[특허]System for electrical generation, conversion, distribution, and starting on board an aircraft

Airbus Operations SAS

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System for electrical generation, conversion, distribution, and starting on board an aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-041/00
미국특허분류(USC)	244/058;
출원번호	US-0445944 (2007-10-25)
등록번호	US-8136756 (2012-03-20)
우선권정보	FR-06 54589 (2006-10-27)
국제출원번호	PCT/EP2007/061475 (2007-10-25)
§371/§102 date	20090417 (20090417)
국제공개번호	WO2008/049886 (2008-05-02)
발명자 / 주소	Duces, Marc Lando, Jean-Louis Foch, Etienne
출원인 / 주소	Airbus Operations SAS
대리인 / 주소	Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
인용정보	피인용 횟수 : 9 인용 특허 : 3

초록

A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of “bleedless” type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines.

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1. A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type with an electrical power architecture with no pneumatic circuits, comprising: first electrical distribution channels that supply high power loads specific to aircraft of the “bleedless” type including at least one of a motor compressor and an air conditioning system; andsecond electrical distribution channels that supply other loads including at least one of a technical load, avionics, lighting, a fuel pump, and a commercial load, whereinthe first and second electrical distribution channels are separated, operate in parallel, and supplied with power by separate generators of an engine of the aircraft in a configuration under normal conditions. 2. The system according to claim 1, comprising: at least two engines;at least two first electrical distribution channels for high power loads; andat least two second electrical distribution channels for other loads. 3. The system according to claim 1, wherein each first electrical distribution channel is a three-phase 115 volt or 230 volt AC system. 4. The system according to claim 3, wherein a frequency of the first electrical distribution channels is between 360 and 800 Hz. 5. The system according to claim 3, wherein a frequency of the first electrical distribution channels is between 800 and 2000 Hz. 6. The system according to claim 3, wherein a frequency of the first electrical distribution channels is between 800 Hz and 2 KHz, and a frequency of the second electrical distribution channels is between 360 Hz and 800 Hz. 7. The system according to claim 2, wherein each generator that powers the first electrical distribution channels is a poly-phase machine having a number of phases equal to or greater than three. 8. The system according to claim 7, wherein the number of phases is equal to five or six. 9. The system according to claim 1, wherein each first electrical distribution channel includes one or two poly-phase rectifier bridges with six or more diodes to change the three-phase 230 volts AC to +/−270 volts DC. 10. The system according to claim 1, wherein all the generators are identical. 11. The system according to claim 10, wherein each generator is a brushless three-phase synchronous generator that is reversible. 12. The system according to claim 11, wherein each generator is a generator that supplies 115 volts or 230 volts AC with a frequency between 360 Hz and 800 Hz. 13. The system according to claim 10, comprising: at least two engines;two first electrical distribution channels for high power loads; andtwo second electrical distribution channels for other loads. 14. The system according to claim 13, wherein each first electrical distribution channel for high power loads includes: an electric starter-generator,an AC busbar,two simple six-diode rectifier bridges with reduced filtering,two DC busbars,two reduced filtering inverters,a transformer-rectifier,a busbar, anda battery. 15. The system according to claim 13, wherein each second electrical distribution channel for other loads includes: an electric starter-generator,an AC busbar,a converter, andan AC busbar. 16. The system according to claim 13, further comprising: a first master box that brings together two first power channels,a second master box that brings together two second power channels,a third master box that brings together the second electrical distribution channels at 230 volts and 115 volts AC, and 28 volt DC circuits, andan emergency back-up master box. 17. The system according to claim 1, comprising: at least two engines;four first electrical distribution channels for high power loads; andtwo second electrical distribution channels for other loads. 18. The system according to claim 17, comprising six identical starter-generators. 19. The system according to claim 17, further comprising: a first master box that brings together two of the first electrical distribution channels,a second master box that brings together two of the first electrical distribution channels,a third master box that brings together the second electrical distribution channels at 230 volts and 115 volts AC, and the 28 volt DC circuits, andan emergency back-up master box. 20. The system according to claim 17, further comprising a crossover between starter-generators and corresponding master boxes at different positions in a fuselage of the aircraft. 21. The system according to claim 1, comprising: at least two engines;four optimized first electrical distribution channels for high power loads; andtwo second electrical distribution channels for other loads. 22. The system according to claim 21, further comprising four power starter-generators dedicated to the optimized first electrical distribution channels and two conventional generators. 23. The system according to claim 22, wherein a principal stage of the starter-generators includes a poly-phase synchronous alternator: three-phase, five-phase, six-phase or with two three-phase systems with a phase angle difference of 30°. 24. The system according to claim 22, wherein the conventional generators are three-stage brushless three-phase synchronous machines. 25. The system according to claim 22, wherein the first electrical distribution channels operate in a variable frequency range that is between 800 and 2000 Hz. 26. The system according to claim 21, further comprising: a first master box that brings together two of the first electrical distribution channels, a DC busbar, and a three phase inverter,a second master box that brings together two of the first electrical distribution channels, a DC busbar, and a three phase inverter,a first half-panel that brings together first technical busbars of the second electrical distribution channels at 115 volts AC, and first commercial busbars of the second electrical distribution channels,a second half-panel that brings together second technical busbars of the second electrical distribution channels at 115 volts AC and second commercial busbars of the second electrical distribution channels,a third half-panel that brings together busbars, power converters, and a transformer rectifier, anda fourth half-panel that brings together busbars, power converters, and a transformer rectifier. 27. The system according to claim 21, further comprising intermittent power actuators supplied with power by a battery that supplies power for high but brief intermittent power demand peaks. 28. The system according to claim 1, wherein the aircraft is an aeroplane. 29. An aircraft comprising the system according to claim 1.

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System for electrical generation, conversion, distribution, and starting on board an aircraft

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이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 피인용횟수: 9

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IPC 상세정보(version : 201201)

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System for electrical generation, conversion, distribution, and starting on board an aircraft

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이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 피인용횟수: 9

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IPC 상세정보(version : 201201)

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