WO2002061905A2 - Aircraft applicable ground fault circuit interrupter - Google Patents
Aircraft applicable ground fault circuit interrupter Download PDFInfo
- Publication number
- WO2002061905A2 WO2002061905A2 PCT/US2002/002893 US0202893W WO02061905A2 WO 2002061905 A2 WO2002061905 A2 WO 2002061905A2 US 0202893 W US0202893 W US 0202893W WO 02061905 A2 WO02061905 A2 WO 02061905A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- circuit
- power
- sensor
- signal
- logic controller
- Prior art date
Links
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
- H02H3/26—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents
- H02H3/32—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at corresponding points in different conductors of a single system, e.g. of currents in go and return conductors
- H02H3/34—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at corresponding points in different conductors of a single system, e.g. of currents in go and return conductors of a three-phase system
- H02H3/347—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to difference between voltages or between currents; responsive to phase angle between voltages or between currents involving comparison of the voltage or current values at corresponding points in different conductors of a single system, e.g. of currents in go and return conductors of a three-phase system using summation current transformers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H1/00—Details of emergency protective circuit arrangements
- H02H1/0007—Details of emergency protective circuit arrangements concerning the detecting means
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H1/00—Details of emergency protective circuit arrangements
- H02H1/06—Arrangements for supplying operative power
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
- H02H3/02—Details
- H02H3/04—Details with warning or supervision in addition to disconnection, e.g. for indicating that protective apparatus has functioned
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
- H02H3/08—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current
- H02H3/10—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current additionally responsive to some other abnormal electrical conditions
- H02H3/105—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current additionally responsive to some other abnormal electrical conditions responsive to excess current and fault current to earth
Definitions
- This invention relates generally to electrical control systems, and more specifically to an aircraft electrical control system which disconnects power to a load when a current imbalance is sensed.
- the present invention is directed towards a ground fault circuit interrupter particularly attractive for use in aircraft for interrupting a circuit having a line side and a load side.
- the ground fault circuit interrupter can be retrofit to existing aircraft, or can be utilized in newly constructed aircraft and new aircraft designs.
- the aircraft applicable ground fault circuit interrupter includes a power supply, a circuit to be monitored, a sensor, a logic controller, and a power controller.
- the power supply is configured to provide power to the sensor and logic controller.
- a second power supply may optionally be provided to power the power controller.
- the sensor is configured to sense a current imbalance in the line side of the circuit to be monitored.
- the logic controller is configured to process input from the sensor.
- the logic controller compares the sensor signal with a range of sensor signals representing acceptable operation and outputs a signal representing a circuit current imbalance when the sensor signal is outside the acceptable range of signals.
- the power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed. In a presently preferred embodiment, the power removal from the load side of the circuit due to a sensed current imbalance is maintained until the power source is cycled.
- the present invention also provides for a method for interrupting an electrical circuit for an electrical load, the electrical circuit having a line side and a load side with a ground fault.
- the method comprises providing a supply of power, continually monitoring the circuit for a current imbalance, sensing a current imbalance in the line side of the circuit, processing input from a power supply and a sensor, receiving input from a logic controller, and interrupting the circuit when a current imbalance is sensed.
- interrupting of the circuit when a current imbalance is sensed is maintained until the power source is cycled.
- the load being supplied by the current is a motor.
- no additional signals, inputs, or sources of power are required.
- the load side of the circuit is connected to a fuel pump, and arcing is suppressed within the fuel pump.
- FIGURE 1 illustrates a block diagram of a first embodiment of a control system of the present invention adapted for a Boeing 757 aircraft, for interrupting the circuit when a current imbalance is sensed;
- FIG. 2 illustrates a detailed view of the power supply portion of the control system shown in FIG. 1 ;
- FIG. 3 illustrates a detailed view of the logic controller portion of the control system shown in FIG. 1;
- FIG. 4 illustrates a detailed view of a sensor for the control system of
- FIG. 5 illustrates a block diagram of a second embodiment of a control system of the present invention adapted for a Boeing 747 aircraft, for interrupting the circuit when a current imbalance is sensed;
- FIG. 6 illustrates a detailed view of the power supply portion of the control system shown in FIG. 5;
- FIG. 7 illustrates a detailed view of the logic controller portion of the control system shown in FIG. 5;
- FIG. 8 illustrates a detailed view of a sensor for the control system of Fig. 5;
- FIG. 9 illustrates a block diagram of an alternate preferred embodiment of a control system of the present invention adapted for providing the speed of a DC relay in an AC application for interrupting the circuit when a current imbalance is sensed;
- FIG. 10 illustrates a detailed view of a preferred embodiment of one section of the power supply portion of the control system shown in FIG. 9;
- FIG. 11 illustrates a detailed view of a second section of the power supply portion of the control system shown in FIG. 9
- FIG. 12 illustrates a detailed view of the preferred logic controller portion of the control system shown in FIG. 9.
- FIG. 13 illustrates a detailed view of a sensor for the control system of Fig. 9.
