CN112511121B - Airplane power grid differential pressure switching-on operation circuit - Google Patents
Airplane power grid differential pressure switching-on operation circuit Download PDFInfo
- Publication number
- CN112511121B CN112511121B CN202011462686.8A CN202011462686A CN112511121B CN 112511121 B CN112511121 B CN 112511121B CN 202011462686 A CN202011462686 A CN 202011462686A CN 112511121 B CN112511121 B CN 112511121B
- Authority
- CN
- China
- Prior art keywords
- generator
- voltage
- operational amplifier
- resistor
- triode
- 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.)
- Active
Links
Classifications
-
- H—ELECTRICITY
- H03—ELECTRONIC CIRCUITRY
- H03F—AMPLIFIERS
- H03F3/00—Amplifiers with only discharge tubes or only semiconductor devices as amplifying elements
- H03F3/45—Differential amplifiers
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/10—Measuring sum, difference or ratio
-
- 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
- H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
- H02J3/388—Islanding, i.e. disconnection of local power supply from the network
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The invention discloses an aircraft power grid differential pressure switching-on operation circuit, which is added between a generator and a junction voltage and comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein when the differential pressure switching-on condition is met, the operation circuit controls a generator main contactor to be switched on and a generator is integrated into a power grid by comparing the junction voltage with the voltage of an output end of the generator; when the voltage value output by the generator can not meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the disconnection of the main contactor of the generator, and the generator exits from the power grid. According to the aircraft power grid differential pressure switching-on operation circuit, grid connection and grid withdrawal are selected according to the actual working condition of the generator, automatic switching of the grid connection and the grid withdrawal of the generator is achieved, pilot judgment selection is not needed, flight is prevented from being influenced due to manual misoperation or other reasons, and the stability of an aircraft is improved.
Description
Technical Field
The invention relates to the technical field of aircraft electrical systems, in particular to an aircraft power grid differential pressure switching-on operation circuit.
Background
The aircraft power system is generally designed with a main power supply, a secondary power supply, an auxiliary power supply, a backup power supply and an emergency power supply according to the power source. The main power system is an engine-driven generator system that provides all of the power during normal flight conditions of the aircraft. As a core device in the main power supply system, a generator, the time for the generator to be incorporated into the power grid and to exit the power grid during normal operation is very important, and the stability of the main power supply system is directly affected in early or late periods. When the output voltage value of the generator can not meet the requirement, a pilot can judge the state of the aircraft according to the alarm, and can select to cut off the power supply line of the generator and power the generator by other power supplies (such as an auxiliary power supply, a backup power supply and an emergency power supply), but the design mode has certain defects, and the fault of the alarm line and the artificial misoperation can possibly lead to unsatisfactory treatment effect, so that the flight stability is influenced.
Disclosure of Invention
The invention aims to solve the technical problem that the effect is not ideal due to the manual operation of the existing aircraft network sending and network returning, and provides an aircraft power grid differential pressure switching-on operation circuit, which enables a generator to be integrated into a power grid when the output voltage of the generator meets the requirement; when the output voltage of the generator is too low, the generator is led to exit the power grid, grid connection and grid withdrawal are selected according to the actual working condition of the generator, automatic switching of the grid connection and the grid withdrawal of the generator is realized, pilot judgment and selection are not needed, flight is prevented from being influenced due to manual misoperation or other reasons, and the stability of the aircraft is improved.
In order to solve the technical problems, the invention provides an aircraft power grid differential voltage switching-on operation circuit, which comprises a first operation amplifier, a second operation amplifier, a first triode and a second triode, wherein the power supply ends of the first operation amplifier and the second operation amplifier are connected with the positive end voltage of a generator, and the grounding ends of the first operation amplifier and the second operation amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the junction voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with the reverse end of the second operational amplifier in series with a diode A400 and a resistor R106, the same-direction end of the second operational amplifier is connected with a resistor R105 in series and grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitter of the first triode is grounded, the collector series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector of the second triode is connected with the main contactor, and the emitter of the second triode is connected with the generator switch signal.
