飞机电气系统相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
41	Protective device for the electrical system of aircraft	US82436859	1959-07-01	US3030473A	1962-04-17	JACK LIKER

42	METHOD AND APPARATUS FOR TESTING AIRCRAFT ELECTRICAL SYSTEMS	PCT/EP2007/010375	2007-11-29	WO2009068061A1	2009-06-04	KNOOP, Sven; GALINSKI, Mike
The present invention provides a method and apparatus for testing an aircraft control system. The method comprises the steps of : coupling a test device (1) to a plurality of separate test points in an aircraft control system simultaneously; selecting each of the plurality of test points individually, such that the test device is enabled for electrical connection with the selected one of the plurality of test points; conducting a test on the control system at each of the plurality of test points selected with the selector means (20,22) using the test device, including detecting a signal or voltage at the test point selected with the selector means; indicating a result of the test at the selected test point to an operator.
43	AIRCRAFT SELECTIVELY ENGAGEABLE ELECTRIC TAXI SYSTEM	US14099162	2013-12-06	US20140332622A1	2014-11-13	DAVID LANE CHARLES; DONALD JEFFREY CHRISTENSEN
An electric taxi system (ETS) for an aircraft may include an annular output gearbox positioned between a wheel and a main strut of a main landing gear of the aircraft. The output gearbox may surround a brake piston assembly of the wheel of the aircraft. One or more selectively operable engaging assemblies, for selectively coupling the ETS with the wheel of the aircraft, may be positioned between the output gearbox and the wheel of the aircraft. The one or more selectively operable engaging assemblies may be coupled with an output gear of the output gearbox to rotate with the output gear.
44	ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT	EP13825807.4	2013-07-29	EP2880734A1	2015-06-10	IWASHIMA, Atsushi; SUGIMOTO, Kazushige; MATSUO, Kazuya; BREIT, Joseph, S.; NOZARI, Farhad
A power stabilizing device in a system includes as a portion of a power converter section, a second PWM converter provided between a second primary AC bus and a second DC bus in an electric system and configured to perform mutual conversion between DC power and AC power. A power stabilizing control section in the power stabilizing device controls charging and discharging of a secondary battery based on a voltage and a frequency in the second primary AC bus, thereby stabilizing the electric system.
45	AIRCRAFT ELECTRICAL SYSTEM AND ASSOCIATED MANAGEMENT METHOD	US13871404	2013-04-26	US20130285443A1	2013-10-31	RENAUD LOISON; OLIVIER SAVIN
The system according to the invention comprises: an electrical network (20), and a regulating assembly (24). The regulating assembly (24) includes a secondary electric power source (58), a conversion assembly (60) for an additional electric power injected on the electrical network (20), the conversion assembly (60) being able, in a first configuration, to consume the additional electric power present on the network (20) to create a supply fluid of the secondary source (58). The assembly (60) includes a reservoir (62A, 62B) for each supply fluid, to collect the supply fluid produced by the conversion assembly (60).
46	POWER SUPPLY UNIT FOR USE WITH AN AIRCRAFT ELECTRICAL SYSTEM	US12052821	2008-03-21	US20080238191A1	2008-10-02	John D. Cottingham; Scott A. Davis; James R. Berllner; Robert A. Lockmiller
A power supply unit that provides uninterrupted power to an aircraft power bus during switchovers of the aircraft bus from one power source to another. The power supply unit includes circuitry to distinguish between loss of bus power due to switchovers between power sources and loss of bus power due to shutdown of the aircraft. The power supply unit includes a low voltage lockout circuit to interrupt the supply of power when the aircraft bus voltage falls below a minimum value.
47	Aircraft electrical system and associated management method	US13871404	2013-04-26	US09487166B2	2016-11-08	Renaud Loison; Olivier Savin
The system according to the invention comprises: an electrical network, and a regulating assembly. The regulating assembly includes a secondary electric power source, a conversion assembly for an additional electric power injected on the electrical network, the conversion assembly being able, in a first configuration, to consume the additional electric power present on the network to create a supply fluid of the secondary source. The assembly includes a reservoir for each supply fluid, to collect the supply fluid produced by the conversion assembly.
48	Method and apparatus for testing aircraft electrical systems	US12744955	2007-11-29	US08564300B2	2013-10-22	Sven Knoop; Mike Galinski
A method, and corresponding apparatus, for testing an aircraft control system is disclosed. The method includes simultaneously coupling a test device to a plurality of separate test points in an aircraft control system, selecting each test point individually such that the test device is enabled for electrical connection with the selected test point, conducting a test on the control system at each selected test point using the test device, detecting a signal or voltage at the selected test point, and indicating a result of the test at the selected test point to an operator.
49	Power supply unit for use with an aircraft electrical system	US12052821	2008-03-21	US07750496B2	2010-07-06	John D. Cottingham, III; Scott A. Davis; James R. Berliner; Robert A. Lockmiller
A power supply unit that provides uninterrupted power to an aircraft power bus during switchovers of the aircraft bus from one power source to another. The power supply unit includes circuitry to distinguish between loss of bus power due to switchovers between power sources and loss of bus power due to shutdown of the aircraft. The power supply unit includes a low voltage lockout circuit to interrupt the supply of power when the aircraft bus voltage falls below a minimum value.
50	SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.	EP10706013.9	2010-01-08	EP2377235B8	2015-12-02	DE WERGIFOSSE, Eric

51	SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.	EP10706013.9	2010-01-08	EP2377235A2	2011-10-19	DE WERGIFOSSE, Eric
The invention relates to an electrical system for starting up an engine (18, 20, 22), including: an AC/DC rectifier (12), supplied with power by an AC power network (14) in order to generate a first DC voltage Vdc; a DC/AC conversion module (12) for generating, on the basis of said first DC voltage Vdc, an AC voltage for starting up the engine, comprising n phase k inverters arrange in parallel (k>1) and generating power at least two times less than a maximum power Pmax that is required to start up the engine. The two power supply lines of each inverter are connected to an electronic protection device that receives the first DC voltage Vdc, and the n outputs of each inverter generate the AC voltage for starting up the engine by means of n inductors in series.
52	SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.	EP10706013.9	2010-01-08	EP2377235B1	2015-09-02	DE WERGIFOSSE, Eric

53	Electrical system for starting up aircraft engines	US13143848	2010-01-08	US08958181B2	2015-02-17	Eric de Wergifosse
An electrical system for starting an engine is provided. The system includes: an AC/DC rectifier powered by an AC power network to deliver a first DC voltage Vdc, a DC/AC converter module for delivering an AC voltage for starting the engine from said first DC voltage Vdc, and k n-phase inverters arranged in parallel (k>1) and each delivering power no greater than half a maximum power Pmax required for starting the engine, and the two power supply lines of each of the inverters are connected to an electronic protection device receiving the first DC voltage Vdc, and the n outputs of each of the inverters delivering the AC voltage for starting the engine via n respective series inductors.
54	ELECTRICAL SYSTEM FOR STARTING UP AIRCRAFT ENGINES	US13143848	2010-01-08	US20110273011A1	2011-11-10	Eric de Wergifosse
An electrical system (18, 20, 22) for starting an engine, the system comprising: an AC/DC rectifier (12) powered by an AC power network (14) to deliver a first DC voltage Vdc, and a DC/AC converter module (16) for delivering an AC voltage for starting the engine from said first DC voltage Vdc, the system comprising k n-phase inverters arranged in parallel (k>1) and each delivering power no greater than half a maximum power Pmax required for starting the engine, and the two power supply lines of each of the inverters are connected to an electronic protection device receiving the first DC voltage Vdc, and the n outputs of each of the inverters delivering the AC voltage for starting the engine via n respective series inductors.
55	Auxiliary electrical generating system for jet aircraft	US3662975D	1970-09-21	US3662975A	1972-05-16	DRISKILL ROBERT E
An auxiliary electrical generating system for jet aircraft wherein compressed air is withdrawn from a jet engine and used to operate a pneumatic turbine which in turn drives a generator. An ancillary gas source may be included for supplying compressed gas to the turbine in the event of engine failure. This abstract is neither intended to define the invention of the application which, of course, is measured by the claims, nor is it intended to be limiting as to scope of the invention in any way.
56	Aircraft power system and apparatus for supplying power to an aircraft electrical system	US11693486	2007-03-29	US07928607B2	2011-04-19	Fred Oliver; Allan Saldecki
An aircraft power system is provided having an aircraft power supply and a bidirectional switch. The aircraft power supply includes an alternator, a battery and a load. The bidirectional switch is coupled between one of the alternator and the battery, and the load. The switch includes a first FET, a second FET and timing circuitry. A source of the first FET is coupled with a source of the second FET. A drain of the first FET is coupled with one of the alternator and the battery. A drain of the second FET is coupled with the load. The timing circuitry is configurable to generate a control signal deliverable to a gate of the first FET and the second FET for setting the first FET in selective on and off positions and the second FET in corresponding selective off and on position.
57	Aircraft Power System and Apparatus for Supplying Power to an Aircraft Electrical System	US11693486	2007-03-29	US20080238201A1	2008-10-02	Fred Oliver; Allan Saldecki
An aircraft power system is provided having an aircraft power supply and a bidirectional switch. The aircraft power supply includes an alternator, a battery and a load. The bidirectional switch is coupled between one of the alternator and the battery, and the load. The switch includes a first FET, a second FET and timing circuitry. A source of the first FET is coupled with a source of the second FET. A drain of the first FET is coupled with one of the alternator and the battery. A drain of the second FET is coupled with the load. The timing circuitry is configurable to generate a control signal deliverable to a gate of the first FET and the second FET for setting the first FET in selective on and off positions and the second FET in corresponding selective off and on position.
58	ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT	EP13846974.7	2013-07-29	EP2880738A2	2015-06-10	IWASHIMA, Atsushi; SUGIMOTO, Kazushige; MATSUO, Kazuya; BREIT, Joseph, S.; NOZARI, Farhad
An electric system of an aircraft includes a power stabilizing device connected to a primary AC bus and a secondary battery. The secondary battery has a rated voltage which allows the secondary battery to absorb regenerative power from a control surface actuator. Based on a voltage and a frequency in the primary AC bus, charging/discharging of the secondary battery is controlled to stabilize the electric system.
59	Electrical systems architecture for an aircraft, and related operating methods	US11944199	2007-11-21	US07687927B2	2010-03-30	Mark S. Shander; Richard A. Cote; Michael L. Drake; Howard Carter, III; John T. Peters; Casey Y. K. Ng; Michael S. Hoag; John T. Paterson
An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).
60	ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT	EP13825807	2013-07-29	EP2880734A4	2016-04-27	IWASHIMA ATSUSHI; SUGIMOTO KAZUSHIGE; MATSUO KAZUYA; BREIT JOSEPH S; NOZARI FARHAD
A power stabilizing device in a system includes as a portion of a power converter section, a second PWM converter provided between a second primary AC bus and a second DC bus in an electric system and configured to perform mutual conversion between DC power and AC power. A power stabilizing control section in the power stabilizing device controls charging and discharging of a secondary battery based on a voltage and a frequency in the second primary AC bus, thereby stabilizing the electric system.

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