- FIG. 1 illustrates a preferred embodiment of a control system 10, adapted for a Boeing 757 aircraft
- FIG. 5 illustrates a preferred embodiment of a control system 10, adapted for a Boeing 747 aircraft, each being constructed in accordance with the present invention for disconnecting power to a load when a current imbalance is sensed.
- the aircraft applicable ground fault circuit interrupter 10 of the invention interrupts a circuit 20 having a line side 24 and a load side 26 with a ground fault.
- the load may be a motor, or any electrical device drawing a load, where protection of equipment or personnel is desired.
- the ground fault circuit interrupter of the invention includes a power supply 30, a sensor 40, a logic controller 50, and a power controller 60.
- the power supply is configured to provide power to the logic controller, and the sensor is configured to sense a current imbalance in the line side 24 of the circuit 20, and to output a sensor signal to the logic controller.
- the logic controller is configured to receive and process the sensor signal input from the sensor, and the power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed.
- FIGS. 2 and 6 illustrate a detailed view of a preferred embodiment of the power supply
- FIGS. 3 and 7 illustrate a detailed view of a preferred embodiment of the logic controller.
- the sensor preferably includes the IC U7, which is an Amploc Pro 5 Hall effect linear sensor with an output of 233 mV/A when operated at 10V. All three pump power-phase wires pass through the sensor core. Kirchhcoff s current law states that the net current in a node is 0.
- the net current in the phase windings when algebraically summed, is 0. If a ground fault exists, that is where the current is supplied through the sensor but does not return through the sensor, the algebraic sum of the currents in the phase wires would be equal to the ground fault current. For example, a fourth wire could be added to the wye connection point, and returned to the power source, but not pass through the sensor. The net current in all four wires would still be 0, but the imbalance current that passed through the sensor, by way of the three phase wires, would be equal to the current in the fourth wire.
- the output of the sensor is approximately one-half of the supply voltage, for no measured imbalance.
- Amplifier U3A amplifies the signal by a factor of 10. The gain is set by the ratio of resistors R5 and R3. The 3 db point is where the reactance of capacitor C4 is equal to the resistance of R5. This occurs at 3386 Hz.
- Resistors Rl, R2, and R4 bias the amplifier and have been selected so that a maximum value of 1 meg, for resistor R4, is required to adjust the amplifier output to mid supply with the sensor at its specified worse case high output. Calibration for the worse case low output of the sensor is easily achieved.
- Amplifiers U3B and U3C, and resistors R6, R7, and R8 are set to detect a current imbalance greater than about 1.5 A.
- a high output from amplifier U3B or U3C indicates an imbalance is present in excess of the 1.5A threshold.
- IC U4A "OR's" the outputs from amplifiers U3B and U3C.
- a logic 0 at its output indicates one or the other failure condition is present. Simultaneous imbalance inputs can be handled but are physically not possible since a positive imbalance cannot exist at the same time as a negative imbalance. If a fault condition exists, it passes through IC U5A presenting a logic 1 to the latch comprised of ICs U4B and U4C.
- a logic 1 at pin 5 forces the output pin 4 low, turning transistor QI off, which removes the drive signal to the power control stage.
- Pin 9 the other input to the latch, is normally at logic 0. This will cause pin 10 to go high, setting the latch by presenting a logic 1 to pin 6.
- the powerup sequence initializes the power control section to the non-operate mode. This is accomplished by presenting a logic 0 to pin 2 of IC U5A to mimic a current imbalance condition.
- the powerup reset pulse created by IC U5B, resistor R13, capacitor C5 and diode CR8 is typically 7 msec. The reset is determined by the time it takes to charge capacitor C5 through resistor R13 to the threshold set by IC U5B. Diode CR8 provides a quick reset.
- Diodes CR1, CR2, CR3, CR4, CR5, and CR6 form a full-wave three- phase bridge.
- Capacitor Cl acts as the storage device for the 281V peak voltage produced by the bridge.
- the regulator is a preferably buck-type configuration with the abnormal architecture of having the inductor in the lower side. This is acceptable because the circuit does not have to be referenced to earth ground. In fact, the on-board electrical ground is approximately 270 V above earth ground.
- the switcher operates in an non-conventional mode. If it senses that output voltage is low, it turns on and remains on until the current through inductor LI reaches a pre-determined amount. Otherwise, the cycle is skipped. Energy is stored in inductor LI and transferred to output capacitor C3 through diode CR7. Proper regulation is determined by Zener VR1 and opto- coupler U2. Capacitor C2 serves to store a small amount of energy that the regulator uses to operate its internal circuitry.
- FIGS. 9-13 illustrating an alternate preferred embodiment of a control system of the present invention adapted for an AC-DC application, to interrupt the circuit when a current imbalance is sensed.
- the aircraft applicable ground fault circuit interrupter 10 of the invention interrupts a circuit 20 having a line side 24 and a load side 26 with a ground fault.
- the load may be a motor, or any electrical device drawing a load, where protection of equipment or personnel is desired.
