Patent application number | Description | Published |
20110204725 | ELECTROMAGNETIC CIRCUIT INTERRUPTER - 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 d | 08-25-2011 |
20110292555 | MEASURING TRANSIENT ELECTRICAL ACTIVITY IN AIRCRAFT POWER DISTRIBUTION SYSTEMS - 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. | 12-01-2011 |
20120068194 | SILICON CARBIDE SEMICONDUCTOR DEVICES - 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. | 03-22-2012 |
20120086266 | POWER DISTRIBUTION SYSTEM - 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. | 04-12-2012 |
20120153928 | POWER CONTROLLER SYSTEM - 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. | 06-21-2012 |
20120175674 | POWER SWITCHES FOR AIRCRAFT - 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. | 07-12-2012 |
20130099560 | MULTIPLE SOURCE ELECTRICAL POWER DISTRIBUTION IN AIRCRAFT - Disclosed herein is a method of providing electrical power to an aircraft. The method comprises selectively sourcing power from a plurality of power sources. The power sources comprise one or more generators driven by an engine, and at least one other power source comprising one or more batteries, one or more fuel cells and/or one or more thermo-electric power sources. | 04-25-2013 |
20130229050 | POWER DISTRIBUTION IN AIRCRAFT - 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. | 09-05-2013 |
20130293989 | APPARATUS AND METHOD FOR ARC FAULT DETECTION - 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. | 11-07-2013 |
20150123463 | ELECTRICAL POWER SYSTEM FOR AN AIRCRAFT - 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. | 05-07-2015 |