Aircraft DC power distribution systems and methods
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H02J-003/38
H02J-001/10
H02J-003/00
H02J-004/00
B64D-047/00
H02M-007/02
H02J-013/00
출원번호
US-0729925
(2015-06-03)
등록번호
US-10090676
(2018-10-02)
발명자
/ 주소
Knowles, Jeffrey A.
Cleek, Keith J.
Lee, Chris K.
Theno, Tad W.
Wong, Ivan H.
출원인 / 주소
Northrop Grumman Systems Corporation
대리인 / 주소
Tarolli, Sundheim, Covell & Tummino LLP
인용정보
피인용 횟수 :
0인용 특허 :
18
초록▼
Systems and methods are provided for distributing DC power in an aircraft. In one example, a method is provided that includes generating a plurality of DC voltages from a plurality of independent sources driven by one or more turbines of the aircraft, providing each of the plurality of DC voltages t
Systems and methods are provided for distributing DC power in an aircraft. In one example, a method is provided that includes generating a plurality of DC voltages from a plurality of independent sources driven by one or more turbines of the aircraft, providing each of the plurality of DC voltages to respective dedicated DC buses, and setting a plurality of switches that selectively couples a first set of dedicated DC buses to a synchronization bus to allow for bus sharing between the first set of dedicated DC buses and bus isolation of a second set of dedicated DC buses.
대표청구항▼
1. An aircraft power distribution system comprising: a plurality of generators, associated with an aircraft, that generate respective AC voltage signals in response to mechanical energy generated by one or more aircraft turbines;a plurality of AC/DC converters, associated with the aircraft, that eac
1. An aircraft power distribution system comprising: a plurality of generators, associated with an aircraft, that generate respective AC voltage signals in response to mechanical energy generated by one or more aircraft turbines;a plurality of AC/DC converters, associated with the aircraft, that each receive a respective AC output signal from a respective generator and generate a respective DC voltage;a plurality of dedicated DC buses, wherein each dedicated DC bus is associated with a respective generator and a respective AC/DC converter to receive a respective DC voltage, each dedicated bus providing power to one or more associated dedicated bus loads;a synchronization bus selectively coupleable to each dedicated DC bus by respective synchronization bus line switches to allow for bus sharing between a first set of dedicated DC buses of the plurality of dedicated DC buses and isolating a second set of selected dedicated DC buses of the plurality of dedicated DC buses; anda vehicle management system to issue a load share command, to the plurality of AC/DC converters, that governs a percentage of power that is supplied by each of the plurality of AC/DC converters. 2. The system of claim 1, further comprising a bus controller that controls the selective closing and opening of the synchronization bus line switches. 3. The system of claim 2, wherein the bus controller is communicatively coupled to the vehicle management system of the aircraft to at least one of receive commands and share status information on a state of at least one of the aircraft power distribution system and the aircraft. 4. The system of claim 2, wherein the bus controller receives discrete input feedback from the power distribution system in determining a state of the synchronization bus line switches. 5. The system of claim 2, wherein each AC/DC converter is part of an inverter controller that communicates with the bus controller to share status information of the power distribution system. 6. The system of claim 5, wherein each inverter controller includes a bus line contactor switch that couples and decouples the respective AC/DC converter from its respective dedicated bus. 7. The system of claim 1, wherein at least one of the generators is associated with a high pressure spool of the aircraft, and at least one of the generators is associated with a low pressure spool of the aircraft. 8. The system of claim 1, wherein at least one of the generators is associated with an auxiliary power unit of the aircraft. 9. The system of claim 1, wherein the plurality of generators comprise a first generator associated with a first high pressure spool coupled to a first engine of the aircraft and a second generator associated with a first low pressure spool coupled to the first engine of the aircraft, and a third generator associated with a second high pressure spool coupled to a second engine of the aircraft and a fourth generator associated with a second low pressure spool coupled to the second engine of the aircraft. 10. An aircraft power distribution system comprising: a first generator, associated with an aircraft, that generates a first AC voltage signal from a high pressure spool;a second generator, associated with the aircraft, that generates a second AC voltage signal from a low pressure spool;a first AC/DC converter, associated with the aircraft, that converts the first AC voltage signal to a first DC voltage;a second AC/DC converter, associated with the aircraft, that converts the second AC voltage signal to a second DC voltage signal;a first dedicated DC bus that receives the first DC voltage and provides the first DC voltage to at least one first dedicated bus load;a second dedicated DC bus that receives the second DC voltage and provides the second DC voltage to at least one second dedicated bus load;a synchronization bus selectively coupleable to the first dedicated DC bus by a first bus line switch and the second dedicated DC bus by a second bus line switch to allow for selective bus sharing between the first and second dedicated DC buses, wherein there are not any bus loads that are directly coupled to the synchronization bus;a bus controller that controls selective closing and opening of the first and second synchronization bus line switches; anda vehicle management system to issue a load share command, to the first and second AC/DC converters, that governs a percentage of power that is supplied by each of the first and second AC/DC converters. 11. The system of claim 10, wherein the bus controller is communicatively coupled to the vehicle management system of the aircraft to at least one of receive commands and share status information on a state of at least one of the aircraft power distribution system and the aircraft. 12. The system of claim 10, wherein the bus controller receives discrete input feedback from the aircraft power distribution system. 13. The system of claim 10, further comprising: a third generator that generates a third AC voltage signal from an auxiliary power unit;a third AC/DC converter that converts the third AC voltage signal to a third DC voltage;a third dedicated DC bus that receives the third DC voltage and provides the third DC voltage to at least one third dedicated bus load, wherein the synchronization bus is selectively coupleable to the third dedicated DC bus by a third bus line switch to allow for selective bus sharing and bus isolation between the first, second and third dedicated DC buses via the bus controller. 14. The system of claim 10, wherein each AC/DC converter is part of an inverter controller that communicates with the bus controller to share status information of the aircraft power distribution system. 15. The system of claim 14, wherein each inverter controller includes a bus line contactor switch that couples and decouples the respective AC/DC converter from its respective dedicated DC bus. 16. The system of claim 10, further comprising: a third generator that generates a third AC voltage signal from a second high pressure spool;a fourth generator that generates a fourth AC voltage signal from a second low pressure spool;a third AC/DC converter that converts the third AC voltage signal to a third DC voltage;a fourth AC/DC converter that converts the fourth AC voltage signal to a fourth DC voltage signal;a third dedicated DC bus that receives the third DC voltage and provides the third DC voltage to at least one third dedicated bus load;a fourth dedicated DC bus that receives the fourth DC voltage and provides the fourth DC voltage to at least one fourth dedicated bus load, wherein the synchronization bus is selectively coupleable to the third dedicated DC bus by a third bus line switch and the fourth dedicated DC bus by a fourth bus line switch to allow for selective bus sharing between the first, second, third and fourth dedicated DC buses. 17. A method of distributing DC power in an aircraft, the method comprising; generating, with a plurality of AC/DC converters associated with the aircraft, a plurality of DC voltages from a plurality of independent sources driven by one or more turbines of the aircraft;providing each of the plurality of DC voltages to respective dedicated DC buses;setting a plurality of switches that selectively couples a first set of dedicated DC buses to a synchronization bus to allow for bus sharing between the first set of dedicated DC buses and isolating a second set of dedicated DC buses; andissuing a load share command, to the plurality of AC/DC converters, that governs a percentage of power that is supplied by each of the plurality of AC/DC converters. 18. The method of claim 17, further comprising monitoring at least one parameter of the aircraft and dynamically setting the plurality of switches based on changes in the monitored at least one parameter. 19. The method of claim 17, further comprising dynamically setting the plurality of switches based on commands received from a vehicle management system of the aircraft. 20. The method of claim 17, wherein the independent sources comprise at least one high pressure spool, at least one low pressure spool, and an auxiliary power unit.
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이 특허에 인용된 특허 (18)
Calvignac, Julien N E; Pons Perez, Marc, Aircraft power management system.
Ejzak Richard P. (Rockford IL) Thom James B. (Rock City IL) Peterson William J. (Rockford IL) Glennon Timothy F. (Rockford IL), Control for an electrical generating and distribution system, and method of operation.
Koeppen, Carsten; Marquardt, Till; Thiel, Sebastian, Device and method for converting supplied electrical power into mechanical power to start at least one engine.
Atkey, Warren A.; Bernier, Alan T.; Bowman, Michael D.; Campbell, Thomas A.; Cruse, Jonathan M.; Fiterman, Charles J.; Meis, Charles S.; Ng, Casey; Nozari, Farhad; Zielinski, Edward, Electric-based secondary power system architectures for aircraft.
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