- the ground fault circuit interrupter of the invention includes a power supply 30, a sensor 40, a logic controller 50, and a power controller 60.
- the power supply is configured to provide power to the logic controller, and the sensor is configured to sense a current imbalance in the line side 24 of the circuit 20, and to output a sensor signal to the logic controller.
- the logic controller is configured to receive and process the sensor signal input from the sensor, and the power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed.
- FIGS. 10 and 11 illustrate a detailed view of a preferred embodiment of the power supply.
- FIG. 12 illustrates a detailed view of a preferred embodiment of the logic controller.
- the sensor preferably includes the IC U7, which is an Amploc Pro 5 Hall effect linear sensor with an output of 233 mV/A when operated at 10V. All three pump power-phase wires pass through the sensor core. Kirchhcoff s current law states that the net current in a node is 0. Considering the wye connection point of the pump winding and looking back to the inputs of the phase windings, the net current in the phase windings, when algebraically summed, is 0.
- a ground fault that is where the current is supplied through the sensor but does not return through the sensor
- the algebraic sum of the currents in the phase wires would be equal to the ground fault current.
- a fourth wire could be added to the wye connection point, and returned to the power source, but not pass through the sensor. The net current in all four wires would still be 0, but the imbalance current that passed through the sensor, by way of the three phase wires, would be equal to the current in the fourth wire.
- the output of the sensor is approximately one-half of the supply voltage, for no measured imbalance.
- Amplifier U3 A amplifies the signal by a factor of 10. The gain is set by the ratio of resistors R5 and R3. The 3db point is where the reactance of capacitor C4 is equal to the resistance of R5. This occurs at 3386 Hz.
- Resistors Rl, R2, and R4 bias the amplifier and have been selected so that a maximum value of 1 meg, for resistor R4, is required to adjust the amplifier output to mid supply with the sensor at its specified worse case high output. Calibration for the worse case low output of the sensor is easily achieved.
- Amplifiers U3B and U3C, and resistors R6, R7, and R8 are set to detect a current imbalance greater than about 1.5A.
- a high output from amplifier U3B or U3C indicates an imbalance is present in excess of the 1.5A threshold.
- IC U4A "OR's" the outputs from amplifiers U3B and U3C.
- a logic 0 at its output indicates one or the other failure condition is present. Simultaneous imbalance inputs can be handled but are physically not possible since a positive imbalance cannot exist at the same time as a negative imbalance.
- IC U5 A presenting a logic 1 to the latch comprised of ICs U4B and U4C.
- a logic 1 at pin 5, forces the output pin 4 low, turning transistor QI off, which removes the drive signal to the power control stage.
- Pin 9 the other input to the latch, is normally at logic 0. This will cause pin 10 to go high, setting the latch by presenting a logic 1 to pin 6.
- the powerup sequence initializes the power control section to the non-operate mode. This is accomplished by presenting a logic 0 to pin 2 of IC U5A to mimic a current imbalance condition.
- the powerup reset pulse created by IC U5B, resistor R13, capacitor C5 and diode CR8 is typically 7 msec. The reset is determined by the time it takes to charge capacitor C5 through resistor R13 to the threshold set by IC U5B. Diode CR8 provides a quick reset.
- Diodes CR1, CR2, CR3, CR4, CR5, and CR6 form a full-wave three- phase bridge.
- Capacitor Cl acts as the storage device for the 281V peak voltage produced by the bridge.
- the regulators are a buck-type configuration with the abnormal architecture of having the inductor in the lower side. This is acceptable because the circuit does not have to be referenced to earth ground. In fact, the onboard electrical ground is approximately 270V and 260V above earth ground for the 10 V and 20V supplies respectively.
- the switcher operates in an non-conventional mode. If it is sensed that an output voltage is low, the corresponding controller turns on and remains on until the current through inductor LI or LI A reaches a pre-determined amount. Otherwise, the cycle is skipped. Energy is stored in inductor LI or LI A and transferred to output capacitor C3 or C3 A through diode CR7 or CR7A. Proper regulation is determined by Zener VR1 or VR1 A and opto-coupler U2 or U2A. Capacitor C2 or C2A serves to store a small amount of energy that each respective regulator uses to operate its internal circuitry.
- the present invention provides a method and apparatus for suppressing arcs in electrical equipment in aircraft which may be adapted to a variety of systems and components. As such, it provides more reliable and rapid disconnect of power than previous systems, thus reducing damage from ground faults in the circuits. While a particular form of the invention has been illustrated and described it will also be apparent that various modifications can be made without departing from the spirit and scope of the invention. Accordingly, it is not intended that the invention be limited except as by the appended claims.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002561338A JP2004519185A (en) | 2001-02-01 | 2002-01-30 | Ground fault circuit breaker applicable to aircraft |
EP02706101A EP1364437A2 (en) | 2001-02-01 | 2002-01-30 | Aircraft applicable ground fault circuit interrupter |
BR0206879-6A BR0206879A (en) | 2001-02-01 | 2002-01-30 | Aircraft Ground Fault Circuit Breaker Applicable |
CA2437377A CA2437377C (en) | 2001-02-01 | 2002-01-30 | Aircraft applicable ground fault circuit interrupter |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/775,337 US6583975B2 (en) | 2001-02-01 | 2001-02-01 | Aircraft applicable ground fault circuit interrupter |
US09/775,337 | 2001-02-01 |
Publications (3)
Publication Number | Publication Date |
---|---|
WO2002061905A2 true WO2002061905A2 (en) | 2002-08-08 |
WO2002061905A3 WO2002061905A3 (en) | 2003-03-13 |
WO2002061905A9 WO2002061905A9 (en) | 2004-04-01 |
Family
ID=25104087
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2002/002893 WO2002061905A2 (en) | 2001-02-01 | 2002-01-30 | Aircraft applicable ground fault circuit interrupter |
Country Status (7)
Country | Link |
---|---|
US (9) | US6583975B2 (en) |
EP (1) | EP1364437A2 (en) |
JP (1) | JP2004519185A (en) |
CN (1) | CN1323475C (en) |
BR (1) | BR0206879A (en) |
CA (1) | CA2437377C (en) |
WO (1) | WO2002061905A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8981265B2 (en) | 2008-12-30 | 2015-03-17 | Ppg Industries Ohio, Inc. | Electric circuit and sensor for detecting arcing and a transparency having the circuit and sensor |
Families Citing this family (53)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7362551B2 (en) * | 2001-02-01 | 2008-04-22 | Hydro-Aire, Inc. | Aircraft applicable circuit imbalance detection and circuit interrupter and packaging thereof |
US7016171B2 (en) * | 2001-02-01 | 2006-03-21 | Hydro-Aire, Inc. | Current fault detector and circuit interrupter and packaging thereof |
US6583975B2 (en) * | 2001-02-01 | 2003-06-24 | Hydro-Aire, Inc. | Aircraft applicable ground fault circuit interrupter |
US6879224B2 (en) * | 2002-09-12 | 2005-04-12 | Agilent Technologies, Inc. | Integrated filter and impedance matching network |
US6924613B2 (en) * | 2002-09-23 | 2005-08-02 | Siemens Energy & Automation, Inc. | System and method for monitoring current and providing motor protection |
KR100400068B1 (en) * | 2003-02-21 | 2003-09-29 | Bong Taek Kim | Performance test equipment system of train driving device and test method thereof |
US7646275B2 (en) | 2003-06-06 | 2010-01-12 | Xantrex Technology, Inc. | Device and method for eliminating transformer excitation losses |
US7254004B2 (en) * | 2003-06-13 | 2007-08-07 | Tdg Aerospace, Inc. | Systems and methods for fault-based power signal interruption |
US7342763B2 (en) * | 2003-06-13 | 2008-03-11 | Tdg Aerospace, Inc. | Fuel system safety device for run-dry conditions |
US7352550B2 (en) * | 2003-06-13 | 2008-04-01 | Tdg Aerospace, Inc. | Method of detecting run-dry conditions in fuel systems |
US7215519B2 (en) * | 2003-10-20 | 2007-05-08 | The Boeing Company | Ground and line fault interrupt controller/adapter |
GB0417473D0 (en) * | 2004-08-05 | 2004-09-08 | Airbus Uk Ltd | Fuel tank |
GB0417472D0 (en) * | 2004-08-05 | 2004-09-08 | Airbus Uk Ltd | Fuel tank system |
GB2463689B (en) * | 2008-09-22 | 2010-11-24 | Ge Aviat Systems Ltd | Arc fault location detection for aircraft wiring |
US20100091419A1 (en) * | 2008-10-15 | 2010-04-15 | Vedula Sastry V | Motor drive ground fault detection |
US8023236B2 (en) * | 2009-03-18 | 2011-09-20 | Hamilton Sundstrand Corporation | Precision ground fault detection for aircraft human body protection |
US8395391B2 (en) * | 2009-08-19 | 2013-03-12 | Astronics Advanced Electronic Systems Corp. | Method and apparatus for locating a parallel arc fault |
US8325504B2 (en) * | 2009-09-18 | 2012-12-04 | Power Distribution, Inc. | Direct current power supply for mission critical applications |
