CN111799755A - A earth leakage protection circuit for aviation aircraft and power supply circuit thereof - Google Patents
A earth leakage protection circuit for aviation aircraft and power supply circuit thereof Download PDFInfo
- Publication number
- CN111799755A CN111799755A CN202010773151.6A CN202010773151A CN111799755A CN 111799755 A CN111799755 A CN 111799755A CN 202010773151 A CN202010773151 A CN 202010773151A CN 111799755 A CN111799755 A CN 111799755A
- Authority
- CN
- China
- Prior art keywords
- circuit
- power supply
- leakage protection
- line
- relay
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001514 detection method Methods 0.000 claims abstract description 25
- 238000012360 testing method Methods 0.000 claims abstract description 25
- 238000012937 correction Methods 0.000 claims description 24
- 230000007935 neutral effect Effects 0.000 claims description 19
- 239000003990 capacitor Substances 0.000 description 15
- 230000006870 function Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 238000005538 encapsulation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/50—Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
- G01R31/52—Testing for short-circuits, leakage current or ground faults
-
- 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
- H02H3/044—Checking correct functioning of protective arrangements, e.g. by simulating a fault
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Emergency Protection Circuit Devices (AREA)
Abstract
The application provides a leakage protection circuit for aviation aircraft and power supply circuit thereof, leakage protection circuit includes: the current detection unit, the relay, the first switch unit, the control unit and the second switch unit receive the test signal through the second switch unit, so that at least one resistor on the output end is connected between the zero line and the live line, a current difference value larger than a preset first current value is formed between the zero line and the live line, then after the detected current difference value larger than the first current value is transmitted to the control unit by the determination current detecting unit, whether the control unit controls the first switch unit to switch on the power supply of the relay so as to disconnect the live wire and the load when the power supply of the relay is switched on to stop the power supply to determine whether the leakage protection circuit has a fault, if the power supply of the power supply is not cut off by the leakage protection circuit under the test condition, the fault exists, and therefore self-checking of the leakage protection circuit is achieved, and safety of the circuit is improved.
Description
Technical Field
The application relates to the technical field of leakage protection, in particular to a leakage protection circuit for an aircraft and a power supply circuit thereof.
Background
At present, a power supply circuit of an aircraft generally has a leakage protection circuit, and the power supply is cut off in time when leakage exists in the power transmission process through the leakage protection circuit, but the leakage protection circuit in the power supply circuit cannot find the fault, so that the problem of low safety exists.
Disclosure of Invention
An object of the embodiment of the application is to provide a leakage protection circuit for an aircraft and a power supply circuit thereof, so as to solve the problem that the safety is low when the leakage protection circuit in the existing power supply circuit fails to find out.
In a first aspect, an embodiment of the present invention provides a leakage protection circuit for an aircraft, where the leakage protection circuit is disposed on a zero line and a live line between a power supply and a load, and the leakage protection circuit includes: the input end of the current detection unit is respectively connected with the zero line and the live line and used for detecting the current difference between the zero line and the live line; the first switch unit is used for switching on the power supply of the relay or cutting off the power supply of the relay so that the relay switches on the connection between the live wire and the load when the power supply is cut off or switches off the connection between the live wire and the load when the power supply is switched on; the control unit is respectively connected with the current detection unit and the first switch unit and is used for controlling the first switch unit to be conducted to switch on the coil of the relay to supply power when the current difference value transmitted by the current detection unit is larger than a preset first current value, so that the relay is disconnected between the live wire and the load; and the output end of the second switch unit is respectively connected with the zero line and the live line through at least one first resistor, the input end of the second switch unit is respectively connected with a first power supply voltage and an external testing device so as to be used for receiving a testing signal sent by the external testing device, and the second switch unit is controlled to be switched on according to the testing signal so that the zero line and the live line are switched on through the at least one first resistor to enable the current difference value between the zero line and the live line to be larger than the preset first current value.
In the designed leakage protection circuit for the aviation aircraft, the second switch unit receives the test signal, so that at least one resistor on the output end of the second switch unit is connected between the zero line and the live line, so that a current difference value larger than a preset first current value is formed between the zero line and the live line, then whether the control unit controls the first switch unit to switch on the power supply of the relay after the current detection unit transmits the detected current difference value larger than the first current value to the control unit is determined, so that the connection between the live line and the load is cut off when the power supply of the relay is switched on to stop the power supply to supply the power to the load to determine whether the leakage protection circuit fails or not, if the leakage protection circuit does not cut off the power supply to supply the power to the load under the test condition, the leakage protection circuit is proved to have a fault, and therefore the self-checking function of the leakage protection, therefore, the problem that the safety is low when the leakage protection circuit in the existing power supply circuit fails is solved, the leakage protection circuit can timely find the leakage protection failure of the power supply circuit, and the safety of the power supply circuit is improved.
In an optional implementation manner of the first aspect, the second switch unit includes an encapsulated four-pin photoelectric relay, an input end of the encapsulated four-pin photoelectric relay includes a first connection terminal and a second connection terminal, an output end of the encapsulated four-pin photoelectric relay includes a third connection terminal and a fourth connection terminal, the first connection terminal is connected to a first power supply voltage, the second connection terminal is connected to the external test device, the third connection terminal is connected to the zero line through the at least one first resistor, and the fourth connection terminal is connected to the live line.
In an alternative embodiment of the first aspect, the first connection is connected to the first supply voltage via a second resistor.
In an optional implementation manner of the first aspect, the current detection unit includes a zero sequence current transformer, a primary side of the zero sequence current transformer is connected to the zero line and a primary side of the zero sequence current transformer are connected to the live line, and a secondary side of the zero sequence current transformer is connected to the control unit.
In an optional implementation manner of the first aspect, the control unit includes a ground fault circuit breaker controller, a VFB pin and a VREF pin of the ground fault circuit breaker controller are respectively connected to two ends of a secondary side of the zero sequence current transformer, an AmpOut pin of the ground fault circuit breaker controller is connected in parallel to the VFB pin, an SCR pin of the ground fault circuit breaker controller is connected to the first switch unit, the first switch unit is connected to the Neutral pin of the ground fault circuit breaker controller and then grounded, and a Line pin of the ground fault circuit breaker controller is connected to the second power supply voltage.
In an optional implementation manner of the first aspect, the first switch unit includes a thyristor, a control stage of the thyristor is connected to an SCR pin of the ground fault circuit breaker controller, a cathode of the thyristor is connected to a Neutral pin of the ground fault circuit breaker controller and then grounded, and an anode of the thyristor is connected to the relay.
In an optional implementation manner of the first aspect, the relay includes a coil and a contact set, the contact set includes a stationary contact, a normally closed movable contact and a normally open movable contact, one end of the coil is connected to an anode of the thyristor, the other end of the coil is connected to a third power supply voltage, the stationary contact is connected to the live wire, the normally closed movable contact is connected to the load, and the normally open movable contact is connected to a ground wire.
In a second aspect, an embodiment of the present invention provides a power supply circuit, where the power supply circuit includes the leakage protection circuit, the filter rectification circuit, the power factor correction circuit, and the inverter circuit as described in any one of the foregoing embodiments; the live wire input end and the zero line input end of the filter and rectifier circuit are respectively connected with the power supply, the live wire output end of the filter and rectifier circuit is connected with the live wire input end of the power factor correction circuit, the zero line output end of the filter and rectifier circuit is connected with the zero line input end of the power factor correction circuit, the live wire output end of the power factor correction circuit is connected with the live wire input end of the inverter circuit, the zero line output end of the power factor correction circuit is connected with the zero line input end of the inverter circuit, and the zero line and the live wire output end of the inverter circuit are connected with the load through the current detection unit in the leakage protection circuit.
In an optional implementation manner of the second aspect, the filter rectification circuit includes a filter circuit and a bridge rectification circuit, a live wire input end and a zero line input end of the filter circuit are connected to the power supply, the filter circuit is connected to the bridge rectification circuit, a live wire output end of the bridge rectification circuit is connected to a live wire input end of the power factor correction circuit, and a zero line output end of the bridge rectification circuit is connected to a zero line input end of the power factor correction circuit.
In an optional implementation manner of the second aspect, the power supply circuit further includes an output filter circuit, and the zero line output end and the live line output end of the inverter circuit are connected to a load through the output filter circuit, the current detection unit and the relay.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of a leakage protection circuit according to an embodiment of the present disclosure;
fig. 2 is a specific circuit diagram of a leakage protection circuit according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a power supply circuit according to an embodiment of the present disclosure;
fig. 4 is a specific circuit diagram of a filter rectifier circuit according to an embodiment of the present application.
