compensate temperature or variations in input feed voltage so that the output voltage is controlled to achieve the desired level.