CN206077036U - A kind of battery charger of aircraft power vehicle - Google Patents
A kind of battery charger of aircraft power vehicle Download PDFInfo
- Publication number
- CN206077036U CN206077036U CN201621077133.XU CN201621077133U CN206077036U CN 206077036 U CN206077036 U CN 206077036U CN 201621077133 U CN201621077133 U CN 201621077133U CN 206077036 U CN206077036 U CN 206077036U
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- China
- Prior art keywords
- rectification module
- plug
- selecting switch
- wire plug
- wire
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- Expired - Fee Related
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The purpose of this utility model is to provide a kind of battery charger that is easy to operate, adapting to the high aircraft power vehicle of various power supply modes, intelligence degree；The charger includes Four wire plug, selecting switch is respectively provided with three phase lines being connected with Four wire plug, the respective outfan of three selecting switch is connected with the first rectification module, wherein respective another outfan of selecting switch in two phase lines is connected with the second rectification module；Described protection switch, the first rectification module, the second rectification module, input voltage sensor, selecting switch are connected with controller respectively；Accumulator can be charged by charger in the case of not dismantling；Can be convenient to charge in various places with input chamber electricity or commercial power in the case where plug is changed without；Accumulator relevant parameter can be detected in charging process, is automatically powered off after charging complete, realize intellectuality of charging.
Description
Technical field
This utility model is related to Ground auxiliary equipment field, more particularly to a kind of accumulator of aircraft power vehicle
Charger.
Background technology
Aircraft power vehicle is to produce unidirectional current or alternating current with diesel-electric machine, is tested as aircraft floor
When power supply, the structure of supply vehicle is similar with motor van structure, sets including driver's cabin, chassis, on the vehicle frame at chassis rear portion
Corresponding generating set and diesel engine are put, in order to protect generating equipment, guard box is set at chassis rear portion generally, by generating set
And diesel engine is put in guard box.
The startup of the diesel engine of aircraft power vehicle is completed by accumulator, but the usage frequency of supply vehicle is not
Height, using often there is the several months interval time, long-time does not use diesel engine, then can make the accumulator of startup use for diesel engine because putting certainly
Electricity and undertension, needs could start diesel engine after recharging, therefore important to one in the routine servicing of supply vehicle
Content is exactly every month accumulator once to be charged, and is directly to unload storage battery removing down, is sent to charging station and fills during charging
It is reinstalled in rear car again after electricity, as accumulator quality is larger, dismounting is inconvenient, and frequently dismounts and easily make accumulator
Damage.
The charging process of accumulator needs special messenger and is responsible for, and is also needed to accumulator and dump in time after charging complete
In order to avoid overcharge, charging process is relatively complicated, and cannot carry out effective monitoring to parameters such as the voltages of accumulator in charging process.
When different location uses different power source charges, in addition it is also necessary to carry corresponding adapter, further increase charger
Volume.
The content of the invention
For the problems referred to above, the purpose of this utility model is to provide a kind of easy to operate, various power supply modes of adaptation, intelligence
The battery charger of the high aircraft power vehicle of change degree.
For achieving the above object, the technical scheme adopted by this utility model is：A kind of electric power storage of aircraft power vehicle
Electrolytic battery charger, described charger include Four wire plug, four in Four wire plug metal insert respectively with three phase lines, one
Ground wire connects；
In four described metal inserts, a metal insert being connected with a phase line can be slided along the axis direction of plug
Dynamic, its excess-three bar metal insert is fixedly installed on Four wire plug；Between every phase line and ground wire, input voltage sensor is set；
It is respectively provided with selecting switch in three described phase lines, the respective outfan of three selecting switch and the first rectification module connect
Connect, respective another outfan of selecting switch and the second rectification in two phase lines being connected with the metal insert being fixedly installed
Module connects；The first described rectification module for by 380V three-phase alternating currents electric rectification be 24V unidirectional currents, the second described rectification
Module for by 220V one-way communications electric rectification be 24V unidirectional currents；Described the first rectification module, the output of the second rectification module
End is connected with output plug by protection switch respectively；
Described protection switch, the first rectification module, the second rectification module, input voltage sensor, selecting switch difference
Be connected with controller, controller also with output plug on arrange output voltage sensor, current sensor, overvoltage protection list
Unit's connection.
Preferably, can connect with the side of spacing ball the bottom of metal insert along which in axial sliding in described Four wire plug
Connect, the opposite side of spacing ball is connected with one end of return spring, the other end of return spring is connected with the bottom of sleeve, and sleeve is solid
Surely it is arranged in Four wire plug, the side of described set medial wall of the tube arranges a groove with spherical arc, card in groove
Enter spacing ball；In described groove, along the radial direction setting through hole of sleeve, one end of spacer pin passes through through hole and spacing ball
Contact, the other end are connected with the spring button being arranged on Four wire plug shell.