In an alternative embodiment of the present application, the generator positive terminal voltage is connected in series with a ground terminal resistor R102 and a zener diode V200.
In an alternative embodiment of the present application, a voltage stabilizing circuit is disposed between the voltage stabilizing tube V200 and the resistor R101.
In an alternative embodiment of the present application, the voltage stabilizing circuit includes a rectifying tube V201 and a resistor R103 connected in parallel.
In an alternative embodiment of the present application, an adjustable resistor R104 is provided between the generator positive terminal voltage and the resistor R100.
The aircraft power grid differential voltage switching-on operation circuit comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein power supply ends of the first operational amplifier and the second operational amplifier are connected with positive end voltage of a generator, and grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the junction voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with the reverse end of the second operational amplifier in series with a diode A400 and a resistor R106, the same-direction end of the second operational amplifier is connected with a resistor R105 in series and grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitter of the first triode is grounded, the collector series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector of the second triode is connected with the main contactor, and the emitter of the second triode is connected with the generator switch signal.
According to the aircraft power grid differential pressure switching-on operation circuit, an operation circuit is added between a generator and a junction voltage, the junction voltage is compared with the voltage of an output end of the generator, and when a differential pressure switching-on condition is met, the operation circuit controls a main contactor of the generator to be switched on, and the generator is integrated into a power grid; when the voltage value output by the generator can not meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the disconnection of the main contactor of the generator, and the generator exits from the power grid. The normal operation of the aircraft power supply system is ensured through the control of the operation circuit, the circuit design can select grid connection and grid withdrawal according to the actual working condition of the generator, the pilot is not required to judge and select, the influence on the flight due to manual misoperation or other reasons is avoided, the stability of the aircraft power supply system can be greatly improved, and the flight safety is ensured.
Drawings
For a clearer description of embodiments of the invention or of the prior art, the drawings that are used in the description of the embodiments or of the prior art will be briefly described, it being apparent that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from them without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of an aircraft power grid differential voltage switching-on operation circuit according to an embodiment of the present application.
Detailed Description
In order to better understand the aspects of the present invention, the present invention will be described in further detail with reference to the accompanying drawings and detailed description. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
As shown in fig. 1, fig. 1 is a schematic diagram of an aircraft power grid differential voltage switching-on operation circuit provided in an embodiment of the present application, where the aircraft power grid differential voltage switching-on operation circuit includes: the power supply ends of the first operational amplifier and the second operational amplifier are connected with the voltage of the positive end of the generator, and the grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the junction voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with the reverse end of the second operational amplifier in series with a diode A400 and a resistor R106, the same-direction end of the second operational amplifier is connected with a resistor R105 in series and grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitter of the first triode is grounded, the collector series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector of the second triode is connected with the main contactor, and the emitter of the second triode is connected with the generator switch signal.
The aircraft power grid voltage difference in this embodiment switches on the operational circuit, has increased an operational circuit between generator and pivot voltage, and this circuit comprises operational amplifier, resistance, voltage regulator tube, rectifier tube, triode etc.. By comparing the pivot voltage with the voltage of the output end of the generator, when the voltage difference connection condition is met, the operation circuit controls the main contactor of the generator to be connected, and the generator is integrated into a power grid; when the voltage value output by the generator can not meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the disconnection of the main contactor of the generator, and the generator exits from the power grid. The circuit design can select grid connection and grid withdrawal according to the actual working condition of the generator, pilot judgment selection is not needed, and flight is prevented from being influenced by manual misoperation or other reasons.
Further, in one embodiment of the present application, the positive terminal voltage of the generator is stabilized with the resistor R102 and the zener diode V200 connected in series with the ground terminal, so as to obtain the preset reference voltage.
Furthermore, the junction voltage is limited by the resistor R101 and then connected to the +end of the N300, so as to eliminate the influence of the junction voltage variation, and to make the (+) voltage at the same direction end of the N300 relatively stable, a voltage stabilizing circuit is arranged between the voltage stabilizing tube V200 and the resistor R101, so that the voltage value is stabilized within a certain range.