Icon: 1-a first connection terminal; 2-a second connection terminal; 3-a third connecting terminal; 4-a fourth connection terminal; an L-fire line; an N-zero line; 10-a current detection unit; 101-zero sequence current transformer; 20-a relay; 201-a coil; 2021-stationary contact; 2022-normally closed moving contact; 2023-normally open moving contact; 30-a first switching unit; Q1-SCR; 40-a control unit; 401-ground fault circuit interrupter controller; 50-a second switching unit; 501-packaging a four-pin photoelectric relay; 200-a filter rectification circuit; 300-power factor correction circuit; 400-an inverter circuit; 500-an output filter circuit; r1 — first resistance; r2 — second resistance; r3 — third resistance; r4-fourth resistor; r5-fifth resistor; c1 — first capacitance; c2 — second capacitance; c3 — third capacitance; c4-fourth capacitance; c5 — fifth capacitance; c6 — sixth capacitance; c7 — seventh capacitance; c8 — eighth capacitance; c9 — ninth capacitance; c10 — tenth capacitance; c11 — eleventh capacitance; c12 — twelfth capacitance; c13 — thirteenth capacitor; c14 — fourteenth capacitance; l1-common mode inductance; l2 — first core inductance; l3 — second core inductance; d1-bridge rectifier; q2-triac; m1-dc sensor.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
First embodiment
As shown in fig. 1, an embodiment of the present application provides an earth leakage protection circuit for an aircraft, where the earth leakage protection circuit has a self-checking function, and the earth leakage protection circuit is disposed on a part between a power supply and a load and a live line L, and for example, may be specifically disposed on a zero line N and a live line of a power supply line on the aircraft, so as to detect whether an electric transmission line of the aircraft leaks electricity.
The utility model relates to a leakage protection circuit for aircraft, including current detection unit 10, relay 20, first switch unit 30, control unit 40 and second switch unit 50, the input of current detection unit 10 is connected with zero line N and live wire L above-mentioned respectively, the output of current detection unit 10 is connected with the control unit 40, the control unit 40 still is connected with the relay 20 through the first switch unit 30, the output of the second switch unit 50 is connected with zero line N and live wire L respectively through at least one first resistance R1, and as can be seen from figure 1, the junction that the output that the second switch unit 50 connects first resistance R1 and zero line N is before the junction that current detection unit 10 and zero line N, the junction that another output of the second switch unit 50 and live wire L is after the junction that current detection unit 10 and live wire L, the input terminals of the second switching unit 50 are connected to the first supply voltage and the external test device, respectively.
When the leakage protection circuit for the aircraft is in use, an external testing device can send a preset test signal to the second switch unit 50, and after the second switch unit 50 receives the preset test signal, the output end of the second switch unit 50 is closed, so that at least one first resistor R1 on the output end of the second switch unit 50 communicates the zero line N and the live line L, and a current difference larger than a preset first current value is generated. Specifically, the resistance value of the resistor can be adaptively selected according to the voltage between the zero line N and the live line L and the first current value required to be preset, so that the current difference value between the zero line N and the live line L after the at least one first resistor R1 is connected is greater than the first current value required to be preset.
On the premise, if the leakage protection circuit works normally, the current detection unit 10 detects a current difference value between the zero line N and the live line L connected to the current detection unit 10, and then transmits the current difference value to the control unit 40 through a line, after the control unit 40 receives the current difference value transmitted by the current detection unit 10, the current difference value is compared with a first current value preset in the control unit 40, at this time, it is determined that the current difference value is larger than the first current value, then the control unit 40 controls the first switch unit 30 to be switched on so as to switch on the power supply of the relay 20, and after the power supply of the relay 20 is switched on, the relay 20 switches off the connection between the live line L and the load so as to cut off the power supply of the power supply, so that the protection action is performed when the current difference value between the leakage zero line N and the live line L is too large (leakage); if the earth leakage protection circuit fails, the connection between the load and the live line L is not broken, and the earth leakage protection circuit does not perform the power supply cutoff operation.