Preferably, wireless signal transmission unit is set in described controller, wireless signal transmission unit with wireless
The display connection of signal receiver.
This utility model has the advantages that：Accumulator can be filled by charger in the case of not dismantling
Electricity, simplifies charging flow；Four wire plug can be connected with three-phase four-wire socket, single-phase three-wire socket respectively, be changed without plug
In the case of can be convenient to charge in various places with input chamber electricity (220V) or commercial power (380V)；First rectification module,
380V three-phase alternating currents, 220V single-phase alternating currents can be rectified into direct current electricity output, accumulator and charging by two rectification modules respectively
Charging voltage, the charging current of accumulator can be detected in plug connection charging process, and calculates precharge time, charging complete
Controller control protection switch is automatically powered off afterwards, realizes the intelligentized control method that accumulator charges.
Description of the drawings
Fig. 1 is charger circuit schematic diagram；
Fig. 2 is controller circuitry schematic diagram；
Fig. 3 is the structural representation of slidably metal insert.
Specific embodiment
A kind of battery charger of aircraft power vehicle as shown in Figure 1-Figure 3, including Four wire plug 1, four lines are inserted
Four metal inserts 11 in 1 are connected with three phase lines, 12, ground wire 13 respectively；
In four described metal inserts 11, a metal insert 11 being connected with a phase line 12 can be along the axle of plug 1
Line direction is slided, and its excess-three bar metal insert 11 is fixedly installed on Four wire plug 1；The structure of slidable metal insert 11 can
To be that its bottom is connected with the side of spacing ball 21, the opposite side of spacing ball 21 is connected with one end of return spring 22, return bullet
The other end of spring 22 is connected with the bottom of sleeve 23, and sleeve 23 is fixedly installed in Four wire plug 1, described 23 medial wall of sleeve
Side arrange one have spherical arc groove, spacing ball 21 is snapped in groove；In described groove, along the footpath of sleeve 23
Through hole 24 is set to direction, one end of spacer pin 25 is passed through through hole 24 and contacted with spacing ball 21, the other end be arranged on four lines
Spring button 26 on 1 shell of plug connects.
Spring button 26 is pressed, then spacer pin 25 is close to spacing ball 21 under the drive of spring button 26, makes spacing ball
21 are withstood in groove, and now slidable metal insert 11 is fixed, and Four wire plug 1 can be connected with three-phase four-wire socket,
For being input into 380V three-phase alternating currents；Spring button 26 is pressed again, then spacer pin 25 is separated with spacing ball 21, slidable gold
When the top of category inserted sheet 11 runs into obstacle, this metal insert 11 can be slipped in sleeve 23, it is ensured that Four wire plug 1 and single-phase three-wire
Supply socket connects, for being input into 220V single-phase alternating currents.
Input voltage sensor 14 is set between every phase line 12 and ground wire 13；Three-phase alternating current is input into Four wire plug 1
Or during single-phase alternating current, three input voltage sensors 14 can detect the voltage of every phase line respectively, to facilitate monitoring to charge
Voltage.Selecting switch 15, three selecting switch, 15 respective outfans and are respectively provided with three described phase lines 12
One rectification module 3 connects, and the selecting switch 15 in two phase lines 12 being connected with the metal insert 11 being fixedly installed is respective another
One outfan is connected with the second rectification module 4.
For being 24V unidirectional currents by 380V three-phase alternating currents electric rectification, its structure can be two to the first described rectification module 3
Pole pipe formula commutator, or SCR type commutator.The second described rectification module 4 is for will be single-phase 220V alternating currents whole
Flow for 24V unidirectional currents；Its structure can be diode-type rectifier, or SCR type commutator.
Described the first rectification module 3, the outfan of the second rectification module 4 are respectively by protection switch 2 and output plug 6
Connection；Described the first rectification module 3, the second rectification module 4, input voltage sensor 14, selecting switch 15 respectively with control
Device 7 connects, controller 7 also with output plug 6 on arrange output voltage sensor 8, current sensor 9, overvoltage protection list
Unit 10 connects.
The using method of described charger is：Four wire plug 1 is inserted in into 380V three-phase alternating currents supply socket or 220V is mono-
In cross streams supply socket, the detection input voltage value of input voltage sensor 14 intersects for 380V tri- when input voltage is detected
During stream electricity, controller 7 controls the selecting switch 15 arranged in three phase lines 12, three phase lines 12 is connected with the first rectification module 3
Connect, 380V three-phase alternating currents export unidirectional current to output plug 6 through the first rectification module 3；When input voltage is detected it is
During 220V single-phase alternating currents, controller 7 controls the selecting switch 15 arranged in corresponding two phase lines 12, makes corresponding two phases
Line 12 is connected with the second rectification module 4, and 220V single-phase alternating currents export unidirectional current to output plug 6 through the second rectification module 4.
Output plug 6 can be connected with accumulator and is charged by the cable with quick plug, in output plug 6
Voltage when can detect that accumulator charges of output voltage sensor 8, current sensor 9, current value, and calculate accumulator
Precharge time；Accumulator can be protected by overvoltage protective unit 10 when in charging process, voltage is excessive.Work as storage
After battery is fully charged, the current value that current sensor 9 is detected reduces, then protection switch 2 is disconnected by controller 7, realizes electric power storage
Pond is automatically powered off after being full of.
Preferably embodiment is：In described controller 7, wireless signal transmission unit 31, wireless signal transmission list are set
Unit 31 is connected with the display 32 with reception of wireless signals equipment.Described display 32 can be mobile phone, notebook computer,
Or the liquid crystal display screen with reception of wireless signals equipment, the precharge time of accumulator, charging voltage, charging current, charging complete
Information afterwards can be checked from display 32.
Claims (3)
1. a kind of battery charger of aircraft power vehicle, described charger include Four wire plug (1), Four wire plug
(1) four metal inserts (11) in are connected with three phase lines (12), a ground wire (13) respectively；
It is characterized in that：In four described metal inserts (11), a metal insert (11) being connected with a phase line (12)
Can slide along the axis direction of plug (1), its excess-three bar metal insert (11) is fixedly installed on Four wire plug (1)；Per root phase
Input voltage sensor (14) is set between line (12) and ground wire (13)；
It is respectively provided with selecting switch (15) on three described phase lines (12), the respective outfan of three selecting switch (15)
It is connected with the first rectification module (3), the selecting switch on two phase lines (12) being connected with the metal insert (11) being fixedly installed
(15) respective another outfan is connected with the second rectification module (4)；Described the first rectification module (3) is for by 380V tri-
Cross streams electric rectification is 24V unidirectional currents, and described the second rectification module (4) is for straight for 24V by 220V one-way communications electric rectification
Stream electricity；Described the first rectification module (3), the outfan of the second rectification module (4) are inserted with output by protection switch (2) respectively
Head (6) connection；
Described protection switch (2), the first rectification module (3), the second rectification module (4), input voltage sensor (14), select
Switch (15) is connected with controller (7) respectively, controller (7) also with the output voltage sensor that arranges on output plug (6)
(8), current sensor (9), overvoltage protective unit (10) connection.
2. the battery charger of aircraft power vehicle according to claim 1, it is characterised in that：Four described lines are inserted
Can be connected with the side of spacing ball (21) bottom of metal insert (11) along which in axial sliding in head (1), spacing ball (21)
Opposite side is connected with the one end of return spring (22), and the other end of return spring (22) is connected with the bottom of sleeve (23), sleeve
(23) it is fixedly installed in Four wire plug (1), the side of described sleeve (23) medial wall arranges one and has spherical arc
Groove, snaps in spacing ball (21) in groove；It is in described groove, along radial direction setting through hole (24) of sleeve (23), spacing
One end of pin (25) is passed through and through hole (24) is contacted with spacing ball (21), the other end be arranged on Four wire plug (1) shell
Spring button (26) connects.
3. the battery charger of aircraft power vehicle according to claim 1, it is characterised in that：Described controller
(7) wireless signal transmission unit (31), wireless signal transmission unit (31) and showing with reception of wireless signals equipment are set in
Show that device (32) connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621077133.XU CN206077036U (en) | 2016-09-23 | 2016-09-23 | A kind of battery charger of aircraft power vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621077133.XU CN206077036U (en) | 2016-09-23 | 2016-09-23 | A kind of battery charger of aircraft power vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206077036U true CN206077036U (en) | 2017-04-05 |
Family
ID=58440505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621077133.XU Expired - Fee Related CN206077036U (en) | 2016-09-23 | 2016-09-23 | A kind of battery charger of aircraft power vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206077036U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108008673A (en) * | 2017-11-30 | 2018-05-08 | 深圳市水务科技发展有限公司 | A kind of wireless telemetering terminating machine based on NB-IOT |
| CN108075673A (en) * | 2017-09-19 | 2018-05-25 | 珠海格力电器股份有限公司 | Multi-path common-ground rectification circuit and switching power supply |
-
2016
- 2016-09-23 CN CN201621077133.XU patent/CN206077036U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108075673A (en) * | 2017-09-19 | 2018-05-25 | 珠海格力电器股份有限公司 | Multi-path common-ground rectification circuit and switching power supply |
| CN108075673B (en) * | 2017-09-19 | 2020-02-28 | 珠海格力电器股份有限公司 | Multi-path common-ground rectification circuit and switching power supply |
| CN108008673A (en) * | 2017-11-30 | 2018-05-08 | 深圳市水务科技发展有限公司 | A kind of wireless telemetering terminating machine based on NB-IOT |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170405 Termination date: 20170923 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |