CN114336525A - Solid-state power distribution controller and power distribution method for unmanned aerial vehicle - Google Patents
Solid-state power distribution controller and power distribution method for unmanned aerial vehicle Download PDFInfo
- Publication number
- CN114336525A CN114336525A CN202111522770.9A CN202111522770A CN114336525A CN 114336525 A CN114336525 A CN 114336525A CN 202111522770 A CN202111522770 A CN 202111522770A CN 114336525 A CN114336525 A CN 114336525A
- Authority
- CN
- China
- Prior art keywords
- solid
- power distribution
- state
- equipment
- bus bar
- 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
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000006870 function Effects 0.000 claims abstract description 13
- 238000011084 recovery Methods 0.000 claims abstract description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 21
- 239000007787 solid Substances 0.000 claims description 15
- 230000000903 blocking effect Effects 0.000 claims description 7
- 238000012544 monitoring process Methods 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 2
- 238000005259 measurement Methods 0.000 claims description 2
- 239000000126 substance Substances 0.000 claims description 2
- 230000010354 integration Effects 0.000 abstract description 3
- 238000012545 processing Methods 0.000 abstract description 3
- 239000010705 motor oil Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 8
- 238000001514 detection method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000004377 microelectronic Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011897 real-time detection Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Landscapes
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention relates to an unmanned aerial vehicle solid-state power distribution controller and a power distribution method. The solid-state power distribution controller is core equipment of a certain unmanned aerial vehicle electrical system, provides direct-current power supply for each direct-current electric equipment on the unmanned aerial vehicle, and controls an engine oil pump, parking equipment, recovery equipment and the like. The solid-state distribution board integrates a plurality of paths of solid-state switches, is a core device of power distribution, and realizes power distribution and power utilization information feedback of power utilization equipment. The computer board integrates DSP, a memory, an interface circuit and the like, realizes a power distribution logic function through power supply management software, controls power on/off of electric equipment through a power distribution instruction, and has functions of storing, processing and communicating externally of electric information. The invention improves the reliability, the testability and the integration of the solid-state power distribution controller of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle electrical systems, in particular to an unmanned aerial vehicle power distribution system.
Background
The unmanned aerial vehicle electrical system generally comprises a power supply system, a power distribution system and electric equipment, wherein the power distribution system comprises power distribution equipment and a power distribution network.
The transmission of electric power on the unmanned aerial vehicle is realized by various block terminal and through distribution network. Automatic air switches, fuses, and relays are typically used to perform control and protection functions. The automatic air switch needs manual reset after realizing the protection function, and the fuse is disposable and needs to be replaced after action. The automatic air switch and the relay adopt contacts to complete on-off control of circuits, an operating mechanism is complex, reliability is low, workload of daily maintenance is large, and online monitoring is not facilitated.
Based on this, the unmanned aerial vehicle solid state power distribution controller who we developed adopts solid state switch according to unmanned aerial vehicle power consumption characteristics, realizes each direct current consumer distribution control on the unmanned aerial vehicle. The solid-state switch can realize load current detection, switch state monitoring, overload and short-circuit protection and the like, has the advantages of no contact, high reliability, small volume and easy computer control and on-line monitoring.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide a power distribution method based on a solid-state switch for an unmanned aerial vehicle, which improves the integration level of a power distribution system of the unmanned aerial vehicle, and has a compact structure and high reliability.
In order to achieve the effect, the invention provides an unmanned aerial vehicle solid-state power distribution controller, which comprises a bus bar, a solid-state power distribution board, a computer board and an aviation electric connector; wherein the content of the first and second substances,
the input end of the power distribution controller is respectively connected to an unmanned airborne generator and a storage battery pack through a solid-state power distribution board, the unmanned airborne generator is connected with a first bus bar of the solid-state power distribution board, and the storage battery pack is connected with a second bus bar of the solid-state power distribution board;
the solid-state power distribution board is connected with a first bus bar, the first bus bar is connected with all the electric equipment and used for executing power supply and monitoring functions and connecting the output power supply of the unmanned aerial vehicle-mounted generator to each electric equipment; the solid-state power distribution board is connected with a second bus bar, the second bus bar is connected with the task equipment, and the instruction of the flight control computer is executed to realize the on-off control of the task equipment;
the first bus bar and the second bus bar are communicated through the blocking diode.