According to the leakage protection circuit for the aviation aircraft, the second switch unit 50 is used for receiving the test signal, at least one resistor on the output end of the second switch unit 50 is connected between the zero line N and the live line L, a current difference value larger than a preset first current value is formed between the zero line N and the live line L, then whether the control unit 40 controls the first switch unit 30 to switch on the power supply of the relay 20 after the current difference value larger than the first current value is detected and transmitted to the control unit is determined, so that the connection between the live line L and the load is cut off when the power supply of the relay 20 is switched on is cut off to stop the power supply to supply the load to determine whether the leakage protection circuit has a fault or not, if the leakage protection circuit does not cut off the power supply to supply the load under the test condition, the leakage protection circuit has a fault, and therefore the self-checking function of the leakage protection is realized, therefore, the problem that the safety is low when the leakage protection circuit in the existing power supply circuit fails is solved, the leakage protection circuit can timely find the leakage protection failure of the power supply circuit, and the safety of the power supply circuit is improved.
In an alternative embodiment of the present embodiment, as shown in fig. 2, the second switch unit 50 includes a packaged four-pin type photo-electric relay 501, the input terminal of the packaged four-pin type photo-electric relay 501 includes a first connection terminal 1, a second connection terminal 2, a third connection terminal 3 and a fourth connection terminal 4, wherein the first connection terminal 1 and the second connection terminal 2 are the input terminal of the packaged four-pin type photo-electric relay 501, the third connection terminal 3 and the fourth connection terminal 4 are the output terminal of the packaged four-pin type photo-electric relay 501, the first connection terminal 1 is connected to a first power supply voltage, the second connection terminal 2 is connected to the external test device, the third connection terminal 3 is connected to the neutral wire N through the at least one resistor R1, and the fourth connection terminal 4 is connected to the live wire L. In addition, the second switching unit 50 may further include a second resistor R2, and the second resistor R2 may be disposed between the first connection terminal 1 and the first power supply voltage, for reducing an input voltage to the packaged four-pin type photo relay 501. Specifically, the packaged four-pin type photoelectric relay 501 may be a photoelectric relay of AQY214S type; the voltage value of the first power supply voltage may be 5V, the number of the at least one resistor R1 may be three, the resistances of the three resistors R1 may be 6.2K Ω, respectively, and the resistance of the second resistor R2 may be 1K Ω.
The third binding post 3 and the fourth binding post 4 of the photoelectric relay 501 output end of the encapsulation four needle type of above-mentioned design are normally open design, when the second binding post 2 of the photoelectric relay 501 of this encapsulation four needle type received the test signal that outside testing arrangement sent, the emitting diode among the photoelectric relay 501 of this encapsulation four needle type produced light energy and then shined on the output and made the third binding post 3 and the fourth binding post 4 switch-on of output end, and then made at least one resistance R1 connect between live wire L and zero line N.
In an alternative embodiment of the present embodiment, as shown in fig. 2, the current detecting unit 10 may be embodied as a zero sequence current transformer 101, a primary side of the zero sequence current transformer 101 is connected to the zero line N and the live line L, respectively, and a secondary side of the zero sequence current transformer 101 is connected to the control unit 40.
As shown in fig. 2, the control unit 40 may include a (Ground Fault Interrupter, GIF) Ground Fault circuit Interrupter controller 401, where the Ground Fault circuit Interrupter controller 401 includes a VFB pin, a VREF pin, an AmpOut pin, an SCR pin, a Neutral pin, and a Line pin, the VFB pin and the VREF pin are respectively connected to two ends of the secondary side of the zero sequence current transformer 101, and specifically, the VFB pin may be connected to one end of the secondary side of the zero sequence current transformer 101 through a third resistor R3; an AmpOut pin of the GIF controller is connected with a VFB pin in parallel, an SCR pin of the GIF controller is connected with a first switch unit 30, the first switch unit 30 is connected with a Neutral pin of the GIF controller and then grounded, and a Line pin of the GIF controller is connected with a second power supply voltage; as shown in fig. 2, a first capacitor C1 may be connected between the SCR pin and the Neutral pin, a second capacitor C2 may be connected between the Neutral pin and the Line pin, two ends of the secondary side of the zero sequence current transformer 101 may further be connected to a third capacitor C3, and the second supply voltage connected to the Line pin of the GIF controller may be 12V.
