41. AIRCRAFT ELECTRICAL SYSTEM OPERATING METHOD

申请号: US14247708

申请日: 2014-04-08

公开（公告）号: US20160185462A1

公开（公告）日: 2016-06-30

发明人: Huw Llewellyn EDWARDS; Parag VYAS

A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.

42. Electric System Stabilizing System for Aircraft

申请号: US14418075

申请日: 2013-07-29

公开（公告）号: US20150183385A1

公开（公告）日: 2015-07-02

发明人: Atsushi Iwashima; Kazushige Sugimoto; Kazuya Matsuo; Joseph S. Breit; Farhad Nozari

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.

43. Electric System Stabilizing System for Aircraft

申请号: US14418074

申请日: 2013-07-29

公开（公告）号: US20150165990A1

公开（公告）日: 2015-06-18

发明人: Atsushi Iwashima; Kazushige Sugimoto; Kazuya Matsuo; Joseph S. Breit; Farhad Nozari

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.

44. ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT

申请号: PCT/US2013052596

申请日: 2013-07-29

公开（公告）号: WO2014062269A3

公开（公告）日: 2014-07-03

发明人: 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.

45. Protective device for the electrical system of aircraft

申请号: US82436859

申请日: 1959-07-01

公开（公告）号: US3030473A

公开（公告）日: 1962-04-17

发明人: JACK LIKER

46. METHOD AND APPARATUS FOR TESTING AIRCRAFT ELECTRICAL SYSTEMS

申请号: PCT/EP2007/010375

申请日: 2007-11-29

公开（公告）号: WO2009068061A1

公开（公告）日: 2009-06-04

发明人: 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.

47. AIRCRAFT SELECTIVELY ENGAGEABLE ELECTRIC TAXI SYSTEM

申请号: US14099162

申请日: 2013-12-06

公开（公告）号: US20140332622A1

公开（公告）日: 2014-11-13

发明人: 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.

48. ELECTRIC SYSTEM STABILIZING SYSTEM FOR AIRCRAFT

申请号: EP13825807.4

申请日: 2013-07-29

公开（公告）号: EP2880734A1

公开（公告）日: 2015-06-10

发明人: 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.

49. AIRCRAFT ELECTRICAL SYSTEM AND ASSOCIATED MANAGEMENT METHOD

申请号: US13871404

申请日: 2013-04-26

公开（公告）号: US20130285443A1

公开（公告）日: 2013-10-31

发明人: 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).

50. POWER SUPPLY UNIT FOR USE WITH AN AIRCRAFT ELECTRICAL SYSTEM

申请号: US12052821

申请日: 2008-03-21

公开（公告）号: US20080238191A1

公开（公告）日: 2008-10-02

发明人: 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.

51. Aircraft electrical system and associated management method

申请号: US13871404

申请日: 2013-04-26

公开（公告）号: US09487166B2

公开（公告）日: 2016-11-08

发明人: 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.

52. Method and apparatus for testing aircraft electrical systems

申请号: US12744955

申请日: 2007-11-29

公开（公告）号: US08564300B2

公开（公告）日: 2013-10-22

发明人: 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.

53. Power supply unit for use with an aircraft electrical system

申请号: US12052821

申请日: 2008-03-21

公开（公告）号: US07750496B2

公开（公告）日: 2010-07-06

发明人: 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.

54. SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.

申请号: EP10706013.9

申请日: 2010-01-08

公开（公告）号: EP2377235B8

公开（公告）日: 2015-12-02

发明人: DE WERGIFOSSE, Eric

55. SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.

申请号: EP10706013.9

申请日: 2010-01-08

公开（公告）号: EP2377235A2

公开（公告）日: 2011-10-19

发明人: 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.

56. SYSTEME ELECTRIQUE DE DEMARRAGE DES MOTEURS D'UN AERONEF.

申请号: EP10706013.9

申请日: 2010-01-08

公开（公告）号: EP2377235B1

公开（公告）日: 2015-09-02

发明人: DE WERGIFOSSE, Eric

57. Electrical system for starting up aircraft engines

申请号: US13143848

申请日: 2010-01-08

公开（公告）号: US08958181B2

公开（公告）日: 2015-02-17

发明人: 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.

58. ELECTRICAL SYSTEM FOR STARTING UP AIRCRAFT ENGINES

申请号: US13143848

申请日: 2010-01-08

公开（公告）号: US20110273011A1

公开（公告）日: 2011-11-10

发明人: 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.