Further, the electric equipment comprises task equipment and key electric equipment, wherein the task equipment comprises an engine stop, an oil pump and recovery equipment; the key electric equipment comprises a flight control computer, a flight control sensor, a steering engine and a measurement and control terminal.
Further, the solid-state power distribution board comprises a plurality of solid-state switches, wherein a part of the solid-state switches are used for executing a power supply function, and the bus bar is switched on through the solid-state switches to supply power to each electric device; and the rest solid-state switches are solid-state switches of the task equipment, and the task equipment is controlled according to the instruction of the flight control computer.
Furthermore, a control unit is arranged on the flight control computer, and the control unit comprises a DSP, a memory and an interface circuit; the DSP is used for realizing the logic function of power distribution control; the memory is used for storing parameters of instruction states, load currents, switch states and fault information, and the interface circuit comprises a communication interface and a switching value input and output circuit.
As a preferred embodiment of the present application, a dual-redundancy solid-state switch is used to supply power to the electric equipment, and simultaneously, the state information of the electric equipment is stored.
Based on the control system, the application also provides an unmanned aerial vehicle electrical control method, which specifically comprises the following steps:
detecting working currents of all electric equipment on the unmanned aerial vehicle, comparing the real-time currents with historical data stored in a database, and determining whether the working state of the electric equipment is normal or not;
detecting the voltage of the unmanned aerial vehicle-mounted generator, and when the voltage is within a preset working voltage range, switching on a solid-state switch GTF to connect the generator with a first bus bar, so that the electric equipment obtains direct-current electric energy through the first bus bar; when the voltage of the unmanned aerial vehicle-mounted motor is not within the preset working voltage range, the GTF is turned off to enable the generator to be separated from the first bus bar;
when the generator takes place voltage excessive pressure, undervoltage and takes place, solid-state switch GTF turns off and makes unmanned aerial vehicle machine carry generator break away from first busbar, and the consumer is disconnected simultaneously, adopts the battery power supply, provides the electric energy to key consumer through the busbar, guarantees to provide safe power supply time of returning voyage.
Further, the electric equipment comprises key electric equipment and task equipment, wherein the task equipment comprises a task load, heating equipment and a navigation lamp; the key electric equipment comprises a flight control computer, a flight control sensor, a steering engine, recovery equipment and data link equipment.
The solid-state power distribution controller has the advantages that the power supply reliability and testability of the unmanned aerial vehicle are improved, the integration level is high, the size is small, the weight is light, and the real-time detection and storage of power distribution data are realized.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the present invention will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without inventive labor.
FIG. 1 is a functional block diagram of a solid state switch;
FIG. 2 is a power control schematic block diagram of a bus bar, solid state switch, computer board and powered device;
FIG. 3 is a schematic block diagram of a solid state switch based generator, battery and bus bar power supply;
FIG. 4 is a functional block diagram of a computer board embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In embodiment 1, fig. 1 is a schematic block diagram of a solid-state switch, which includes circuits such as a current-voltage detection module, a temperature detection module, a load current feedback output module, a logic module, a driving module, and a MOSFET, and is capable of detecting a power supply voltage, a load current, and a temperature, and has a load current output signal terminal, an on-off control signal input terminal, a power supply input terminal, and a load output terminal. The MOSFET is used as a non-contact switch component with the capability of controlling the on-off of power, and has the advantages of high switching speed, no electric arc, small electromagnetic interference and high reliability. The current, voltage and temperature detection circuit sends detection signals to the logic module, and on-off control signals are sent to the logic module and then connected to the MOSFET through the driving module. The current feedback output module converts the load current into a load current source with a certain proportion, and sends the load current source to the control unit on the computer board so as to analyze the load current. The solid-state switch is an intelligent switch component integrating the on-off function of the relay and the circuit protection function of the circuit breaker, and the development of the relay and the circuit breaker from a contact switch circuit to a non-contact solid-state electronic switch is realized. The method has the advantages that the state of the solid-state switch, the voltage and the current of the electric equipment can be fed back to the computer board for processing in real time, and the testability is greatly improved.
