• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention provides systems, methods and devices for distributing aircraft electrical energy (200), comprising a bipolar high-voltage direct current source component (210); an electric charge component (226) capable of absorbing electrical power from the bipolar high voltage direct current source component (210); a set of switching components (216) configured to selectively establish an electrical connection of the bipolar high-voltage direct current source component (210) to the electric charge component (226) and an earth fault interrupt component ( 232) coupled to the set of switching components (216). The ground fault interrupt component (232) is configured to detect a ground fault based on a detected difference between an output current of the switch component set (216) and an output current of the switch component set (216). return current from the electric charge component (226).
    公开号:FR3039823A1
    申请号:FR1657556
    申请日:2016-08-04
    公开日:2017-02-10
    发明作者:Peter James Handy
    申请人:GE Aviation Systems Ltd；
    IPC主号:
    专利说明:

    Bipolar High Voltage DC Earth Fault Detection Systems, Methods and Devices
    Electrical power distribution systems manage the power allocation of power sources to electrical loads that consume distributed electrical power. In an aircraft, gas turbines used to propel the aircraft typically provide mechanical energy which ultimately excites a number of different accessories such as generators, generators / starters, permanent magnet alternators ( PMA), fuel pumps and hydraulic pumps, ie equipment for functions needed on aircraft other than propulsion. For example, today's aircraft require electrical energy for electrical loads related to avionics, engines, and other electrical equipment.
    Over time, the voltages of aircraft electrical power sources have increased. Aircraft with 14 to 28 Volt DC (DC) power systems were replaced by aircraft with 115 VAC and 230 VAC power systems. Currently, an aircraft may include one or more sources of electrical power that operate at voltages of greater than or equal to 270 VDC. For example, a current commercial two-engine jumbo uses an electrical system that is a hybrid voltage system with subsystems that operate at 230 VAC, 115 VAC, 28 VDC, and a DC subsystem. bipolar high voltage which has sources of plus and minus 270 VDC.
    Voltages in high voltage direct current (DC) electrical systems reach levels comparable to those of domestic AC systems. In domestic AC systems, a circuit breaker can trip to a cut-off position, typically by means of an electromechanical switch that can be operated in about 50 milliseconds (ms), to power off the power line when the Earth current exceeds a level of 25 to 30 milliamps (mA). But in a high voltage DC electrical system, it is complicated to make similar arrangements because of limited access to the earth loop, which is necessary to obtain a sufficiently accurate current measurement. Namely, for unipolar DC electrical systems, it is difficult to measure the difference between the output current and the return current because the current return path from the load passes through the chassis of the aircraft.
    According to one aspect of the invention, an aircraft electrical power distribution system comprises a bipolar high voltage direct current source component provided with a positive voltage conductor and a negative voltage conductor; an electric charge component capable of absorbing electrical power from the bipolar high-voltage direct current source component; a set of switching components configured to selectively establish an electrical connection of the bipolar high-voltage direct current source component to the electric charge component by switching between an open state that electrically disconnects the bipolar high-voltage direct current source component from the electric charge component and a closed state that electrically connects the high voltage direct current source component to the electric charge component, wherein a first subset of switching components is coupled to the positive conductor of the bipolar high voltage direct current source component and a second sub-set of switching components the set of switching components is coupled to the negative conductor of the bipolar high-voltage direct current source component; and an earth fault interrupt component coupled to the set of switching components. The ground fault interrupt component is configured to detect a ground fault based on a detected difference between an output current of the switching component set and a feedback current from the component. forming electric charge.
    In another aspect, a ground fault mitigation method includes powering up a bipolar high voltage direct current source component having a positive voltage conductor and a voltage conductor. negative; closing a set of switching components for electrically connecting the bipolar high-voltage direct current source component to an electric charge component capable of absorbing power from the bipolar high-voltage direct current source component; detecting a ground fault using an earth fault interrupt component based on a detected difference between an output current of the switching component set and a current of return from the electric charge component; applying a signal indicative of the detected earth fault to the set of switching components; and opening the switching component assembly to electrically disconnect the bipolar high-voltage direct current source component from an electric charge component.
    In another aspect, a ground fault interrupt device includes a ground fault interrupt component coupled to a set of switching components. The set of switching components are configured to selectively establish an electrical connection of a bipolar high-voltage direct current source component to an electric charge component capable of absorbing electrical power from the bipolar high-voltage direct current source component. by switching between an open state that electrically disconnects the bipolar high-voltage direct current source component of the electric charge component and a closed state that electrically connects the high voltage direct current source component to the electric charge component. A first subset of switching components is coupled to a positive conductor of the bipolar high voltage direct current source component and a second subset of switching components is coupled to the negative conductor of the bipolar high voltage direct current source component. The ground fault interrupt component is configured to detect a ground fault based on a detected difference between an output current of the switching component set and a feedback current from the component. forming electric charge.
    Various other objectives, features and advantages of the invention will emerge from the following detailed description, illustrated by the drawings in which: FIG. 1 is a schematic top view of an example of an aircraft and a system electric power distribution system according to various aspects of the present invention; FIG. 2 is a diagram of an example of a high voltage DC electric power distribution system according to various aspects of the present invention; FIG. 3 is a flowchart of a ground fault interrupt method on a bipolar high voltage DC power supply system according to various aspects of the present invention; FIG. 4 is a schematic representation of an example of a bipolar high voltage electrical power distribution system provided with a ground fault interrupting component according to various aspects of the present invention; FIG. 5 is a schematic representation of an example of a bipolar high voltage electrical power distribution system provided with a ground fault interrupting component according to various aspects of the present invention; FIG. 6 is a graphical representation of an example of voltage and current waveforms which illustrates the operation of the bipolar high voltage electrical energy distribution system provided with an interruption component in the event of a defect in the earth according to various aspects of the present invention; and FIG. 7 is a graphical representation of an example of voltage and current waveforms which illustrates the operation of the bipolar high voltage electrical power distribution system provided with an interrupting component in case of a fault. to earth according to various aspects of the present invention.
    In this description, the embodiments of the present invention are described in the context of an aircraft, which allows the production of electrical energy from an energy source such as a turbine engine, jet fuel, hydrogen, etc. Although an embodiment of the invention is shown in the environment of an aircraft, it will be understood, however, that the invention is not so limited and can be applied generally to energy distribution systems. in non-aviation applications, such as other mobile applications and non-mobile industrial, commercial and residential applications. For example, applicable mobile environments may include an aircraft, a spacecraft, a space launcher, a satellite, a locomotive, an automobile, etc. Commercial environments may include manufacturing plants or facilities or infrastructure for the generation and distribution of electrical energy.
    At least some embodiments of the invention provide bipolar high voltage electrical power distribution systems, methods and apparatus that include earth fault detection and interruption capabilities. The bipolar high voltage electrical power distribution system includes a set of switching components such as Solid State Power Controllers (SSPCs). It will be understood that an "array" may comprise any number of semiconductor switches, including a single semiconductor switch. Similarly, "a set," as the term is used herein, can include any number of elements, including a single element. It will be appreciated that a bipolar DC power supply or a bipolar DC power source, as used herein, can be defined as a DC power source whose output voltage can be set to positive or negative and that can provide a current. It will be understood that high voltage direct current, as used herein, can be defined as electrical energy at voltages high enough to inflict damage to living things. For example, voltages greater than 50 V applied to a continuous segment of dry human skin can cause cardiac fibrillation if they generate electrical currents in body tissues that pass through the thoracic area. It will be appreciated that a ground fault, as the term is used herein, may be defined as accidental contact between a live conductor of an electrical load or an electrical power distribution system and "earth" or electric ground such as a chassis mass.
    Currently, few aircraft have bipolar high voltage energy sources such as plus and minus 270 VDC, and none of these aircraft incorporate an electrical power distribution system for bipolar high voltage power. However, through the use of a high voltage DC power distribution system, bipolar high voltage DC sources will no longer be confined to a single area of the aircraft. Therefore, bipolar high voltage DC sources will require, through the electrical power distribution system, an ability to attenuate earth fault events that can occur at any point on the earth. the aircraft where a load is fed by the high voltage bipolar DC source.
    Turning now to Fig. 1 is a schematic top view of an exemplary aircraft and electric power distribution system according to various aspects of the present invention. An aircraft 2 is shown as having at least one gas turbine, shown here in the form of a left engine system 12 and a right engine system 14 which may be substantially identical to each other. The aircraft 2 may comprise any number of engine systems. The left engine system 12 may be coupled to one or more electrical power sources 16 that convert mechanical energy into electrical energy. It will be understood that any part or all of the engines of an aircraft 2, comprising the left and right engine systems 12, 14, can thus be coupled to one or more bipolar 16 high-voltage DC power sources. A bipolar high voltage DC power source 16 may be coupled to an electrical power distribution system 18 that selectively powers a set of systems and devices on the aircraft 2 that collectively constitute the electrical load. Systems and devices powered by the bipolar high voltage DC power source 16 through the electrical power distribution system 18 may be any system or device on an aircraft capable of absorbing electrical power and include, but are not limited to, flight control actuators 26, localized step-down converters 27 for cockpit electronic indicators, climate control systems 28, etc.
    In the aircraft 2, the left and right engine systems 12, 14 in operation provide mechanical energy that can be extracted through a body, to provide a motive force for the DC power source. Bipolar high voltage 16. Other sources of energy may include, without limitation, generators, batteries, fuel cells, emergency power sources such as a reel-assisted turbine generator (RAT), rectifiers for converting one or more AC source inputs into a bipolar high voltage DC source, etc. The electrical power source 16 itself provides the electric power generated to the electrical loads for the systems and devices 26, 27, 28 for charging operation, which is distributed by the electrical power distribution system 18.
    Referring now to FIG. 2 is a diagram of an exemplary bipolar high voltage electrical power distribution system 50 according to various aspects of the present invention. The bipolar high voltage DC power distribution system includes a bipolar high voltage DC source component 52 coupled to a set of switching components 54. The switch component assembly 54 selectively provides an electrical connection of the DC voltage source component. electrical charge component bipolar high voltage 58. A ground fault interrupt component 56, coupled to the set of switching components 54 and the electric charge component 58, provides the measurement of the output current. of the set of switching components 54 and the return current from the electric charge component 58. A communication component 60 is coupled to the set of switching components 54 to control and monitor the state of the set of switching components 54.
    The bipolar high voltage DC source component 52 is a bipolar high voltage power source or DC power supply. The bipolar high voltage DC source component 52 can provide any positive and negative voltage level to be used in the electrical power distribution to an electric charge component 58, including but not limited to a positive and negative 270 V voltage. . The switching component assembly 54 includes a set of semiconductor switches. The semiconductor switch assembly can include any type of solid-state switch that can be turned on or off (that is, closed or open) when an external voltage is present. is applied to a set of control terminals of the switch. Each of the semiconductor switches in the switching component assembly 54 may include a solid-state electronic switching device that switches current to the charging circuit of the electric charge component 58, and a coupling mechanism for allow the control signal to activate the switch without electromechanical components. The switching component assembly 54 may be any type of solid state electronic switch, including but not limited to a solid state power controller (SSPC), a solid state relay having a single metal-oxide-semiconductor field effect transistor (MOSFET), a solid-state relay comprising multiple MOSFET transistors mounted in a parallel configuration, etc .;
    One configuration of the switching component set 54 is to use SSPCs which are semiconductor devices that control the electric power supplied to a load. In addition, SSPCs perform monitoring and diagnostic functions to identify overload situations and prevent short circuits. Functionally, the SSPCs are similar to circuit breakers with electromechanical switching elements that will protect the wiring and loads against faults, but since SSPCs are more reliable and cut the current faster than electromechanical breaker elements, the SSPCs are typically used in safety-critical electrical systems, such as those found in aircraft. SSPCs can change state in less than a few microseconds, compared to electromechanical switches that require about 30 ms to complete a transition from one state to another. When implemented with SSPCs, the set of switching components 54 may include integrated monitoring and protection functions including, but not limited to, voltage monitoring, current monitoring, temperature monitoring, current limiting, I2t monitoring, arc fault protection and low fidelity earth fault protection, etc. The built-in monitoring and protection functions of the SSPCs allow the switching component assembly 54 to function as a controller that can control outputs for the loads to ensure proper operations. SSPCs may include configurable microprocessors that can be programmed to increase control characteristics. Current monitoring on a SSPC typically does not have sufficient resolution for ground fault detection. Namely, the current monitoring functions of the SSPCs offer a resolution range of 3 to 5%. As a result, a switch transmitting approximately 10 amperes (A) will not detect a ground fault of less than 300 mA with the built-in earth fault protection of an SSPC. The switching component assembly 54 may comprise any number of switches, including but not limited to a first switch coupled to a positive lead of the bipolar high voltage DC component component 52 and a second switch coupled to a negative lead of the source component. Thus, in one configuration, the set of switching components 54 comprises a first SSPC coupled to a positive conductor of the bipolar high voltage DC component component 52 and a second SSPC coupled to a negative conductor of the source component. DC high voltage bipolar 52.