The voltage stabilizing circuit is not particularly limited, and may be a rectifying tube V201 and a resistor R103 connected in parallel, where the resistor R103 and the rectifying tube V201 stabilize the voltage value within a certain range so as to eliminate the influence of the change of the junction voltage.
In another embodiment of the present application, the output voltage of the generator is limited by the resistor R100 and then connected to the reverse end of the first operational amplifier, an adjustable resistor R104 is disposed between the positive end voltage of the generator and the resistor R100, and the adjustable resistor R104 is a shunt circuit, so that the reverse end voltage of the first operational amplifier can be adjusted in advance, the reverse end voltage is still higher than the same-direction end voltage even if the normal voltage value of the generator is 0.2-0.5V lower than the normal value of the junction voltage, the output of the first operational amplifier is turned over, and the output high potential is changed into the low potential (the differential pressure signal is valid).
Specifically, as shown in fig. 1, the operational amplifier N300 outputs a high potential when the reverse terminal (-) voltage is lower than the same-direction terminal (+) voltage, and outputs a low potential (signal valid) when the reverse terminal (-) voltage is higher than the same-direction terminal (+) voltage. The working power supplies of the operational amplifiers N300 and N301 are all from the positive end voltage C of the generator, the working power supplies are grounded from F to F after passing through 1 hole and 2 holes of the operational amplifiers N300 and N301, and the working power supplies are divided by the resistor R102 and stabilized by the voltage stabilizing tube V200. The main contactor on control circuit is composed of an operational amplifier N301 and switching circuits of triodes B500 and B501.
The junction voltage is input from B, and is connected to the plus end of N300 after being limited by a resistor R101, and the resistor R103 and a rectifying tube V201 stabilize the voltage value within a certain range so as to eliminate the influence of the junction voltage change and ensure that the (+) voltage at the same direction end of N300 is relatively stable. The output voltage of the generator is input by A, and is connected to the reverse end (-) of the operational amplifier N300 after being limited by the resistor R100, the adjustable resistor R104 is a shunt circuit, and the voltage of the reverse end (-) of the N300 can be adjusted in advance, so that the voltage of the reverse end (-) is still higher than the voltage of the same direction end (+) even if the normal voltage value of the generator output is 0.2-0.5V lower than the normal value of the junction voltage, the output of the operational amplifier N300 is overturned, and the output high potential is changed into low potential (the differential pressure signal is effective).
The differential pressure signal output by the operational amplifier N300 is connected to the reverse end (-) of the operational amplifier N301 through the diode A400 and the resistor R106, and the same-direction end (+) of the operational amplifier N301 is connected to a preset reference voltage regulated by the resistor R105. When the voltage at the reverse end (-) of the N301 is lower than the same-direction end (+), the operational amplifier outputs high potential, the triode B500 is operated through the rectifying tube V202 and the resistor R107, if the generator switching signal is switched on (E input), the base electrode of the B501 is provided with current after the collector current of the B500 passes through the resistor R108, the B501 is operated, the voltage input at the E point outputs a main contactor operation signal through the B501 and the K, the main contactor is operated, and the generator is integrated into a power grid.
When the voltage difference signal is invalid (i.e. the operational amplifier N300 outputs a high potential), the voltage at the reverse end (-) of the operational amplifier N301 is higher than the preset voltage value at the same direction end (+), a low potential is output at this time, the triode B500 is cut off, the triode B501 is cut off, the voltage input at the E point can not reach K through the triode B501 and output a working signal of the main contactor, the main contactor does not work, and the generator exits from the power grid.
According to the aircraft power grid voltage difference switching-on operation circuit, when the output voltage of the generator is higher than the hub voltage and lower than a preset voltage value, the generator can be combined into a power grid to work, and otherwise, the power grid is withdrawn. The circuit design greatly improves the stability of the aircraft power supply system, and avoids the influence on the normal operation of the aircraft power supply system due to human misoperation, line faults and other reasons.