Embodiment 2, fig. 2 is a power supply control schematic block diagram of a bus bar, a solid state switch, a computer board and a powered device. The bus bar is one of the bearing parts of the distribution current, an onboard power supply (a generator and a storage battery) distributes power to the electric equipment through the bus bar and the solid-state switch, and the solid-state switch receives a computer board instruction signal to realize the connection or disconnection of the bus bar to the electric equipment. The two solid-state switches GTa and GTb are connected in parallel to work to provide dual-redundancy power supply for the electric equipment, the instruction A and the instruction B from the computer board respectively control the two solid-state switches, and the state signals and the current feedback signals of the solid-state switches are respectively transmitted to the computer board for storage and processing. The circuit improves the reliability of power supply and the flexibility of power distribution, and can monitor the power utilization state in real time.
Embodiment 3, fig. 3 is a schematic block diagram of a solid-state switch-based power generator, a storage battery and a bus bar power supply. The direct-current electric energy of the generator is connected to the first bus bar through the solid-state switch, the electric energy of the storage battery is connected to the second bus bar through the solid-state switch, the first bus bar is communicated with the second bus bar through the blocking diode, the electric energy can only flow from the first bus bar to the bus bar 2, the second bus bar receives the parallel power supply of the first bus bar and the storage battery, and the power supply redundancy is improved. Generally, the onboard electric equipment is divided into two types according to importance, flight control equipment and data link equipment which affect flight safety are used as key electric equipment, and task equipment is used as general electric equipment. The first bus bar supplies power to the task device through the solid-state switch, and the second bus bar supplies power to the key power utilization device through the solid-state switch. According to the double-bus-bar power distribution scheme, the first bus bar is ensured to receive the electric energy of the generator and supply power to the task power utilization equipment, meanwhile, the second bus bar is also supplied with power through the blocking diode, and if the task equipment has faults such as short circuit or overcurrent, voltage fluctuation cannot be caused to the second bus bar; the second bus bar receives power supply of the first bus bar and the storage battery, and provides uninterrupted power supply, so that power supply of the flight control equipment and the data link equipment is not interrupted.
Embodiment 4, fig. 4 is a functional block diagram of a computer board embodiment of the present invention. Solid state switch GT in the figure1、GT2、 GTn、GTF、GTBAnd the solid-state switch simultaneously feeds back signals of real-time current, voltage and the like of the electric equipment to the computer board. The bus bars are configured to be a first bus bar and a second bus bar, the first bus bar supplies power to the second bus bar through two blocking diodes, and due to the unidirectional conductivity of the diodes, current can only flow from the first bus bar to the second bus bar, and cannot be supplied reversely. The first bus bar can only receive the electric energy of the generator, the second bus bar can simultaneously receive the electric energy of the generator and the storage battery, and the second bus bar realizes dual-redundancy power supply.
In the actual working process, firstly, after the on-board engine is started, the generator starts to generate electricity, the computer board receives a voltage signal of the generator, and after the power supply voltage of the generator is stable, the computer board transmits a GT signal to the solid-state switch according to the power supply logicFSend out the generator closing command, the solid switch GTFThe generator is connected to the first bus bar in a conducting mode, and the electric energy of the generator supplies power to the first bus bar and continues to supply power to the second bus bar through the blocking diode; secondly, the computer board receives the voltage signal of the storage battery, and if the voltage of the storage battery is normal, the computer board transmits power supply logic to the solid-state switch GTBSend out the closing command of the storage battery, and the solid state switch GTBSwitch on and insert the second busbar with the battery, battery electric energy supplies power to the second busbar this moment, and the generator is accepted simultaneously to the second busbar and the power supply of battery dual supply, and the second busbar has incessant busbar function. Because the power supply voltage output by the normal work of the generator is higher than the discharge voltage of the storage battery but lower than the highest charging voltage of the storage battery, the electric equipment connected on the second bus bar only consumes the electric energy of the generator, the storage battery is in a standby working state, and the storage battery discharges only when the voltage of the second bus bar is reduced due to the fluctuation of the power supply voltage of the generator or sudden load addition. Generally, a first electric device and a second electric device are connected to a first bus bar, the first electric device and the second electric device are airborne task-type devices, such as an SAR and a photoelectric platform, load current is large, load properties are special, input harmonic distortion is large, and surge current at the moment of connection is large, so that other microelectronic devices are prone to failure. The nth electric equipment such as flight control equipment and data link equipment is connected into the second bus bar, the second bus bar is supplied with power by the dual-redundancy power supply, the generator and the storage battery provide electric energy, meanwhile, due to the existence of the blocking diode, the electric energy is ensured to only flow from the first bus bar to the second bus bar, backflow cannot be generated, namely the electric energy of the generator can be transmitted to the second bus bar, and the electric energy of the storage battery cannot be transmitted to the first bus bar. The second bus bar receives the parallel power supply of the dual power supplies of the generator and the storage battery, and the power supply voltage of the storage battery is stable, so that the power quality and the power supply reliability of key equipment such as flight control equipment, a data chain equipment and the like are ensured
And because the storage battery has stable power supply voltage, the uninterrupted power supply of the second bus bar power supply equipment is realized.
And the computer board receives signals such as current, voltage, switch state and the like fed back by all the solid-state switches in real time, and stores and processes the signals. After the computer board receives the output voltage and current signals of the generator, when the voltage of the generator is compared with the overvoltage and undervoltage set values, and the overvoltage and undervoltage set values are judged to be overvoltage and undervoltage of a power supply of the generator, the connection between the generator and the first bus bar is cut off, the first electric equipment and the second electric equipment are powered off, and the safety of the electric equipment is protected; when the current of the generator is compared with an overcurrent set value and the load is judged to be overcurrent, an alarm signal is sent out, and if necessary, the overcurrent power utilization equipment is cut off according to the power supply logic.
And after receiving the output voltage and current signals of the storage battery, the computer board continuously calculates the discharge capacity and the discharge power of the storage battery. Under normal conditions, the voltage of the storage battery is monitored in real time, and when the voltage drops to the rated discharge voltage of the storage battery, a storage battery discharge alarm is sent out. Because the storage battery is an onboard emergency power supply, the solid-state switch of the storage battery is not cut off except in the ground static joint test stage, so that the safety of flight or ground dynamic tests is ensured. And the computer board gives an alarm to the flight control equipment in different grades according to the discharge capacity of the storage battery so as to facilitate judgment and decision of an operator.
The computer board monitors the voltage, the current and the solid-state switch state signals of the first electric equipment, the second electric equipment and the nth electric equipment in real time, and stores and processes the signals. And controlling the on-off of the electric equipment according to the power supply logic. Generally, for the first electric device or the second electric device connected to the first bus bar, if the electric device is abnormal, resulting in current overload or short circuit, the power supply to the electric device is cut off by the solid-state switch. For the nth electric equipment connected to the second bus bar, the electric equipment belongs to flight control equipment or data link equipment, only alarms are carried out, and power supply is not cut off.