    The communication component 60 for controlling and monitoring the state of the switch component assembly 54 communicates with other control elements of the aircraft. The communication component 60 reports the status of the SSPCs to other vehicle management control systems. The communication component 60 can send data to the switch, the data being indicative of instructions for the switch, reading the state of the switch which comprises the state of opening or closing of the switch , and monitoring the health of the switch that understands the temperature of the switch. The communication component 60 may be based on any hardware and data communication protocol for transmitting control and status data of the set of switching components 54, including but not limited to balanced interconnect cable configured to implement the recognized standard 458 (RS-485), a two-wire serial cable configured to implement a controller network protocol (CAN bus), a three- or five-wire serial cable configured to implement the recognized standard 232 (RS-232), etc.
    The earth fault interrupt component 56 monitors the output currents of the positive and negative SSPCs in the bipolar high voltage DC distribution system 50. With a bipolar high voltage electrical distribution system 50, the current flows from of the bipolar high-voltage DC source component 52, outputs to the switching component assembly 54, exits to and returns to the electric charge component 58. Accordingly, the ground fault interrupt component 56 is configured to determine the difference between the current flowing from the set of switching components 54 to the electric charge component 58 and the flowing current of the forming component. electrical load 58 to the set of switching components 54. The ground fault interrupt component 56 may be any device capable of determining a differential current indicative of a ground fault in the earth. the bipolar high voltage electrical distribution system 50, including but not limited to a conventional physical transformer, a toroidal current transformer, a Hall effect DC sensor, and a fluxgate current transducer.
    Referring now to FIG. 3 is a flowchart showing a ground fault interrupt method 100 on a bipolar high voltage DC power supply system according to various aspects of the present invention. In step 110, the bipolar high voltage DC source component 52 energizes the bipolar high voltage DC distribution system 50. Depending on the type or configuration of the bipolar high voltage DC source component 52, the power up may include a generator, starting a motor, sending a command to turn on the power of the source, closing one or more circuits, etc. At a step 112, the set of switching components 54 are closed. The electric charge components 58 are energized and, during normal operation, properly absorb power in accordance with the operating requirements of said electric charge components 58. If a ground fault occurs, at a step 114 the interrupt component in case of earth fault 56 detects the earth fault. To detect a ground fault, the earth fault interrupt component 56 can measure or detect any electrical characteristic indicative of a ground fault, including but not limited to a voltage, a current , a resistor, a voltage variation, a current variation or a resistance variation in any electrical component internal or external to the electrical power distribution system 50. The interruption component in the event of a ground fault 56 can measure or detect the signal with any modality used for signal detection and processing, including but not limited to digital, analog, discrete, continuous, or combinations thereof. The earth fault interrupt component 56 applies a signal, in a step 116, to a monitoring module, for example in a component 218 described below with reference to FIGS. 4 and 5, of the set of switching components 54. In a step 118, the switching component assembly 56 opens the switches and turns off the electric charge component 58.
    Referring now to Figure 4 which is a schematic representation of an example of a bipolar high voltage electrical power distribution system 200 provided with a ground fault interrupting component 232 in various aspects of the invention. present invention. The bipolar high voltage DC source component 210 includes two high voltage DC sources 211 each coupled to a chassis ground 236, one by the negative conductor and the other by the positive conductor. The bipolar high voltage DC source component 210 is coupled to the switch component assembly 216 which includes two SSPCs 212 and 214; a first SSPC 212 coupled to the positive side of the bipolar high voltage DC source component 210 and a second SSPC 214 coupled to the negative side of the bipolar high voltage DC source component 210. The coupling between the bipolar high voltage DC source component 210 and the set of Switching components 216 may include a current limiting wire 238. The switch component assembly 216 is coupled to the interruption component in the event of a ground fault 232. The ground fault interrupt component 232 is coupled to the electric charge component 226. The coupling between the earth fault interrupt component 232 and the electric charge component 226 may include a current limiting wire 238.
    The first and second SSPC 212, 214 may include a number of subcomponents and modules for controlling and protecting the set of switching components 216. An SSPC 212, 214 may include a main semiconductor switch 224 which opens or closes for coupling or decoupling the electric charge component 226 to the bipolar high voltage DC source component 210. The main semiconductor switch 224 may include one or more protection elements, including but not limited to a metal oxide varistor (MOV), a transient voltage suppressor (TVS), and the like. An SSPC 212, 214 may include one or more damping circuits 228 connected to the input of the switch, the output of the switch, or both, to suppress voltage spikes and dampen oscillation due to inductance of the circuit when opening a switch. An SSPC 212, 214 may include one or more integrated test circuits 230 for providing integrated test functions (BITs). The integrated test circuit 230 allows the operation of an integrated triggered test system (IBIT) which enables automatic testing of the SSPC 212, 214 to verify the proper operation of the SSPC 212, 214. The integrated test circuit 230 can test any function of the SSPC and includes without limitation an arc fault detection circuit for the detection of an arc fault. When the two SSPCs are open, the voltage developed at the output of each SSPC due to a leakage of the semiconductor components is managed by a resistive element 240, 241 coupled to the output of the SSPC 212, 214 and to the earth. 236. The SSPC 212, 214 may include a switch control subcomponent 222 that can coordinate communications with external communication components 234, enable protection functions through a monitoring module 218. and controlling the state of the main switch 224 of the SSPC 212, 214. The monitoring module 218 may include any monitoring functions for determining potential events that may damage the switch, including but not limited to functions of voltage monitoring, current monitoring, temperature monitoring, current limiting, I2t monitoring, power loss protection arc fault and earth fault protection, etc. The control module 220 can control the state of the main switch 224 based on inputs from either external communication components 234 or the monitoring module 218, or combinations of the two.
    As shown in Fig. 4, the earth fault interrupt component 232 includes a conventional magnetic core physical transformer. Positive and negative power cables from the positive and negative SSPC output 212, 214 are passed through the transformer with in-phase windings. The detection windings 242 at the transformer provide an indicative imbalance indication of a ground fault. During normal operation, during which the current from the positive side of the charge of the electric charge component 226 and the current from the negative side of the charge of the electric charge component 226 are of equal magnitude, the resulting detection voltage is zero. Since the charge of the electric charge component 226 is not asymmetrically referenced to the chassis, as would be the case for a unipolar DC voltage source system, at the time a ground fault occurs on the output positive or negative of the set of switching components 216, a positive or negative voltage peak is detected on the sensing windings 242 of the interrupting component transformer in the event of a ground fault 232, thereby determining the existence and the location of the defect. Two windings are provided on the transformer of the ground fault interrupt component 232 to account for both SSPC 212, 214 monitoring earth faults. Since there is no continuous magnetic field in the transformer core during normal operation, the transformer may comprise either an air core or a high permeability core. To provide more sensitivity to ground faults, it is possible to increase the number of turns on each sense coil 242, as well as the permeability of the selected core material. The output voltage of each sensing coil may be filtered to eliminate nuisance tripping created by the switching operation between multiple charges having different electrical characteristics.
    Fig. 5 is a schematic representation of an example of a bipolar high voltage electrical power distribution system provided with a ground fault interrupting component according to various aspects of the present invention. The bipolar high voltage electrical power distribution system with earth fault interrupting component is similar to that shown in FIG. 4; accordingly, analogous components will be identified by the same numbers increased by 100, and it will be understood that the description of analogous components of the first bipolar high-voltage electrical energy distribution system with interruption component in case of earth fault applies to the second bipolar high-voltage electrical distribution system with interrupting component in the event of a ground fault, unless otherwise specified. The ground fault switch component 332 includes a toroidal current transformer.
    Fig. 6 shows the result of a simulation of the earth fault detection system with a human body model directly connected to the output of the positive SSPC 212. The set of graphs provided by way of example are intended to illustrate a non-restrictive example of the method described, and do not specifically represent signals, sensors, values or operations necessary for the process. At a time (1), the bipolar high voltage DC source component 52, which is a positive and negative 270 VDC power supply as shown in FIG. 4 and FIG. 5 at 210 and 310, is energized. At a time (2), the set of switching components 54, which are two SSPCs 212, 214, are closed to energize an electrical charge component 58. At a time (3), a ground fault which is modeled by a capacitor of 450 nanofarads (nF) in parallel with a resistor of 500 ohms (Ω) is applied to the output of the positive SSPC 212, 312, which triggers a voltage spike on the sense winding 242, 342 of the earth fault interrupt component 56, 232, 332. The signal can be applied to the monitoring module 218, 318 of the switch control subcomponent 222, 322 of the SSPC 212, 214, 312, 314. In the case of a confirmed fault, the control module 220, 320 may open the SSPC 212, 214, 312, 314.
    Fig. 7 shows the result of a simulation of the earth fault detection system with a human body model connected directly to the negative SSPC output 214, 314. Again, the set of graphs provided as Examples are intended to illustrate a non-restrictive example of the method described, and do not specifically represent signals, sensors, values or operations necessary for the process. At a time (1), the bipolar high voltage DC source component 52, which is a positive and negative 270 VDC power supply as shown in FIG. 4 and FIG. 5 at 210 and 310, is energized. At a time (2), the set of switching components 54, which are two SSPCs 212, 214, 312, 314, are closed to energize an electrical charge component 58. At a time (3), a fault to ground which is modeled by a capacitor of 450 nanofarads (nF) in parallel with a resistor of 500 ohms (Ω) is applied to the output of the positive SSPC 212, 312, which triggers a voltage peak on the winding of detection 242, 342 of the ground fault interrupt component 56, 232, 332. Again, the signal can be applied to the monitoring module 218, 318 of the switch control subcomponent 222, 322 of the SSPC 212, 214, 312, 314. In the case of a confirmed fault, the control module 220 can open the SSPC 212, 214.
    Although a unipolar DC power distribution system returns current through the aircraft chassis, a bipolar DC source power distribution system transmits power to the first wire and return by another, which provides access to the return of each power supply. In this way, the ground fault interrupt component operates positive and negative wires on the load. As a result, the bipolar DC power distribution system can provide measurement of a differential current between the supply and return conductors. The differential current measurement allows the bipolar DC power distribution system to determine whether power is being transmitted from one side of the load to the chassis ground, indicating a ground fault. .
    The technical effects of the embodiments described above include the detection and mitigation of earth fault events in a high voltage DC power distribution system, based on the use of a detection technique and simple and cost effective ground fault interrupt. In addition, the embodiments described above circumvent the problem of continuous steady-state polarization, in a transformer-based ground fault interrupt system, by use of a single magnetic core for the dc currents. power supply and return, resulting in the absence of permanent magnetic field in the core of the transformer. The electrical power distribution system described above monitors the positive and negative SSPC output currents in a bipolar high voltage DC array, and can determine a ground leakage current of the order of 5 mA to provide earth fault detection system more sensitive.
    To a extent not already described, the various features and structures of the various embodiments may be used in combination with each other as needed. The fact that a feature is not illustrated in all embodiments does not mean that it can not be, but this is done for the sake of brevity of the description. Thus, the various features of the various embodiments may be mixed and associated as needed to form new embodiments, whether or not the new embodiments are expressly disclosed. All combinations or permutations of features described in the present invention are covered by this description.
    Component List 2 Aircraft 12, 14 Engine System 16 Bipolar High Voltage DC Power Source 18 Electric Power Distribution System 26 Actuator 27 Localized Voltage Step Down Converter 28 Climate Control System 50 High DC Power Distribution System bipolar voltage 52 DC bipolar high voltage source component 52 Switching component assembly 56 Ground fault interrupt component 58 Electrical load component 60 Communication component 100 Interrupted ground fault method 110, 112, 114, 116, 118
    Process steps 100 200 Bipolar High Voltage DC Distribution System 210 Bipolar High Voltage DC Component Component
    211 Source CC
    212 SSPC
    214 SSPC 216 Switching Component Assembly 218 Monitoring Module 220 Control Module 222 Switching and Monitoring Control Sub-Component 224 Main Switch 226 Electric Charge Component 230 Built-in Test Circuit (BIT) 228 Damping Circuit 232 Interrupt component in the event of a ground fault 234 Communication component 236 Chassis ground 238 Current limiting wire 240 Resistance 242 Detection winding 300 DC bipolar high voltage distribution system 310 DC bipolar high voltage source component
    311 Source CC
    312 SSPC
    314 SSPC 316 Switching component assembly 318 Monitoring module 320 Control module 322 Switching and monitoring control subcomponent 324 Main switch 326 Electric charging component 330 Integrated test circuit (BIT) 328 Damping circuit 332 Interrupt component in case of earth fault 334 Communication component 336 Chassis ground 338 Current limiting wire 340 Resistance 342 Detection winding
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    An aircraft electrical power distribution system (200), comprising: a bipolar high-voltage direct current source component (210) having a positive voltage conductor and a negative voltage conductor; an electric charge component (226) capable of absorbing electrical power from the bipolar high voltage direct current source component (210); a set of switching components (216) configured to selectively establish an electrical connection of the bipolar high-voltage direct current source component (210) to the electric charge component (226) by switching between an open state that electrically disconnects the current source component continuous bipolar high voltage (210) of the electric charge component (226) and a closed state that electrically connects the bipolar high voltage direct current source component (210) to the electric charge component (226), wherein a first subset of switching components (212) is coupled to the positive conductor of the bipolar high-voltage direct current source component (210) and a second subset of switching components (214) is coupled to the negative conductor of the high-voltage direct current source component bipolar (210); and a ground fault interrupt component (232) coupled to the set of switching components (216) and configured to detect a ground fault based on a detected difference between an output current of the switching component assembly (216) and a return current from the electric load component (226).
    [2" id="c-fr-0002]
    The system of claim 1, wherein at least a subset of the set of switching components (216) opens in response to a detected signal from the interruption component in the event of a ground fault ( 232).
    [3" id="c-fr-0003]
    The system of claim 1, wherein the bipolar high-voltage direct current source component (210) comprises two 270-volt DC power supplies (211).
    [4" id="c-fr-0004]
    The system of claim 3, wherein a negative lead of one of the two 270 volt DC power supplies is coupled to a chassis ground (236) and the positive lead of the other of the two power supplies. 270 volts DC is coupled to chassis ground (236).
    [5" id="c-fr-0005]
    The system of claim 1, wherein the switch component assembly (216) comprises two solid state power controllers (SSPCs).
    [6" id="c-fr-0006]
    The system of claim 1, further comprising a communication component (234) configured to apply an external voltage to a set of control terminals of the set of switching components (216) to change the state of the device. set of switching components (216).
    [7" id="c-fr-0007]
    The system of claim 1, wherein the ground fault interrupt component (232) comprises a transformer provided with either a high permeability core or an air core.
    [8" id="c-fr-0008]
    The system of claim 7, wherein the transformer comprises a toroidal current transformer.
    [9" id="c-fr-0009]
    The system of claim 1, wherein the ground fault interrupt component (232) comprises either a Hall effect DC sensor or a magnetometric probe current transducer.
    [10" id="c-fr-0010]
    The system of claim 7, wherein the transformer comprises a pair of sense windings (242) which detect a positive or negative voltage peak indicative of a ground fault based on the difference between the current from the positive side of the charge of the electric charge component (226) and the current from the negative side of the charge of the electric charge component (226).
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    FR2836303A1|2003-08-22|DEVICE FOR REGULATING AN ELECTRICAL NETWORK, ESPECIALLY A MOTOR VEHICLE
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    同族专利:
    公开号 | 公开日
    CN106443301B|2019-12-17|
    US10569895B2|2020-02-25|
    GB201513998D0|2015-09-23|
    US20180134408A1|2018-05-17|
    GB2541026B|2019-07-31|
    BR102016018159A2|2017-02-14|
    GB2541026A|2017-02-08|
    CA2938234A1|2017-02-07|
    JP2017060381A|2017-03-23|
    CN106443301A|2017-02-22|
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    法律状态:
    2017-08-25| PLFP| Fee payment|Year of fee payment: 2 |
    2018-07-13| PLSC| Search report ready|Effective date: 20180713 |
    2019-08-23| RX| Complete rejection|
    2020-04-10| RX| Complete rejection|Effective date: 20200305 |
    优先权:
    申请号 | 申请日 | 专利标题
    GB1513998.3A|GB2541026B|2015-08-07|2015-08-07|Systems, methods and devices for bipolar high voltage direct current ground fault detection|
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