It should be noted that, in this document, the terms center, upper, lower, left, right, vertical, horizontal, inner, outer, etc. refer to an azimuth or a positional relationship based on that shown in the drawings, or an azimuth or a positional relationship in which the inventive product is conventionally put in use, merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal," "vertical," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
It should also be noted that, unless explicitly stated and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
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. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements is inherent to. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element. In addition, the parts of the above technical solutions provided in the embodiments of the present application, which are consistent with the implementation principles of the corresponding technical solutions in the prior art, are not described in detail, so that redundant descriptions are avoided.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present invention and its core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.
Claims (5)
1. An aircraft power grid differential pressure switching-on operation circuit is characterized in that: the power supply end of the first operational amplifier and the power supply end of the second operational amplifier are connected with the positive end voltage of the generator, and the grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the junction voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with the reverse end of the second operational amplifier in series with a diode A400 and a resistor R106, the same-direction end of the second operational amplifier is connected with a resistor R105 in series and grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitter of the first triode is grounded, the collector series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector of the second triode is connected with the main contactor, and the emitter of the second triode is connected with the generator switch signal.
2. An aircraft power grid voltage difference switching-on operation circuit according to claim 1, wherein the generator positive terminal voltage and ground terminal series resistor R102 and zener diode V200.
3. An aircraft power grid voltage difference switching-on operation circuit according to claim 2, wherein a voltage stabilizing circuit is arranged between the voltage stabilizing diode V200 and the resistor R101.
4. A voltage-difference-on operation circuit for an aircraft power grid according to claim 3, wherein the voltage stabilizing circuit comprises a rectifying tube V201 and a resistor R103 connected in parallel.
5. An aircraft power grid voltage difference switching-on operation circuit according to claim 1, wherein an adjustable resistor R104 is arranged between the generator positive terminal voltage and the resistor R100.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462686.8A CN112511121B (en) | 2020-12-12 | 2020-12-12 | Airplane power grid differential pressure switching-on operation circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462686.8A CN112511121B (en) | 2020-12-12 | 2020-12-12 | Airplane power grid differential pressure switching-on operation circuit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112511121A CN112511121A (en) | 2021-03-16 |
| CN112511121B true CN112511121B (en) | 2024-04-02 |
Family
ID=74972546
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011462686.8A Active CN112511121B (en) | 2020-12-12 | 2020-12-12 | Airplane power grid differential pressure switching-on operation circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112511121B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4078194A (en) * | 1976-04-28 | 1978-03-07 | Micro Communications Corporation | Arrangement for controlling the speed of a motor |
| EP2765665A2 (en) * | 2013-02-09 | 2014-08-13 | Doepke Schaltgeräte GmbH | Device for detecting differential currents, in particular of mixed currents of smoothed direct current and alternating currents |
| CN204597772U (en) * | 2015-05-22 | 2015-08-26 | 天水华天微电子股份有限公司 | Airborne DC power supply anti-surge circuit |
| CN106093579A (en) * | 2016-06-08 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of electrically combining controls combination current limiting safeguard resistor method of testing |
| CN107591835A (en) * | 2017-08-07 | 2018-01-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Main variable frequency alternating current power source is thrown and moves back power grid control method |
| CN109347060A (en) * | 2018-11-20 | 2019-02-15 | 陕西航空电气有限责任公司 | A kind of differential error protection control method of aviation power system |