In summary, the computer board monitors the voltage and current of the generator, the storage battery and the electric equipment, and the state of the solid-state switch, makes a decision according to the power supply logic, implements power supply management and electric equipment power distribution management, and returns the state information of the power supply and the electric equipment to the flight control equipment through the communication port.
It is noted that, herein, 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. Furthermore, 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 does not include elements inherent in the list. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. In addition, parts of the above technical solutions provided in the embodiments of the present application, which are consistent with the implementation principles of corresponding technical solutions in the prior art, are not described in detail so as to avoid redundant description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. An unmanned aerial vehicle solid state power distribution controller is characterized by comprising a bus bar, a solid state power distribution board, a computer board and an aviation electric connector; wherein the content of the first and second substances,
the input end of the power distribution controller is respectively connected to an unmanned airborne generator and a storage battery pack through a solid-state power distribution board, the unmanned airborne generator is connected with a first bus bar of the solid-state power distribution board, and the storage battery pack is connected with a second bus bar of the solid-state power distribution board;
the solid-state power distribution board is connected with a first bus bar, the first bus bar is connected with all the electric equipment and used for executing power supply and monitoring functions and connecting the output power supply of the unmanned aerial vehicle-mounted generator to each electric equipment; the solid-state power distribution board is connected with a second bus bar, the second bus bar is connected with the task equipment, and the instruction of the flight control computer is executed to realize the on-off control of the task equipment; the first bus bar and the second bus bar are communicated through the blocking diode.
2. The unmanned aerial vehicle solid state power distribution controller of claim 1,
the electric equipment comprises task equipment and key electric equipment, wherein the task equipment comprises an engine stop, an oil pump and recovery equipment; the key electric equipment comprises a flight control computer, a flight control sensor, a steering engine and a measurement and control terminal.
3. The unmanned aerial vehicle solid state power distribution controller of claim 1,
the solid-state power distribution board comprises a plurality of solid-state switches, wherein a part of the solid-state switches are used for executing a power supply function, and the bus bar is switched on through the solid-state switches to supply power to each electric device; and the rest solid-state switches are solid-state switches of the task equipment, and the task equipment is controlled according to the instruction of the flight control computer.
4. The unmanned aerial vehicle solid state power distribution controller of claim 1,
the flight control computer is provided with a control unit, and the control unit comprises a DSP (digital signal processor), a memory and an interface circuit; the DSP is used for realizing the logic function of power distribution control; the memory is used for storing parameters of instruction states, load currents, switch states and fault information, and the interface circuit comprises a communication interface and a switching value input and output circuit.
5. The electrical control method for the unmanned aerial vehicle according to any one of claims 1 to 4, wherein a dual-redundancy solid-state switch is adopted to supply power to the electric equipment, and meanwhile, the state information of the electric equipment is stored.
6. An electrical control method for an unmanned aerial vehicle is characterized by specifically comprising the following steps:
detecting working currents of all electric equipment on the unmanned aerial vehicle, comparing the real-time currents with historical data stored in a database, and determining whether the working state of the electric equipment is normal or not;
detecting the voltage of the unmanned aerial vehicle-mounted generator, and when the voltage is in a preset working voltage range, switching on the solid-state switch GTFConnecting the generator with the first bus bar, and obtaining direct current electric energy by the electric equipment through the first bus bar; when the voltage of the unmanned aerial vehicle-mounted motor is not in the preset working voltage range, the solid-state switch GTFTurning off the generator from the first bus bar;
when the generator generates overvoltage and undervoltage, the solid switch GTFThe turn-off makes unmanned aerial vehicle carry generator break away from first busbar, and the consumer is disconnected simultaneously, adopts the battery power supply, provides the electric energy through the busbar to key consumer, ensures to provide safe return voyage power supply time.
7. The electrical control method for unmanned aerial vehicle of claim 6,
the electric equipment comprises key electric equipment and task equipment, wherein the task equipment comprises a task load, heating equipment and a navigation lamp; the key electric equipment comprises a flight control computer, a flight control sensor, a steering engine, recovery equipment and data link equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522770.9A CN114336525A (en) | 2021-12-14 | 2021-12-14 | Solid-state power distribution controller and power distribution method for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522770.9A CN114336525A (en) | 2021-12-14 | 2021-12-14 | Solid-state power distribution controller and power distribution method for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114336525A true CN114336525A (en) | 2022-04-12 |
Family
ID=81050196
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111522770.9A Pending CN114336525A (en) | 2021-12-14 | 2021-12-14 | Solid-state power distribution controller and power distribution method for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114336525A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112462642A (en) * | 2020-10-30 | 2021-03-09 | 天津航空机电有限公司 | SSPC and contactor combined control system and method suitable for airplane |
| CN113675938A (en) * | 2021-07-09 | 2021-11-19 | 南京航空航天大学 | High-integration-level comprehensive electrical control box for unmanned aerial vehicle and electrical control method for unmanned aerial vehicle |
| CN114172251A (en) * | 2021-11-12 | 2022-03-11 | 天津航空机电有限公司 | Power distribution system of small and medium-sized unmanned helicopter |
-
2021
- 2021-12-14 CN CN202111522770.9A patent/CN114336525A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112462642A (en) * | 2020-10-30 | 2021-03-09 | 天津航空机电有限公司 | SSPC and contactor combined control system and method suitable for airplane |
| CN113675938A (en) * | 2021-07-09 | 2021-11-19 | 南京航空航天大学 | High-integration-level comprehensive electrical control box for unmanned aerial vehicle and electrical control method for unmanned aerial vehicle |
| CN114172251A (en) * | 2021-11-12 | 2022-03-11 | 天津航空机电有限公司 | Power distribution system of small and medium-sized unmanned helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP7432995B2 (en) | Lithium-ion battery high voltage power distribution system architecture | |
| CN110774937B (en) | Vehicle-mounted centralized power distribution type parallel battery management system | |
| CN204376464U (en) | A kind of battery of electric vehicle intelligent management system | |
| CN203472565U (en) | High-voltage electric protection system of electric vehicle | |
| CN110912114A (en) | High-safety low-voltage direct current system | |
| CN216904359U (en) | Intelligent driving power management system and vehicle | |
| CN115513541A (en) | Energy storage safety control system and method | |
| CN116316518A (en) | DC power supply and distribution system of unmanned ship | |
| CN203318314U (en) | Vehicle dark current intelligent control protection system | |
| CN114336525A (en) | Solid-state power distribution controller and power distribution method for unmanned aerial vehicle | |
| CN208571667U (en) | A kind of extension transformer substation communication equipment power-on time device | |
| CN214450308U (en) | Electric automobile low-voltage power supply self-control module with CAN communication | |
| CN212085877U (en) | Large-scale unmanned aerial vehicle power supply redundancy system | |
| CN209621696U (en) | A kind of high-voltage frequency converter cooling fan power supply switching circuit | |
| US6420850B1 (en) | Telecommunication power distribution systems and apparatuses and methods of supplying power to a telecommunication device | |
| CN207184043U (en) | Partial electric grid protection system based on FTU | |
| CN108879866A (en) | Transformer substation communication equipment extends power supply unit | |
| CN1972050A (en) | A multifunctional electric apparatus with programmable and trip circuit output | |
| CN218805246U (en) | Battery management module, fault detection system and vehicle | |
| CN221150999U (en) | Measurement and control module for intelligent charge and discharge and charge and discharge system adopting module | |
| CN220586243U (en) | Direct current short circuit breaking combiner box | |
| CN104037935A (en) | Double-power-source switch controller with short circuit motion-refusing protection function | |
| CN113726000B (en) | Power supply device and power supply method thereof | |
| CN218997768U (en) | Power distribution control monitoring device | |
| CN211744141U (en) | Internet energy gateway circuit breaker management system |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220412 |