Aircraft comprising a reversible rotary electrical machine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B60L-001/00
B64D-041/00
출원번호
US-0967765
(2010-12-14)
등록번호
US-9162773
(2015-10-20)
발명자
/ 주소
Mavier, Jérôme
Foch, Etienne
Lando, Jean-Louis
Roboam, Xavier
Barkowsky, Jan
출원인 / 주소
AIRBUS OPERATIONS SAS
대리인 / 주소
Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a
The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a reversible power converter (40) connected to said machine (30) and to said network (70), and a control circuit (50) configured to control said converter (40) for, in a motor operating mode of said machine (30), taking a supply current from said network (70) to supply said machine (30) and drive said wheel (35), and, in an alternator operating mode of said machine (30), in which a stream of air flows in said first ventilation duct (15) and imparts movement to said wheel (35), to provide supply power to said network (70) which is generated by said machine (30) driven by said wheel (35).
대표청구항▼
1. An aircraft comprising: at least one rotary electrical machine;at least one wheel for imparting movement to a stream of air, linked to said at least one rotary electrical machine;at least one system to cool;at least one first ventilation duct configured to supply said wheel with air;an electricit
1. An aircraft comprising: at least one rotary electrical machine;at least one wheel for imparting movement to a stream of air, linked to said at least one rotary electrical machine;at least one system to cool;at least one first ventilation duct configured to supply said wheel with air;an electricity distribution network;at least one power converter connected to said at least one rotary electrical machine and to said electricity distribution network; andat least one control circuit configured to control said at least one power converter;at least one second ventilation duct in which are disposed said at least one rotary electrical machine and at least partially said at least one system to cool;wherein said at least one rotary electrical machine is reversible and said at least one power converter is reversible, said at least one control circuit being configured to control said at least one reversible power converter for:in a first motor operating mode of said at least one reversible rotary electrical machine, taking a supply current from said electricity distribution network to electrically supply said reversible rotary electrical machine and thereby drive said at least one wheel for imparting movement to a stream of air, by virtue of which said at least one system to cool is cooled; andin a second alternator operating mode of said at least one reversible rotary electrical machine, in which a stream of air flows in said at least one first ventilation duct and imparts movement to said at least one wheel, providing supply power to said electricity distribution network, which power is generated by said reversible rotary electrical machine which is driven by said wheel,wherein said at least one first ventilation duct includes a device for regulating a rate of flow of the stream of air entering that first duct, and the device for regulating is positioned at an entrance to the first ventilation duct, andwherein said first ventilation duct is juxtaposed against said second ventilation duct and comprises an air inlet and an opposite air outlet, which air outlet discharges into said second ventilation duct. 2. An aircraft according to claim 1, comprising a control module configured to control said device for regulating the rate of flow of the stream of air entering said first duct, by virtue of which said regulating device is able to minimize the rate of flow of air in motor mode and adapt or even maximize the rate of flow of air in alternator mode, depending on need for energy in the network. 3. An aircraft according to claim 1, comprising at least one energy storage module electrically connected to said electricity distribution network. 4. An aircraft according to claim 1, wherein at least one control circuit is configured to control the power delivered by said at least one reversible rotary electrical machine by adapting the current passing through at least one reversible converter. 5. An aircraft according to claim 1, wherein at least one control circuit is configured to control voltage supplied by at least one reversible converter to said electricity distribution network. 6. An aircraft according to claim 1, wherein at least one control circuit is configured to control current supplied by at least one reversible converter to said electricity distribution network, by virtue of which said at least one rotary electrical machine acts as a source of current. 7. An aircraft according to claim 1, comprising a d.c./d.c. type electrical energy coupling device disposed between a first reversible converter and a second reversible converter, said first reversible converter being connected to said at least one reversible rotary electrical machine and said second reversible converter being connected to said distribution network, said at least one control circuit being configured to control the voltage supplied by said d.c./d.c. type electrical energy coupling device to said second reversible converter. 8. An aircraft according to claim 1, comprising at least one energy storage module connected to the distribution network and to said at least one reversible converter, and a checking unit which is configured to check said at least one control circuit, said checking unit furthermore being configured to check voltage at terminals of said at least one energy storage module. 9. An aircraft according to claim 8, wherein said checking unit is configured to check quantities of current entering and current leaving said at least one energy storage module. 10. An aircraft according to claim 1, wherein said distribution network transports alternating or direct current electrical energy. 11. An aircraft according to claim 1, wherein said at least one reversible rotary electrical machine operates in alternator mode when the aircraft is in what is referred to as emergency operation. 12. An aircraft according to claim 1, wherein said system to cool is a heat exchanger.
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이 특허에 인용된 특허 (4)
Williams Samuel B. ; Jones John F. ; Thompson ; Jr. Robert S., Environment control unit for turbine engine.
Soma, Takaya; Yoshida, Hiroshi; Mogari, Takeshi; Suzuki, Takahiro, Maximum output setting device, driving device including the maximum output setting device, power output apparatus including the driving device, motor vehicle mounted with the power output apparatus, and maximum output setting method.
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