Patents by Inventor Adrian Shipley
Adrian Shipley has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11079425Abstract: An electrical fault detecting system (10) for a circuit includes a conductor (20) delivering an electrical signal from a source (12) to a destination (14), a sheath (22) encircling the conductor, and a fault detection circuit (18). The sheath further includes an electrical insulator layer (24) and a conductive shield (26) encircling the conductor. The fault detection circuit is configured to detect a change in the electrical characteristics of the conductor and/or conductor sheath.Type: GrantFiled: February 23, 2015Date of Patent: August 3, 2021Assignee: GE Aviation Systems LLCInventors: Arthur Vorwerk Radun, Adrian Shipley
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Patent number: 9963095Abstract: An electrical power system for an aircraft having electrical loads and at least one jet engine with a high pressure spool and a low pressure spool, the electrical power system includes a first electrical machine driven by a first pressure spool and outputting a first voltage, a second electrical machine driven by a second pressure spool and outputting a second voltage, and an electrical distribution bus receiving the first and second voltages and supplying the voltages to the loads.Type: GrantFiled: May 1, 2014Date of Patent: May 8, 2018Assignee: GE Aviation Systems LimitedInventors: Hao Huang, Adrian Shipley
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Patent number: 9915694Abstract: A method for detecting electrical faults in an electrical circuit having transmission wires for power transmission includes determining whether a potential electrical fault condition exists along the transmission wires and confirming the potential electrical fault is an actual electrical fault. If the potential electrical fault is confirmed as an actual electrical fault, the method may disable the electrical circuit.Type: GrantFiled: November 22, 2013Date of Patent: March 13, 2018Assignee: GE AVIATION SYSTEMS LIMITEDInventors: Peter James Handy, Adrian Shipley
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Patent number: 9908489Abstract: A power distribution system for an aircraft is provided. The power distribution system comprises a first wiring harness connected to a power supply, at least one integrated switching power converter connected to the power supply through the first wiring harness, and at least one electrical load connected to a respective output of a respective integrated switching power converter through a second wiring harness.Type: GrantFiled: August 30, 2012Date of Patent: March 6, 2018Assignee: GE AVIATION SYSTEMS LIMITEDInventors: Adrian Shipley, Andrew Wyer
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Publication number: 20180017611Abstract: An electrical fault detecting system (10) for a circuit includes a conductor (20) delivering an electrical signal from a source (12) to a destination (14), a sheath (22) encircling the conductor, and a fault detection circuit (18). The sheath further includes an electrical insulator layer (24) and a conductive shield (26) encircling the conductor. The fault detection circuit is configured to detect a change in the electrical characteristics of the conductor and/or conductor sheath.Type: ApplicationFiled: February 23, 2015Publication date: January 18, 2018Inventors: Arthur Vorwerk RADUN, Adrian SHIPLEY
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Patent number: 9746512Abstract: A system for detecting the location of arc faults in an aircraft electrical wiring arrangement is provided. The system comprises a controller, operable to generate a test signal and a directional coupler for coupling the test signal into electrical wiring and for coupling reflected test signals from the electrical wiring to the controller. The electrical wiring comprises one or more wire under test and the controller is further operable to detect test signals reflected from arc faults in the wire under test and to analyze reflected test signals in order to determine one or more arc fault position therefrom. The wire under test may be live and testing can be performed without the need to use invasive in-line components.Type: GrantFiled: September 14, 2009Date of Patent: August 29, 2017Assignee: GE AVIATION SYSTEMS LIMITEDInventor: Adrian Shipley
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Publication number: 20160291073Abstract: A method for detecting electrical faults in an electrical circuit having transmission wires for power transmission includes determining whether a potential electrical fault condition exists along the transmission wires and confirming the potential electrical fault is an actual electrical fault. If the potential electrical fault is confirmed as an actual electrical fault, the method may disable the electrical circuit.Type: ApplicationFiled: November 22, 2013Publication date: October 6, 2016Inventors: Peter James HANDY, Adrian SHIPLEY