The control unit 40 designed above may preset a first current value in advance in the AO pin of the GIF controller, then receive a current difference value transmitted by the zero sequence current transformer 101 through the VFB pin and the VREF pin, and further control the level output of the SCR pin through the first current value preset in the AO pin and the current difference value received by the VFB pin and the VREF pin, for example, when the current difference value is greater than the preset first current value, the SCR pin drives the first switch unit 30 to be turned on, so that the connection between the live wire L and the load is disconnected when the relay 20 supplies power to be turned on, so as to stop the power supply output of the power supply.
In an alternative embodiment of this embodiment, as shown in fig. 2, the first switch unit 30 may include a thyristor Q1, the relay 20 includes a coil 201 and a contact group, the contact group includes a fixed contact 2021, a normally closed movable contact 2022 and a normally open movable contact 2023, a control stage of the thyristor Q1 is connected to an SCR pin of the ground fault circuit interrupter controller 401, a cathode of the thyristor Q1 is connected to a Neutral pin of the ground fault circuit interrupter controller 401 and then grounded, an anode of the thyristor Q1 is connected to one end of the coil 201 of the relay 20, the other end of the coil 201 is connected to a third power supply level, the fixed contact 2021 is connected to a live line L, the normally closed movable contact 2022 is connected to a load, and the normally open movable contact 2023 is connected to a ground line. Specifically, under a normal condition, the fixed contact 2021 is connected to the normally closed movable contact 2022, when a current difference is greater than a preset first current value, an SCR pin of the ground fault circuit breaker controller 401 sends a control signal to a control stage of the thyristor Q1, so as to control the conduction of the thyristor Q1, after the conduction of the thyristor Q1, a third power supply level is the power supply conduction of the coil 201 of the relay 20, the coil 201 of the relay 20 operates, so that the mutually connected fixed contact 2021 and the normally closed movable contact 2022 in the relay 20 are disconnected, the fixed contact 2021 is connected to the normally open movable contact 2023, and the live line L is connected to the ground line, so that the live line L and the neutral line N are not connected to the load at the same time, thereby cutting off the power supply output of the power supply. Of course, the normally closed moving contact 2022 of the relay 20 may also be connected to the neutral line N, so long as the neutral line N and the live line L are not connected to the load at the same time.
Second embodiment
The application provides a power supply circuit, this power supply circuit can be the power supply line of aircraft, as shown in fig. 3, this power supply circuit specifically can include the leakage protection circuit who is used for aircraft in the first embodiment, filter rectifier circuit 200, power factor correction circuit 300 and inverter circuit 400, filter rectifier circuit 200's live wire input end and zero line input end are connected with the power respectively, filter rectifier circuit 200's live wire output end is connected with power factor correction circuit 300's live wire input end, filter rectifier circuit 200's zero line output end is connected with power factor correction circuit 300's zero line input end, power factor correction circuit 300's live wire output end is connected with inverter circuit 400's live wire input end, power factor correction circuit 300's zero line output end is connected with inverter circuit 400's zero line input end, inverter circuit's zero line and live wire output end are connected with the load through current detection unit 10 and relay 20 in the leakage protection circuit.
Specifically, the input power supply in the power supply circuit designed above may be a 115V/400HZ power supply, and then sequentially filtered by the filter and rectifier circuit 200, specifically, a surge suppression circuit is used to filter the input power signal, absorb the surge outside the safety range of the aircraft, ensure the safe operation of the post-stage circuit, and extract the line noise and interference. After filtering, the direct current voltage of about 150V can be converted by rectification through a rectifying circuit, and then transmitted to the power factor correction circuit 300 for power factor correction, thereby realizing the maximization of the benefit of the electricity utilization of the airplane, further, after the power factor correction circuit 300 performs power factor correction, 190V high-voltage direct current is output, then the 190V high voltage dc is converted into 110V/60HZ ac by the inverter circuit 400 and then outputted to the load through the current detecting unit 10 and the relay 20, the above designed circuit, the current detecting unit 10 detects the current difference between the live line and the neutral line at the output terminal of the inverter circuit 400 in the whole process, and then, passes to the control unit 40 for control, and further determines whether to cut off the output of the power supply, the self-test of the leakage protection circuit is the same as the self-test in the first embodiment, and is not described herein again.
In an optional implementation manner of this embodiment, the power supply circuit may further include an output filter circuit 500, and the neutral and live output terminals of the inverter circuit 400 are connected to a load through the output filter circuit 500, the current detection unit 10 and the relay 20.
In an alternative embodiment of this embodiment, the filter rectification circuit 200 may specifically include a filter circuit and a bridge rectification circuit, which may specifically be circuits as shown in fig. 4, the filter circuit includes a fourth capacitor C4, a fifth capacitor C5, a sixth capacitor C6, a seventh capacitor C7, an eighth capacitor C8, a ninth capacitor C9, a tenth capacitor C10, an eleventh capacitor C11, a twelfth capacitor C12, a thirteenth capacitor C13 and a fourteenth capacitor C14, a common-mode inductor L1, a first core inductor L2, a second core inductor L3, a bridge rectifier D1, a fourth resistor R4, a fifth resistor R4, a triac Q4 and a dc sensor M4, as shown in the figure, the common-mode inductor L4 is connected between the input neutral line and the live line, the common-mode inductor L4 is connected to both ends of the C4 and both the first end of the C4 and the second end of the C4 in series connection with the second ends of the C4 and the second ends of the C4, a first end of C7 is connected to a first end of C5, a second end of C7 is connected to a first end of C6, a first end of C8 is connected to a first end of C7, a second end of C8 is connected to a second end of C7, a first end of L2 is connected to a first end of C8, a second end of L2 is connected to a first end of C9, a first end of L3 is connected to a second end of C8, a second end of L3 is connected to a second end of C9, a first end of C9 is connected to a first end of C10, a second end of C10 is connected to a first end of a bridge rectifier D1, a second end of a bridge rectifier D1 is connected to a first end of C10, a third end of a bridge rectifier D1 is a live output end of the filter rectifier circuit 200, and a fourth end of a bridge D1 is a neutral output end of the filter rectifier circuit 200; the second terminal of the C9 is connected to the first terminal of the triac Q2 and to the second terminal of the triac Q2 through a fourth resistor R4, the second terminal of the C10 is also connected to the first terminal of the triac Q2, the gate of the triac Q2 is connected to the second terminal of the C11 through a fifth resistor R5, the first terminal of the triac Q2 is connected to the first terminal of the C11, the first terminal of the C11 is connected to the first terminal of the C12, the second terminal of the C11 is connected to the second terminal of the C12, the first terminal of the C12 is connected to the VO + pin of the dc sensor M1; the second terminal of C12 is connected to VO-of the dc sensor M1, the VIN + pin of the dc sensor M1 is connected to the first terminal of C13, the VIN-pin of the dc sensor M1 is connected to the second terminal of C13, the first terminal of C13 is connected to the first terminal of C14, the second terminal of C13 is connected to the second terminal of C14, the first terminal of C14 is connected to a supply voltage, and the second terminal of C14 is connected to ground.
The filter circuit has a surge suppression function, can filter an input power signal, absorbs surges outside a safety range, ensures the safe operation of a post-stage circuit, and removes line noise and interference, and the bridge rectifier circuit converts alternating current into direct current.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one logical division, and there may be other divisions when actually implemented, and for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection of devices or units through some communication interfaces, and may be in an electrical, mechanical or other form.
In addition, units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
Furthermore, the functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
It should be noted that the functions, if implemented in the form of software functional modules and sold or used as independent products, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk.
In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. The utility model provides a leakage protection circuit for aviation aircraft, leakage protection circuit sets up on zero line and the fire line between power and load, its characterized in that, leakage protection circuit includes:
the input end of the current detection unit is respectively connected with the zero line and the live line and used for detecting the current difference between the zero line and the live line;
the first switch unit is used for switching on the power supply of the relay or cutting off the power supply of the relay so that the relay switches on the connection between the live wire and the load when the power supply is cut off or switches off the connection between the live wire and the load when the power supply is switched on;
the control unit is respectively connected with the current detection unit and the first switch unit and is used for controlling the first switch unit to be conducted to switch on the coil of the relay to supply power when the current difference value transmitted by the current detection unit is larger than a preset first current value, so that the relay is disconnected between the live wire and the load;
and the output end of the second switch unit is respectively connected with the zero line and the live line through at least one first resistor, the input end of the second switch unit is respectively connected with a first power supply voltage and an external testing device so as to be used for receiving a testing signal sent by the external testing device, and the second switch unit is controlled to be switched on according to the testing signal so that the zero line and the live line are switched on through the at least one first resistor to enable the current difference value between the zero line and the live line to be larger than the preset first current value.
2. The earth leakage protection circuit of claim 1, wherein the second switch unit comprises an encapsulated four-pin type photo relay, an input terminal of the encapsulated four-pin type photo relay comprises a first connection terminal and a second connection terminal, an output terminal of the encapsulated four-pin type photo relay comprises a third connection terminal and a fourth connection terminal, the first connection terminal is connected with a first power supply voltage, the second connection terminal is connected with the external test device, the third connection terminal is connected with the zero line through the at least one first resistor, and the fourth connection terminal is connected with the live line.
3. The leakage protection circuit of claim 2, wherein the first terminal is coupled to the first supply voltage via a second resistor.
4. The earth leakage protection circuit of claim 1, wherein the current detection unit comprises a zero sequence current transformer, a primary side of the zero sequence current transformer is connected to the neutral line and the live line, respectively, and a secondary side of the zero sequence current transformer is connected to the control unit.
5. The earth leakage protection circuit of claim 4, wherein the control unit comprises a ground fault circuit breaker controller, a VFB pin and a VREF pin of the ground fault circuit breaker controller are respectively connected with two ends of a secondary side of the zero sequence current transformer, an AmpOut pin of the ground fault circuit breaker controller is connected in parallel with the VFB pin, an SCR pin of the ground fault circuit breaker controller is connected with the first switch unit, the first switch unit is connected with a Neutral pin of the ground fault circuit breaker controller and then grounded, and a Line pin of the ground fault circuit breaker controller is connected with a second power supply voltage.
6. The earth leakage protection circuit of claim 5, wherein the first switch unit comprises a thyristor, a control stage of the thyristor is connected to an SCR pin of the ground fault circuit interrupter controller, a cathode of the thyristor is connected to a Neutral pin of the ground fault circuit interrupter controller and then grounded, and an anode of the thyristor is connected to the relay.
7. The earth leakage protection circuit of claim 6, wherein said relay comprises a coil and a contact set, said contact set comprising a stationary contact, a normally closed moving contact and a normally open moving contact, one end of said coil being connected to an anode of said thyristor, the other end of said coil being connected to a third supply voltage, said stationary contact being connected to said live wire, said normally closed moving contact being connected to said load, said normally open moving contact being connected to a ground wire.
8. A power supply circuit, characterized in that the power supply circuit comprises the earth leakage protection circuit, the filter rectification circuit, the power factor correction circuit and the inverter circuit according to any one of claims 1 to 7;
the live wire input end and the zero line input end of the filter and rectifier circuit are respectively connected with the power supply, the live wire output end of the filter and rectifier circuit is connected with the live wire input end of the power factor correction circuit, the zero line output end of the filter and rectifier circuit is connected with the zero line input end of the power factor correction circuit, the live wire output end of the power factor correction circuit is connected with the live wire input end of the inverter circuit, the zero line output end of the power factor correction circuit is connected with the zero line input end of the inverter circuit, and the zero line and the live wire output end of the inverter circuit are connected with the load through the current detection unit in the leakage protection circuit.
9. The power supply circuit according to claim 8, wherein the filter rectification circuit comprises a filter circuit and a bridge rectification circuit, the live wire input end and the zero line input end of the filter circuit are connected to the power supply, the filter circuit is connected to the bridge rectification circuit, the live wire output end of the bridge rectification circuit is connected to the live wire input end of the power factor correction circuit, and the zero line output end of the bridge rectification circuit is connected to the zero line input end of the power factor correction circuit.
10. The power supply circuit of claim 8, further comprising an output filter circuit, wherein the neutral and live outputs of the inverter circuit are connected to a load through the output filter circuit, the current detection unit and the relay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010773151.6A CN111799755A (en) | 2020-08-04 | 2020-08-04 | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010773151.6A CN111799755A (en) | 2020-08-04 | 2020-08-04 | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111799755A true CN111799755A (en) | 2020-10-20 |
Family
ID=72828925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010773151.6A Pending CN111799755A (en) | 2020-08-04 | 2020-08-04 | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111799755A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114779118A (en) * | 2022-04-20 | 2022-07-22 | 中国第一汽车股份有限公司 | Electric leakage detection device, electric leakage detection method and automobile charging equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013020274A1 (en) * | 2011-08-09 | 2013-02-14 | 深圳市良辉科技有限公司 | Safe quick-break leakage protector |
| CN203722205U (en) * | 2014-02-20 | 2014-07-16 | 厦门振泰成科技有限公司 | Overvoltage and electric leakage protection circuit |
| WO2016021088A1 (en) * | 2014-08-07 | 2016-02-11 | パナソニックＩｐマネジメント株式会社 | Electric leakage protection device and feed control device |
| CN106451329A (en) * | 2016-07-19 | 2017-02-22 | 中山市开普电器有限公司 | Leakage protection apparatus |
| CN212231077U (en) * | 2020-08-04 | 2020-12-25 | 成都锐能科技有限公司 | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof |
-
2020
- 2020-08-04 CN CN202010773151.6A patent/CN111799755A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013020274A1 (en) * | 2011-08-09 | 2013-02-14 | 深圳市良辉科技有限公司 | Safe quick-break leakage protector |
| CN203722205U (en) * | 2014-02-20 | 2014-07-16 | 厦门振泰成科技有限公司 | Overvoltage and electric leakage protection circuit |
| WO2016021088A1 (en) * | 2014-08-07 | 2016-02-11 | パナソニックＩｐマネジメント株式会社 | Electric leakage protection device and feed control device |
| CN106451329A (en) * | 2016-07-19 | 2017-02-22 | 中山市开普电器有限公司 | Leakage protection apparatus |
| CN212231077U (en) * | 2020-08-04 | 2020-12-25 | 成都锐能科技有限公司 | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114779118A (en) * | 2022-04-20 | 2022-07-22 | 中国第一汽车股份有限公司 | Electric leakage detection device, electric leakage detection method and automobile charging equipment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201724988U (en) | Input phase failure detector for power unit of high-voltage frequency converter | |
| CN201724975U (en) | Brown out detection circuit of electric meter system | |
| CN112019039A (en) | Power interface circuit with high-grade surge protection and high EMI performance | |
| CN104283441A (en) | Direct-current power source and direct-current power source providing method | |
| CN109188278B (en) | Three-phase unbalance detection circuit and system | |
| CN104426128B (en) | Broken neutral line detects circuit and corresponding residual current circuit breaker | |
| CN201331555Y (en) | Power unit input open-phase detector of high-voltage inverter | |
| CN101447667A (en) | High voltage transducer power unit input phase loss detector | |
| CN212231077U (en) | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof | |
| CN108110728A (en) | Protection switch | |
| CN111799755A (en) | A earth leakage protection circuit for aviation aircraft and power supply circuit thereof | |
| CN202524057U (en) | Earth fault protection device of locomotive auxiliary power system and electric locomotive | |
| CN112134267A (en) | Surge protection circuit, electromagnetic heating circuit and household appliance | |
| CN105896563A (en) | Zero-crossing trigger control circuit for anti-parallel thyristor split-phase switched capacitor | |
| CN203406776U (en) | DC power supply | |
| CN203439864U (en) | Elevator control cabinet | |
| CN214506872U (en) | Low-voltage starting high-voltage anti-surge current circuit and switching power supply | |
| CN209748404U (en) | Three-phase rectification protection circuit with input surge current suppression function | |
| CN210123943U (en) | Alternating current channeling fault isolation module of direct current system of transformer substation | |
| CN104418194A (en) | Elevator control cabinet | |
| CN209217694U (en) | A kind of low-voltage distribution transformer load distribution device with protective device | |
| CN106026017A (en) | Leakage breaker with over-voltage protection and under-voltage protection | |
| CN112532085A (en) | Power supply circuit and power adapter | |
| CN217901869U (en) | Alternating current-direct current driving voltage detection circuit | |
| CN204794015U (en) | Electric leakage circuit breaker |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |