Aerospace electrical power DC subsystem configuration using multi-functional DC/DC converter
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H02J-003/02
H02J-003/38
H02J-005/00
B64D-041/00
출원번호
UP-0589196
(2006-10-30)
등록번호
US-7701082
(2010-05-20)
발명자
/ 주소
Lazarovich, David
Dangeti, Srinivasa R.
Rusan, Ileana
출원인 / 주소
Honeywell International Inc.
대리인 / 주소
Oral Caglar, Esq.
인용정보
피인용 횟수 :
7인용 특허 :
18
초록▼
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 r
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).
대표청구항▼
We claim: 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 connecte
We claim: 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.
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이 특허에 인용된 특허 (18)
Aberle, Markus; Boehmisch, Mathias; Zinser, Wolfgang, Apparatus for generating and distributing electrical power to loads in a vehicle.
Dubovsky, Stephen M., Grid-connected power systems having back-up power sources and methods of providing back-up power in grid-connected power systems.
DeDoncker Rik W. (Niskayuna NY) Kheraluwala Mustansir H. (Madison WI) Divan Deepakraj M. (Madison WI), Power conversion apparatus for DC/DC conversion using dual active bridges.
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