US8749928B2 (en) * | 2009-12-23 | 2014-06-10 | Goodrich Corporation | Aircraft electrical appliance |
US8564916B2 (en) * | 2010-02-16 | 2013-10-22 | Western Gas And Electric Company | Photovoltaic array ground fault detection method for utility-scale grounded solar electric power generating systems |
US8618456B2 (en) * | 2010-02-16 | 2013-12-31 | Western Gas And Electric Company | Inverter for a three-phase AC photovoltaic system |
JP4805396B2 (en) * | 2010-03-31 | 2011-11-02 | ファナック株式会社 | Motor drive device |
US9482698B2 (en) * | 2010-10-07 | 2016-11-01 | Raritan Americas, Inc. | Methods and apparatus for resistive voltage sensing in an isolated power distribution unit |
US20140049261A1 (en) * | 2011-04-28 | 2014-02-20 | Aerovironment, Inc. | Pulsed missing ground detector circuit |
KR101298779B1 (en) * | 2011-06-10 | 2013-08-22 | 한국항공우주산업 주식회사 | Integrated test system for supporting multiple forms of aircraft and mehtod for controlling that system |
CN102508437B (en) * | 2011-09-14 | 2014-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Multifunctional electromechanical system simulation method for simulation of airplane power supply control management system |
SG189579A1 (en) * | 2011-10-21 | 2013-05-31 | Schneider Electric South East Asia Hq Pte Ltd | Method and relay for communicating a value of a parameter of a source to be monitored |
US8775052B2 (en) * | 2011-12-15 | 2014-07-08 | GM Global Technology Operations LLC | Sensors bias detection for electronic returnless fuel system |
US9660435B2 (en) * | 2011-12-21 | 2017-05-23 | Sikorsky Aircraft Corporation | Multi-directional electrical power protection system |
US8552887B2 (en) | 2012-01-25 | 2013-10-08 | Garmin International, Inc. | Determining an electrical short in an aviation communication apparatus |
US8692398B2 (en) | 2012-03-30 | 2014-04-08 | Thermo King Corporation | Mobile environment-controlled unit having a magnetic sensor for a high-voltage alternating current bus |
US20130272898A1 (en) * | 2012-04-17 | 2013-10-17 | Schlumberger Technology Corporation | Instrumenting High Reliability Electric Submersible Pumps |
GB2501762A (en) * | 2012-05-04 | 2013-11-06 | Andrew John Harker | An electric control module for a hydraulic coupler |
US9170293B2 (en) * | 2012-06-07 | 2015-10-27 | Cooper Technologies Company | Power line indicator accessory for fusible circuit protection device array |
US8988837B2 (en) | 2012-06-08 | 2015-03-24 | Hamilton Sundstrand Corporation | Power distribution system incorporating ground fault interrupt protection |
FR2992486B1 (en) * | 2012-06-21 | 2015-07-17 | Sagem Defense Securite | ELECTRICAL CUTTING CIRCUIT OF AN ELECTRIC POWER SUPPLY WITH TRANSISTORS AND FUSES WITH REDUNDATED LOGIC |
CN102903582A (en) * | 2012-08-21 | 2013-01-30 | 江苏云意电气股份有限公司 | Controller device of intelligent residual current circuit breaker |
US9897656B2 (en) | 2013-05-16 | 2018-02-20 | Carrier Corporation | Method for sensing welded contacts on a switching device |
CN104345243A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Electrical performance check tester for fuel system |
BE1022018B1 (en) * | 2013-08-14 | 2016-02-04 | Cockerill Maintenance & Ingenierie S.A. | DEVICE FOR SWITCHING AND REMOTELY PROTECTING ELECTRICAL SYSTEMS. |
CN104300526A (en) * | 2014-09-17 | 2015-01-21 | 安徽天健环保车辆部件有限公司 | Connection protector of special vehicle power source |
CN105811377B (en) * | 2014-12-31 | 2018-12-07 | 上海良信电器股份有限公司 | The built-in protective module control circuit of breaker more changer controller |
DE102015200008A1 (en) * | 2015-01-02 | 2016-07-07 | Airbus Operations Gmbh | Offset residual current device |
CN104820751B (en) * | 2015-05-11 | 2017-11-14 | 中国民航大学 | Aircraft electrical power system small disturbed stability analysis method based on generalized state space average |
US10001519B2 (en) * | 2015-06-12 | 2018-06-19 | Allegro Microsystems, Llc | Ground reference fault detection in circuits with multiple ground references |
CN105571710A (en) * | 2015-12-11 | 2016-05-11 | 中国航空工业集团公司西安航空计算技术研究所 | Acquisition circuit of airborne vibration signals of engine |
US10177757B2 (en) | 2016-12-07 | 2019-01-08 | Hamilton Sundstrand Corporation-Pcss | Single event latchup mitigation with sample and hold |
US11131720B2 (en) * | 2017-05-11 | 2021-09-28 | Mitsubishi Electric Corporation | Electronic control device |
US10700603B2 (en) | 2017-12-13 | 2020-06-30 | Ovh | Circuit and system implementing a power supply configured for spark prevention |
EP3499669A1 (en) * | 2017-12-13 | 2019-06-19 | Ovh | Circuit and system implementing a smart fuse for a power supply |
US11133665B2 (en) * | 2018-08-29 | 2021-09-28 | Hamilton Sundstrand Corporation | Direct current over voltage monitoring and protection |
US11562872B2 (en) * | 2020-09-16 | 2023-01-24 | Abb Schweiz Ag | Circuit interrupter for detecting breaker fault conditions and interrupting an electric current |
CN114326367B (en) * | 2021-12-06 | 2024-04-02 | 中国商用飞机有限责任公司 | Circuit protection device management system for aircraft |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3512045A (en) * | 1968-06-28 | 1970-05-12 | Gen Signal Corp | Ground fault responsive apparatus for electric power distribution apparatus |
US4093977A (en) * | 1976-06-15 | 1978-06-06 | Westinghouse Electric Corp. | Ground fault protective device |
US4783713A (en) * | 1986-08-29 | 1988-11-08 | Cezhan Chen | Full automatic electric shock protector apparatus |
Family Cites Families (57)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6049A (en) * | 1849-01-23 | Improvement in seed-planters | ||
US36048A (en) * | 1862-07-29 | Improved apparatus for leaching tan-bark and obtaining extracts | ||
US22713A (en) * | 1859-01-25 | Richard dudgeon | ||
US3611038A (en) | 1969-09-08 | 1971-10-05 | Purex Corp Ltd | Ground fault and high current responsive circuit breaker utilizing amplified signals |
GB1386792A (en) | 1971-04-08 | 1975-03-12 | Rotax Ltd | Electrical heating apparatus for reducing or preventing the formation of ice on aircraft parts |
US4034267A (en) | 1975-12-12 | 1977-07-05 | Westinghouse Electric Corporation | Indicating apparatus |
US4115829A (en) | 1977-05-06 | 1978-09-19 | General Electric Company | Overcurrent and ground fault responsive trip unit for circuit breakers |
US4173774A (en) | 1977-12-08 | 1979-11-06 | Westinghouse Electric Corp. | Parallel AC electrical system with differential protection immune to high current through faults |
US4205358A (en) | 1978-10-26 | 1980-05-27 | General Electric Company | Ground fault protection system |
US4271444A (en) | 1979-07-31 | 1981-06-02 | General Electric Company | Ground fault trip mode network for static trip circuit breakers |
US4347540A (en) | 1981-04-27 | 1982-08-31 | Westinghouse Electric Corp. | Solid-state load protection system having ground fault sensing |
US4672501A (en) * | 1984-06-29 | 1987-06-09 | General Electric Company | Circuit breaker and protective relay unit |
US4688134A (en) | 1985-01-10 | 1987-08-18 | Slater Electric Inc. | Ground fault circuit interrupter and electronic detection circuit |
DE3504034A1 (en) | 1985-02-06 | 1986-08-07 | Siemens AG, 1000 Berlin und 8000 München | Circuit for energising the winding of a monostable relay |
US4685022A (en) | 1985-05-10 | 1987-08-04 | Square D Company | Ground fault circuit interrupter capable of deriving energy from ground fault current in order to achieve circuit interruption in the presence of a reduced supply voltage |
US4851950A (en) | 1987-06-09 | 1989-07-25 | Bassani Ticino, S.P.A. | Electrical apparatus for magnetothermal and differential protection |
JPH0834705B2 (en) * | 1988-11-16 | 1996-03-29 | 株式会社大林組 | Switch |
JPH0362858U (en) | 1989-10-20 | 1991-06-19 | ||
US5047890A (en) | 1990-03-12 | 1991-09-10 | Westinghouse Electric Corp. | Differential current protection circuits |
JPH0428737A (en) | 1990-05-25 | 1992-01-31 | Mitsubishi Petrochem Co Ltd | Thermoplastic resin composition |
JPH0729698Y2 (en) * | 1990-06-28 | 1995-07-05 | 株式会社戸上電機製作所 | Ground fault protection relay with arc light ground fault indicator |
JP2774693B2 (en) * | 1990-11-09 | 1998-07-09 | 株式会社東芝 | Earth leakage breaker |
JP2774377B2 (en) * | 1990-11-28 | 1998-07-09 | 協栄産業株式会社 | Ground fault detector |
US5241443A (en) | 1991-01-14 | 1993-08-31 | Jannock Electrical Products Inc. | Transformer fault protection device |
US5334912A (en) * | 1992-08-24 | 1994-08-02 | Usi Lighting, Inc. | Ground fault detector and associated logic for an electronic ballast |
US5361183A (en) | 1993-06-30 | 1994-11-01 | Alliedsignal Inc. | Ground fault protection for electrothermal de-icing applications |
US5521787A (en) | 1993-07-28 | 1996-05-28 | Sundstrand Corporation | Differential current fault protection for a system utilizing a power conversion unit exhibiting balanced load characteristics |
US5966280A (en) | 1993-08-24 | 1999-10-12 | Xerox Corporation | Modular, distributed equipment leakage circuit interrupter |
JPH07105819A (en) * | 1993-10-07 | 1995-04-21 | Toshiba Toransupooto Eng Kk | Trouble detecting circuit breaking apparatus |
US5552952A (en) | 1994-10-21 | 1996-09-03 | Sundstrand Corporation | Detection and isolation circuit for a failed bridge power rectifier and an electrical system employing same |
US5644510A (en) * | 1994-11-25 | 1997-07-01 | General Electric Company | Apparatus and method for motor overload protection using an elapsed-time signal for enabling computation of motor temperature data independently of temporary power interruption |
JPH08223777A (en) * | 1995-02-09 | 1996-08-30 | Toshiba Corp | Load controller |
US6246556B1 (en) | 1995-03-13 | 2001-06-12 | Square D Company | Electrical fault detection system |
US5745322A (en) | 1995-11-28 | 1998-04-28 | Raychem Corporation | Circuit protection arrangements using ground fault interrupter for overcurrent and overvoltage protection |
DE19618279A1 (en) | 1996-05-07 | 1997-11-13 | Kopp Heinrich Ag | DI protection switch |
GB2318002A (en) | 1996-10-02 | 1998-04-08 | Melvyn Webster | Earth leakage current sensor |
US5835322A (en) | 1997-07-07 | 1998-11-10 | Donald E. Smith | Ground fault interrupt circuit apparatus for 400-Hz aircraft electrical systems |
NL1007122C2 (en) | 1997-09-25 | 1999-03-26 | Odink & Koenderink Bv | Switching device for managing a multi-phase AC voltage network with a number of user units. |
US5969921A (en) | 1998-01-29 | 1999-10-19 | Eaton Corporation | Ground fault electrical switching apparatus for coordinating tripping with a downstream ground fault switch |
EP1080458B1 (en) | 1998-05-21 | 2007-08-15 | Smiths Aerospace, Inc. | Fault condition protective device for aircraft fuel gauging systems |
US6266219B1 (en) | 1998-06-02 | 2001-07-24 | Pass & Seymour, Inc. | Combination ground fault and arc fault circuit interrupter |
US6246558B1 (en) | 1998-08-24 | 2001-06-12 | Leviton Manufacturing Company | Circuit interrupting device with reverse wiring protection |
US6002563A (en) | 1998-09-03 | 1999-12-14 | Electronic Theatre Controls, Inc. | Plug-in power module incorporating ground-fault detection and reporting |
US6246332B1 (en) | 1998-11-18 | 2001-06-12 | Abb Power T&D Company Inc. | System and method for detecting voltage and current imbalance in an electrical energy supply |
JP2000217245A (en) * | 1999-01-22 | 2000-08-04 | Matsushita Electric Works Ltd | Ground-fault circuit breaker |
US6327124B1 (en) | 1999-02-05 | 2001-12-04 | Smc Electrical Products, Inc. | Low current ground fault relay |
JP3062858U (en) * | 1999-03-15 | 1999-10-15 | 彬發 柯 | Outlet overcurrent and leakage protection devices |
US6249230B1 (en) | 1999-03-18 | 2001-06-19 | Abb Power T&D Company Inc. | Ground fault location system and ground fault detector therefor |
JP2000354332A (en) * | 1999-06-09 | 2000-12-19 | Matsushita Electric Works Ltd | Charging device for electric vehicle |
US6278596B1 (en) | 1999-06-17 | 2001-08-21 | Tektronix, Inc. | Active ground fault disconnect |
US6329785B1 (en) * | 2000-02-29 | 2001-12-11 | Gas Research Institute | Pulse width modulated controlled induction motor |
JP2001268779A (en) | 2000-03-15 | 2001-09-28 | Matsushita Electric Works Ltd | Earth-leakage circuit breaker |
ES2164593B1 (en) | 2000-03-17 | 2003-05-16 | Ge Power Controls Iberica S L | DETECTION DEVICE FROM GROUND TO EARTH. |
US6320731B1 (en) | 2000-05-24 | 2001-11-20 | Electric Boat Corporation | Fault tolerant motor drive arrangement with independent phase connections and monitoring system |
US6583975B2 (en) * | 2001-02-01 | 2003-06-24 | Hydro-Aire, Inc. | Aircraft applicable ground fault circuit interrupter |
JP4178109B2 (en) | 2002-07-16 | 2008-11-12 | フレゼニウス メディカル ケアー ドイチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング | Dialysis container |
JP4200229B2 (en) | 2004-04-12 | 2008-12-24 | 謙治 佐藤 | White board, projection screen device |
-
2001
- 2001-02-01 US US09/775,337 patent/US6583975B2/en not_active Expired - Lifetime
- 2001-09-14 US US09/954,474 patent/US6618229B2/en not_active Expired - Lifetime
-
2002
- 2002-01-30 WO PCT/US2002/002893 patent/WO2002061905A2/en not_active Application Discontinuation
- 2002-01-30 BR BR0206879-6A patent/BR0206879A/en not_active Application Discontinuation
- 2002-01-30 CN CNB028044576A patent/CN1323475C/en not_active Expired - Fee Related
- 2002-01-30 CA CA2437377A patent/CA2437377C/en not_active Expired - Fee Related
- 2002-01-30 EP EP02706101A patent/EP1364437A2/en not_active Withdrawn
- 2002-01-30 JP JP2002561338A patent/JP2004519185A/en active Pending
-
2003
- 2003-07-01 US US10/611,218 patent/US6788505B2/en not_active Expired - Lifetime
-
2004
- 2004-10-18 US US10/967,482 patent/US7064941B2/en not_active Expired - Lifetime
-
2006
- 2006-04-28 US US11/413,737 patent/US7312965B2/en not_active Expired - Lifetime
-
2007
- 2007-10-31 US US11/931,803 patent/US7630182B2/en not_active Expired - Fee Related
-
2008
- 2008-03-20 US US12/052,451 patent/US7672099B2/en not_active Expired - Fee Related
- 2008-03-21 US US12/053,071 patent/US7688558B2/en not_active Expired - Fee Related
- 2008-03-21 US US12/052,975 patent/US7667935B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3512045A (en) * | 1968-06-28 | 1970-05-12 | Gen Signal Corp | Ground fault responsive apparatus for electric power distribution apparatus |
US4093977A (en) * | 1976-06-15 | 1978-06-06 | Westinghouse Electric Corp. | Ground fault protective device |
US4783713A (en) * | 1986-08-29 | 1988-11-08 | Cezhan Chen | Full automatic electric shock protector apparatus |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8981265B2 (en) | 2008-12-30 | 2015-03-17 | Ppg Industries Ohio, Inc. | Electric circuit and sensor for detecting arcing and a transparency having the circuit and sensor |
Also Published As
Publication number | Publication date |
---|---|
US6583975B2 (en) | 2003-06-24 |
US7312965B2 (en) | 2007-12-25 |
US6788505B2 (en) | 2004-09-07 |
CN1498448A (en) | 2004-05-19 |
US20060250730A1 (en) | 2006-11-09 |
US20080062592A1 (en) | 2008-03-13 |
US20040090724A1 (en) | 2004-05-13 |
US20090086396A1 (en) | 2009-04-02 |
JP2004519185A (en) | 2004-06-24 |
US7672099B2 (en) | 2010-03-02 |
WO2002061905A3 (en) | 2003-03-13 |
CA2437377A1 (en) | 2002-08-08 |
CN1323475C (en) | 2007-06-27 |
US20020101698A1 (en) | 2002-08-01 |
WO2002061905A9 (en) | 2004-04-01 |
US7064941B2 (en) | 2006-06-20 |
US7667935B2 (en) | 2010-02-23 |
US6618229B2 (en) | 2003-09-09 |
US7630182B2 (en) | 2009-12-08 |
BR0206879A (en) | 2004-01-20 |
EP1364437A2 (en) | 2003-11-26 |
US20050146818A1 (en) | 2005-07-07 |
US20080304190A1 (en) | 2008-12-11 |
US20020105764A1 (en) | 2002-08-08 |
US7688558B2 (en) | 2010-03-30 |
CA2437377C (en) | 2012-03-27 |
US20080316658A1 (en) | 2008-12-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2437377C (en) | Aircraft applicable ground fault circuit interrupter | |
US7417836B2 (en) | Aircraft applicable circuit imbalance detection and circuit interrupter and packaging thereof | |
US7016171B2 (en) | Current fault detector and circuit interrupter and packaging thereof | |
US5805394A (en) | Overvoltage protection circuit for a generating system utilizing a fault current sensing Circuit in combination with a shunting circuit | |
US5422778A (en) | Protection system for controller and control wiring induced under voltage faults in an electric power generating system | |
EP0803144A1 (en) | Protection system for a shorted rectifying diode within a synchronous generator | |
WO2008027874A2 (en) | Current limiting dc motor starter circuit | |
CN108281331B (en) | Three-phase undervoltage tripping device and molded case circuit breaker with same | |
US7554301B2 (en) | Fault current limiting in an electrical power network | |
JPH0993790A (en) | Earth leakage breaker |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A2 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ OM PH PL PT RO RU SD SE SG SI SK SL TJ TM TN TR TT TZ UA UG UZ VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A2 Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
AK | Designated states |
Kind code of ref document: A3 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ OM PH PL PT RO RU SD SE SG SI SK SL TJ TM TN TR TT TZ UA UG UZ VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A3 Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2002561338 Country of ref document: JP Ref document number: 2437377 Country of ref document: CA |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2002706101 Country of ref document: EP Ref document number: 028044576 Country of ref document: CN |
|
WWP | Wipo information: published in national office |
Ref document number: 2002706101 Country of ref document: EP |
|
REG | Reference to national code |
Ref country code: DE Ref legal event code: 8642 |
|
COP | Corrected version of pamphlet |
Free format text: PAGES 1-9, DESCRIPTION, REPLACED BY NEW PAGES 1-9; PAGES 10-13, CLAIMS, REPLACED BY NEW PAGES 10-13; PAGES 1/13-13/13, DRAWINGS, REPLACED BY NEW PAGES 1/14-14/14; DUE TO LATE TRANSMITTAL BY THE RECEIVING OFFICE |
|
WWW | Wipo information: withdrawn in national office |
Ref document number: 2002706101 Country of ref document: EP |