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Patent number: 9246482Abstract: The present invention relates generally to power switches for aircraft. According to a first aspect, the present invention provides an integrated solid state power switch for fault protection in an aircraft power distribution system. The integrated solid state power switch is formed of semiconductor material that provides a field effect transistor (FET) channel that is operable during normal device operation to provide an operating current flow path and a bipolar transistor channel that is operable during device overload conditions to provide an overload current flow path. A method for manufacturing such an integrated solid state power switch is also described. Various embodiments of the invention provide automatic overload current protection for aircraft systems without the need to use bulky switches or heavy cooling equipment.Type: GrantFiled: April 7, 2011Date of Patent: January 26, 2016Assignee: GE AVIATION SYSTEMS LIMITEDInventors: Adrian Shipley, Martin James Stevens, Phil Mawby, Angus Bryant
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Patent number: 9236744Abstract: A power distribution system which may be provided in an aircraft for example is described, the power distribution system comprising: a power distribution bus and a plurality of localized voltage converters each supplied by the power distribution bus. By providing a plurality of localized voltage converters, the power distribution system may use fewer, or just a single power distribution bus at a particular voltage and convert to the desired voltage at or near to each of a plurality of pieces of electrical equipment being supplied.Type: GrantFiled: September 27, 2011Date of Patent: January 12, 2016Assignee: GE AVIATION SYSTEMS LIMITEDInventors: Adrian Shipley, Stephen Curwen
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Patent number: 9118177Abstract: A power controller system configured to electrically supply a load via a circuit is provided. The system comprises, a switching device provided in an electrical pathway for supplying current to the load, a controller configured to open the switching device when a current through or voltage across the switching device exceeds a predetermined level; and an electrical pathway provided parallel to the load to enable load current to continue to flow through the parallel electrical pathway and the load when the switching device is open to dissipate inductive energy stored in the circuit connecting the parallel electrical pathway to the load.Type: GrantFiled: October 21, 2011Date of Patent: August 25, 2015Assignee: GE Aviation Systems, LLCInventor: Adrian Shipley
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Publication number: 20150123463Abstract: An electrical power system for an aircraft having electrical loads and at least one jet engine with a high pressure spool and a low pressure spool, the electrical power system includes a first electrical machine driven by a first pressure spool and outputting a first voltage, a second electrical machine driven by a second pressure spool and outputting a second voltage, and an electrical distribution bus receiving the first and second voltages and supplying the voltages to the loads.Type: ApplicationFiled: May 1, 2014Publication date: May 7, 2015Applicant: GE Aviation Systems LimitedInventors: Hao Huang, Adrian Shipley
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Patent number: 8842398Abstract: An apparatus and method for detecting an arc fault using a power conductor on a printed circuit board (PCB), which supplies power from an external power source to electrical components on the PCB by sensing a value indicative of the rate of change of current passing through the power conductor. The apparatus and method may be used for detecting arc faults both internal and external to the PCB.Type: GrantFiled: August 28, 2012Date of Patent: September 23, 2014Assignee: GE Aviation Systems LimitedInventors: Adrian Shipley, Peter James Handy
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Patent number: 8755160Abstract: An electrical power distribution system for an aircraft comprises a power source electrically connected to an electrical load and at least one circuit interruption device for interrupting current in the power distribution system. A distinguishing device is connected to the system for distinguishing a transient electrical event in the system from a steady-state level of electrical activity in the system, wherein the transient electrical event induces a potential difference across all or part of the distinguishing device. The circuit interruption device is operable to interrupt current flowing through the power distribution system if the potential difference across the distinguishing device exceeds a threshold voltage.Type: GrantFiled: May 23, 2011Date of Patent: June 17, 2014Assignee: GE Aviation Systems LimitedInventor: Adrian Shipley
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Publication number: 20130293989Abstract: An apparatus and method for detecting an arc fault using a power conductor on a printed circuit board (PCB), which supplies power from an external power source to electrical components on the PCB by sensing a value indicative of the rate of change of current passing through the power conductor. The apparatus and method may be used for detecting arc faults both internal and external to the PCB.Type: ApplicationFiled: August 28, 2012Publication date: November 7, 2013Applicant: GE AVIATION SYSTEMS LIMITEDInventors: Adrian Shipley, Peter James Handy
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Patent number: 8564389Abstract: In one aspect, the present invention provides an electromagnetic circuit interrupter for use in a high voltage direct current (DC) aircraft power distribution system. The electromagnetic circuit interrupter comprises a contact mechanism operable to separate first and second electrical contacts by a first predetermined distance d1 for a predetermined time ? so as to sustain an arc when the contact mechanism is opened. The contact mechanism is further operable to separate the first and second electrical contacts by a second predetermined distance d2 after the predetermined time ? so as to extinguish the arc. The first predetermined distance d1 is less than said second predetermined distance d2. By deliberately sustaining the arc for a relatively long period of time, this aspect of the present invention is particularly useful for extending the operational lifetime of the contacts and thereby of the electromagnetic circuit interrupter itself.Type: GrantFiled: May 4, 2011Date of Patent: October 22, 2013Assignee: GE Aviation Systems LimitedInventor: Adrian Shipley
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Publication number: 20130229050Abstract: A power distribution system for an aircraft is provided. The power distribution system comprises a first wiring harness connected to a power supply, at least one integrated switching power converter connected to the power supply through the first wiring harness, and at least one electrical load connected to a respective output of a respective integrated switching power converter through a second wiring harness.Type: ApplicationFiled: August 30, 2012Publication date: September 5, 2013Inventors: Adrian Shipley, Andrew Wyer
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Publication number: 20120175674Abstract: The present invention relates generally to power switches for aircraft. According to a first aspect, the present invention provides an integrated solid state power switch for fault protection in an aircraft power distribution system. The integrated solid state power switch is formed of semiconductor material that provides a field effect transistor (FET) channel that is operable during normal device operation to provide an operating current flow path and a bipolar transistor channel that is operable during device overload conditions to provide an overload current flow path. A method for manufacturing such an integrated solid state power switch is also described. Various embodiments of the invention provide automatic overload current protection for aircraft systems without the need to use bulky switches or heavy cooling equipment.Type: ApplicationFiled: April 7, 2011Publication date: July 12, 2012Inventors: Adrian Shipley, Martin James Stevens, Phil Mawby, Angus Bryant
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Publication number: 20120153928Abstract: A power controller system configured to electrically supply a load via a circuit is provided. The system comprises, a switching device provided in an electrical pathway for supplying current to the load, a controller configured to open the switching device when a current through or voltage across the switching device exceeds a predetermined level; and an electrical pathway provided parallel to the load to enable load current to continue to flow through the parallel electrical pathway and the load when the switching device is open to dissipate inductive energy stored in the circuit connecting the parallel electrical pathway to the load.Type: ApplicationFiled: October 21, 2011Publication date: June 21, 2012Inventor: Adrian SHIPLEY
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Publication number: 20120086266Abstract: A power distribution system which may be provided in an aircraft for example is described, the power distribution system comprising: a power distribution bus and a plurality of localised voltage converters each supplied by the power distribution bus. By providing a plurality of localised voltage converters, the power distribution system may use fewer, or just a single power distribution bus at a particular voltage and convert to the desired voltage at or near to each of a plurality of pieces of electrical equipment being supplied.Type: ApplicationFiled: September 27, 2011Publication date: April 12, 2012Inventors: Adrian SHIPLEY, Stephen Curwen
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Publication number: 20120068194Abstract: A method of manufacturing a semiconductor device, wherein the method comprises applying a first layer comprising silicon to a second layer comprising silicon carbide, wherein an interface is defined between the first and second layers; and oxidising sonic or all of the first layer.Type: ApplicationFiled: September 15, 2011Publication date: March 22, 2012Inventors: Adrian Shipley, Philip Mawby, Michael Jennings, James Covington