| CN208730923U (en) * | 2018-07-25 | 2019-04-12 | 成都市智航飞科科技有限责任公司 | A kind of instruction control box |
| CN209982448U (en) * | 2019-06-12 | 2020-01-21 | 广州韵驰电子有限公司 | Operational amplifier circuit in power amplifier protection circuit |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8053925B2 (en) * | 2009-02-04 | 2011-11-08 | Astronics Advanced Electronic Systems Corp. | Modulation monitor and control |
| FR2996964B1 (en) * | 2012-10-11 | 2016-02-05 | Airbus Operations Sas | METHOD AND DEVICE FOR PROTECTING AN ELECTRICAL NETWORK FOR AN AIRCRAFT |
-
2020
- 2020-12-12 CN CN202011462686.8A patent/CN112511121B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4078194A (en) * | 1976-04-28 | 1978-03-07 | Micro Communications Corporation | Arrangement for controlling the speed of a motor |
| EP2765665A2 (en) * | 2013-02-09 | 2014-08-13 | Doepke Schaltgeräte GmbH | Device for detecting differential currents, in particular of mixed currents of smoothed direct current and alternating currents |
| CN204597772U (en) * | 2015-05-22 | 2015-08-26 | 天水华天微电子股份有限公司 | Airborne DC power supply anti-surge circuit |
| CN106093579A (en) * | 2016-06-08 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of electrically combining controls combination current limiting safeguard resistor method of testing |
| CN107591835A (en) * | 2017-08-07 | 2018-01-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Main variable frequency alternating current power source is thrown and moves back power grid control method |
| CN208730923U (en) * | 2018-07-25 | 2019-04-12 | 成都市智航飞科科技有限责任公司 | A kind of instruction control box |
| CN109347060A (en) * | 2018-11-20 | 2019-02-15 | 陕西航空电气有限责任公司 | A kind of differential error protection control method of aviation power system |
| CN209982448U (en) * | 2019-06-12 | 2020-01-21 | 广州韵驰电子有限公司 | Operational amplifier circuit in power amplifier protection circuit |
Non-Patent Citations (2)
| Title |
|---|
| Variable sampling frequency in iterative learning current Control for Shunt Active Filter in aircraft power systems;Pericle Zanchetta等;《2011 IEEE Energy Conversion Congress and Exposition》;20111031;3528-3534 * |
| 浅谈某型飞机断电告警电路的改进;丁德鹏;《航空装备维修技术及应用研讨会论文集》;20151011;625-632 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112511121A (en) | 2021-03-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| DE69503627T2 (en) | DETECTOR FOR MONITORING THE EARTH CONNECTION OF AN ELECTRICAL DEVICE | |
| EP2719043B1 (en) | Fault identification and location in a power supply line which is fed from one side | |
| DE602004002588T2 (en) | PROCESS AND SAFETY DEVICE FOR ERDF PROTECTION | |
| DE102016223264A1 (en) | breaker | |
| DE2556734A1 (en) | EMERGENCY LIGHTING SYSTEM WITH INVERTER WITH HIGH EFFICIENCY | |
| CN108983041B (en) | Device for detecting faults in electrical lines | |
| CN107231108B (en) | A kind of generator of nuclear power station excitation regulation device and method | |
| DE69032123T2 (en) | Circuit for monitoring the energy supply | |
| CN112511121B (en) | Airplane power grid differential pressure switching-on operation circuit | |
| DE60219066T2 (en) | PROGRAMMABLE SYSTEM FOR VOLTAGE STABILIZATION AND CONTROL IN PARTICULAR FOR IMPROVED MANAGEMENT OF LIGHTING UNITS WITH FLUORESCENT LAMPS AND SIMILAR | |
| DE69509492T2 (en) | Monitoring and control device for an electrical system | |
| CN218633353U (en) | Generator and grid-connected device | |
| CN207652028U (en) | A kind of switching power circuit and its protection circuit | |
| CN213125848U (en) | Voltage conversion circuit with current limiting function, power supply equipment and aircraft | |
| CN213240354U (en) | Voltage conversion circuit with zero-ohm resistor, power supply equipment and aircraft | |
| CN203931986U (en) | With the circuit breaker of overvoltage/undervoltage protection and auto-reset function | |
| CN113820625A (en) | Circuit for detecting leakage current of alternating current solid-state relay | |
| CN217332600U (en) | Current sampling circuit, power control circuit and power supply system | |
| CN106526361B (en) | Three-phase driving plate fault determining circuit and three-phase driving plate | |
| CN219657794U (en) | Insulation detection device of direct current system | |
| CN217007453U (en) | A kind of voltage rapid detection circuit and electronic equipment | |
| CN115903978B (en) | A voltage stabilizing circuit suitable for wide input voltage | |
| CN216697034U (en) | Input/output detection control system | |
| CN217739384U (en) | Voltage-stabilizing diode array reliability test circuit | |
| CN218940767U (en) | Power supply switching system and power supply |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |