Patents Assigned to GE Aviation Systems Limited
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Patent number: 10571909Abstract: One example aspect of the present disclosure relates to a method. The method can include determining, by one or more autonomous distress tracking (ADT) devices installed in a designated fire zone, a state of the vehicle. When the state of the vehicle is the normal state, the method can include transmitting first data via a first transmitter at a first interval, wherein the first transmitter is configured to transmit messages over a frequency band used for normal communications. When the state of the vehicle is the possible distress state, the method can include transmitting second data via the first transmitter at a second interval. When the state of the vehicle is the distress state, the method can include transmitting third data continuously via a second transmitter, wherein the second transmitter is configured to transmit messages over a frequency band reserved for emergency communications.Type: GrantFiled: May 14, 2018Date of Patent: February 25, 2020Assignee: GE Aviation Systems LimitedInventor: Stefan Alexander Schwindt
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Patent number: 10569895Abstract: Systems, methods, and devices for aircraft power distribution include a bipolar high voltage direct current source component; an electrical loading component capable of drawing electrical power from the bipolar high voltage direct current source component; a set of switching components configured to selectively couple power from the bipolar high voltage DC source component to the electrical loading and a ground fault interruption component coupled to the set of switching components. The ground fault interruption component is configured to detect a ground fault based on a sensed difference between a current flowing out of the set of switching components and back from the electrical loading component.Type: GrantFiled: July 29, 2016Date of Patent: February 25, 2020Assignee: GE Aviation Systems LimitedInventor: Peter James Handy
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Patent number: 10569904Abstract: In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.Type: GrantFiled: November 7, 2017Date of Patent: February 25, 2020Assignee: GE Aviation Systems LimitedInventors: Colin John Halsey, Michael David Bailey
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Patent number: 10560087Abstract: A passive leakage management circuit for a switch leakage current including a switch having operable in a first operating mode, wherein the switch output supplies an output current having a first predetermined voltage, and a second operating mode, wherein the switch output supplies a leakage current having a second voltage, a first current path, and a leakage current path.Type: GrantFiled: June 29, 2015Date of Patent: February 11, 2020Assignee: GE Aviation Systems LimitedInventors: Peter James Handy, Nicholas George Tembe
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Publication number: 20200042016Abstract: A system and method for operating a wildlife intercept system, including receiving an indication of a presence of an intrusion in a predetermined area, determining a location of the intrusion in the predetermined area, and directing the intrusion away from the predetermined area by at least a subset of vehicles.Type: ApplicationFiled: August 1, 2019Publication date: February 6, 2020Applicant: GE Aviation Systems LimitedInventor: Stefan Alexander Schwindt
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Patent number: 10547183Abstract: A high voltage battery pack includes a set of battery bricks, wherein the battery bricks each have a positive and a negative terminal. Each battery brick is connected in series or in parallel to an adjacent battery brick to generate a total voltage of the battery pack. A battery pack lower assembly holds the battery bricks. A battery pack upper assembly includes a battery pack upper housing and a circuit board connected to the battery pack upper housing, the circuit board having brick connectors attached thereto. The brick connectors are positioned to come into physical contact with the positive and negative terminals of the battery bricks to generate the total voltage of the battery pack, and the battery pack upper housing defines a physical separation distance between the brick connectors and an exterior of the battery pack upper housing.Type: GrantFiled: May 24, 2018Date of Patent: January 28, 2020Assignee: GE Aviation Systems LimitedInventor: Colin John Halsey
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Patent number: 10531587Abstract: A method and apparatus for modular power distribution includes an end module and at least one switching module having a switching module electrical power interface configured to electrically connect to at least one of the end module electrical power interface, to another switching module electrical power interface, or to at least one voltage converter module, and having at least one of a switching element, an input/output connector, a switching module communication interface, or a bus bar connector, wherein the modules are physically secured.Type: GrantFiled: March 1, 2017Date of Patent: January 7, 2020Assignee: GE Aviation Systems LimitedInventors: Russell Mark Compton, John Oliver Collins
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Patent number: 10514214Abstract: A heat transfer assembly for transferring heat from a heat generating electrical element and having a porous element having a portion configured to contact the heat generating element and a moveable diaphragm having a portion adjacent the porous element and where the diaphragm is moveable between an extended position towards the porous element and a retracted position away from the porous element.Type: GrantFiled: September 10, 2014Date of Patent: December 24, 2019Assignee: GE AVIATION SYSTEMS LIMITEDInventor: Graham John Baldwin
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Publication number: 20190372975Abstract: Systems and methods for authenticating data transmissions are provided, such as e.g., analog radio streams received at a vehicle. In one aspect, the vehicle includes features that allow for detection and decryption of an encrypted source identifier embedded or introduced into a data transmission transmitted to the vehicle. The source identifier may be used to determine whether the source is authorized to transmit data transmissions to the vehicle and the data transmission may be authenticated accordingly. In another aspect, the vehicle includes features that determine the location of the transmitting device used to transmit the data transmission to the vehicle. The location is then used to determine whether the data transmission should be authenticated.Type: ApplicationFiled: May 31, 2019Publication date: December 5, 2019Applicant: GE Aviation Systems LimitedInventor: Stefan Alexander Schwindt
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Publication number: 20190371341Abstract: Systems and methods for control of vehicles are provided. A computer-implemented method in example embodiments may include receiving, at a computing system comprising one or more processors positioned in a vehicle, voice data from one or more audio sensors positioned in the vehicle. The system can determine whether configuration of a reference voiceprint for a speech processing system of the vehicle is authorized based at least in part on performance data associated with the vehicle. In response to determining that configuration of the reference voiceprint is authorized, a first reference voiceprint based on the reference voice data can be stored and the speech processing system configured to authenticate input voice data for a first set of voice commands based on the reference voiceprint.Type: ApplicationFiled: May 31, 2019Publication date: December 5, 2019Applicant: GE Aviation Systems LimitedInventors: Stefan Alexander Schwindt, Barry Foye
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Patent number: 10498130Abstract: Method(s) for limiting current in an electrical circuit having transmission wires for power transmission include determining whether an unexpected operating condition exists along the transmission wires and limiting the current to prevent (damage caused by) the unexpected operating condition. The method may further include disabling the electrical circuit if the unexpected operating condition persists. Additionally, a system includes a power source, a solid state power controller (SSPC) configured to operate in a first conducting state and a second non-conducing state, and a controller.Type: GrantFiled: August 17, 2016Date of Patent: December 3, 2019Assignee: GE Aviation Systems LimitedInventors: Peter James Handy, Julian Peter Mayes, David Alan Elliott
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Patent number: 10494119Abstract: A power distribution connector is provided, which includes an electrically conductive bus bar configured to conduct electricity between a power-supplying node and an opposing power-consuming node, and has a set of surfaces between the opposing nodes and a thermally conductive polymer having a first surface abutting at least a portion of a subset of the bus bar surfaces and a second surface spaced from the first surface.Type: GrantFiled: December 14, 2016Date of Patent: December 3, 2019Assignee: GE Aviation Systems LimitedInventor: Michael James Smith
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Patent number: 10486795Abstract: A propeller blade for rotation about a hub assembly is provided, wherein the propeller blade defines a radial direction along its length from a blade root to a blade tip, the propeller blade including a radially inner region, a radially outer region located between the blade root and the blade tip at a position where rotational forces on the blade are sufficient, in use, to remove ice from an uncoated blade, a coating disposed at least along a leading edge of the propeller blade, the coating including an icephobic material, wherein the coating extends along the propeller blade from the radially inner region to the radially outer region. The coating overlays a substrate portion of the propeller blade defining a color visually indicative of wear of the coating.Type: GrantFiled: January 9, 2017Date of Patent: November 26, 2019Assignee: GE Aviation Systems LimitedInventor: Paul Nicholas Methven
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Patent number: 10422826Abstract: The present embodiments are directed to locating electrical faults in an electrical circuit, in particular electrical faults in transmission wires of an electrical circuit. Examples of the present embodiments provide a method and apparatus for opening a switch in the electrical circuit to cause an open circuit or discontinuity at the fault; transmitting a signal to be reflected from the open circuit or discontinuity and receiving the signal reflected from the open circuit or discontinuity to determine the location of the fault. Examples are particularly suitable for high voltage systems, for example over 100V.Type: GrantFiled: September 1, 2015Date of Patent: September 24, 2019Assignee: GE Aviation Systems LimitedInventor: Peter James Handy
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Patent number: 10417921Abstract: According to an example, coordinates in a coordinate space of a display device at which a line is to be displayed may be determined. A first set of intensity profile discs corresponding to the determined coordinates and a second set of intensity profile discs having inverted intensity profiles from the first set of intensity profile discs may be identified. The identified second set of intensity profile discs may be displayed at the determined coordinates on the display device and the identified first set of intensity profile discs may be displayed over the displayed second set of intensity profile discs on the display device.Type: GrantFiled: July 19, 2017Date of Patent: September 17, 2019Assignee: GE Aviation Systems LimitedInventors: Stephen Christopher Cox, Roger Lee, Trevor Marc Yates
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Patent number: 10396565Abstract: A system for aircraft power distribution (100) includes a source of energy (112) to deliver an input power; a bus contactor (122); a set of switches (130) connected between the bus contactor and a set of essential and non-essential devices (132); a current analysis component (315) to determine a power level drawn from the source of current by the set of essential and non-essential devices (132); a variation reduction component (317) to determine an energization schedule of the set of essential and non-essential devices (132) based on reducing temporal variation in the input power drawn from the source of energy (112) to the bus contactor (122); and a switch control component (319) configured to adjust the set of switches (130) according to the energization schedule. If too much power is drawn, the set of switches (130) will be configured such as not to exceed the maximum power rating of the source (112).Type: GrantFiled: May 6, 2015Date of Patent: August 27, 2019Assignee: GE Aviation Systems LimitedInventors: Michael David Bailey, Colin John Halsey, Ross Jonathan Williams
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Patent number: 10384763Abstract: A pitch control assembly for adjusting the pitch of a propeller blade, including a pitch control unit comprising a housing, with a plurality of control valves and corresponding hydraulic lines located within the housing, a blade angle unit, a transfer bearing mounted to the housing and having a plurality of hydraulic lines fluidly coupled to the hydraulic lines of the pitch control unit, a transfer tube axially receiving and axially moveable relative to at least a portion of the transfer bearing, a magnetic core sleeve carried by the transfer tube and located within the blade angle unit.Type: GrantFiled: October 7, 2013Date of Patent: August 20, 2019Assignee: GE AVIATION SYSTEMS LIMITEDInventor: Christopher Roy Carrington
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Patent number: 10370091Abstract: An aircraft assembly (10) having an indicator (20) configured to provide an indication of when an element of the aircraft assembly has received a predetermined load or traveled to a predetermined position.Type: GrantFiled: November 9, 2015Date of Patent: August 6, 2019Assignee: GE AVIATION SYSTEMS LIMITEDInventors: Stuart John Lacy, Indrakaji Gurung
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Patent number: 10362702Abstract: An avionics power management panel and door assembly where the panel includes a cabinet including a set of walls at least partially defining an interior with an open face and door assembly includes a central panel a front panel that includes a set of rows with apertures formed between two adjacent rows and where the set of rows have a crimped profile.Type: GrantFiled: January 23, 2018Date of Patent: July 23, 2019Assignee: GE AVIATION SYSTEMS LIMITEDInventors: John Michael Brett, Adrian John Hughes
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Publication number: 20190208485Abstract: Systems and methods for providing time reference synchronization for an aircraft are provided. In one embodiment, a method can include receiving, by one or more computing devices associated with a data acquisition system of an aircraft, a signal comprising time synchronization information, wherein the signal comprises a first signal portion and a second signal portion. The method can include filtering, by the one or more computing devices, the signal comprising the time synchronization information to distinguish the first signal portion and the second signal portion from noise associated with the signal. The method can include determining, by the one or more computing devices, the time synchronization information based at least in part on the first signal portion and the second signal portion. The method can include synchronizing, by the one or more computing devices, a set of data acquired by the data acquisition system with the time synchronization information.Type: ApplicationFiled: May 25, 2017Publication date: July 4, 2019Applicant: GE Aviation Systems LimitedInventors: Timothy Robert NORTH, Tod Alexander GILBERT, Steven BONNETT