CN220775438U - Multipath parallel constant current charging device for aircraft battery - Google Patents
Multipath parallel constant current charging device for aircraft battery Download PDFInfo
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- CN220775438U CN220775438U CN202322486294.0U CN202322486294U CN220775438U CN 220775438 U CN220775438 U CN 220775438U CN 202322486294 U CN202322486294 U CN 202322486294U CN 220775438 U CN220775438 U CN 220775438U
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- battery
- power supply
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- 238000010277 constant-current charging Methods 0.000 title claims abstract description 27
- 238000007600 charging Methods 0.000 claims abstract description 92
- 238000001816 cooling Methods 0.000 claims description 11
- 238000009966 trimming Methods 0.000 claims description 7
- 230000001012 protector Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 5
- 230000017525 heat dissipation Effects 0.000 description 5
- 238000005259 measurement Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000005669 field effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
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Abstract
The utility model discloses a multipath parallel constant current charging device for aircraft batteries, which comprises a box body and a first panel, wherein the first panel is arranged at one end of the box body, and a battery charging area is arranged at one side of the first panel, which is close to the box body, and can charge multipath aircraft batteries at the same time in a constant current manner; the first panel is further provided with an external direct current power supply access area which is arranged on the same side as the battery charging area of the first panel and used for accessing external current of the first panel. The utility model solves the problem that a plurality of direct current power supplies are needed when the current battery is charged, and can realize the constant current charging of a plurality of aircraft batteries at the same time by only connecting one direct current power supply, thereby greatly reducing the charging cost and improving the power utilization rate.
Description
Technical Field
The utility model relates to the technical field of plane battery multipath parallel constant current charging devices, in particular to a plane battery multipath parallel constant current charging device.
Background
At present, a direct-current power supply direct charging mode is generally adopted for charging the aircraft battery, the direct-current power supply generally has two or three paths of parallel power supply outputs, a plurality of direct-current power supplies are needed when the number of the batteries to be charged is large, the price of the direct-current power supply is high, the charging cost is high, and the use efficiency is low.
Disclosure of Invention
The utility model aims to provide a multipath parallel constant current charging device for an aircraft battery, so as to solve the problems in the prior art.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:
a multipath parallel constant current charging device for an aircraft battery comprises a box body and a hollow cavity;
the first panel is arranged at one end of the box body, and a battery charging area is arranged at one side of the first panel, which is close to the box body, and can charge a plurality of aircraft batteries in a constant-voltage manner at the same time;
the first panel is also provided with an external direct current power supply access area which is arranged on the same side as the battery charging area of the first panel and used for accessing external current of the first panel.
In some embodiments, the battery charging area of the first panel includes a plurality of charging units, and the plurality of charging units are sequentially arranged on the first panel.
In some of these embodiments, the charging unit includes: the charging device comprises a battery access port, a charging switch, a charging indicator lamp, a charging voltage measuring hole, a charging voltage display, a charging current trimming potentiometer, a charging current display and a charging current measuring hole; the battery access port, the charging switch, the charging indicator lamp, the charging voltage measuring hole, the charging voltage display, the charging current trimming potentiometer, the charging current display and the charging current measuring hole are electrically connected in sequence.
In some embodiments, the external dc power access area includes a dc power input aperture, a power switch, and a power indicator;
the direct current power input hole, the power switch and the power indicator lamp are electrically connected in sequence.
In some embodiments, the method further comprises:
the second panel is arranged on one side, far away from the first panel, of the box body and is used for radiating heat for the box body.
In some embodiments, the second panel is provided with a direct current power input hole, a power supply safety and a power input end of the cooling fan; the direct current power input hole, the power supply safety device and the power supply input end of the cooling fan are electrically connected.
In some embodiments, the method further comprises:
the cooling fan is arranged on the second panel and is electrically connected with the power input end of the cooling fan.
In some embodiments, each charging unit charges an aircraft battery.
In some embodiments, the method further comprises: the handle is arranged on one side of the first panel, which is far away from the box body.
The beneficial effects of the utility model are as follows:
the utility model discloses a multipath parallel constant current charging device for aircraft batteries, which comprises a box body and a first panel, wherein the first panel is arranged at one end of the box body, and a battery charging area is arranged at one side of the first panel, which is close to the box body, and can charge multipath aircraft batteries at the same time in a constant current manner; the first panel is further provided with an external direct current power supply access area which is arranged on the same side as the battery charging area of the first panel and used for accessing external current of the first panel. The utility model solves the problem that a plurality of direct current power supplies are needed when the current battery is charged, and can realize the constant current charging of a plurality of aircraft batteries at the same time by only connecting one direct current power supply, thereby greatly reducing the charging cost and improving the power utilization rate.
Drawings
FIG. 1 is a schematic diagram of a multi-channel parallel constant current charging device for an aircraft battery;
FIG. 2 is a schematic diagram of a first panel of an aircraft battery multi-channel parallel constant current charging device according to the present utility model;
FIG. 3 is a schematic diagram of a second panel of an aircraft battery multi-channel parallel constant current charging device according to the present utility model;
FIG. 4 is a schematic diagram of the operation of a multi-channel parallel constant current charging device for an aircraft battery according to the present utility model;
fig. 5 is a schematic diagram of a charging circuit board of the multi-channel parallel constant current charging device for the aircraft battery.
In the drawing, 100, a first panel; 110. a charging current display; 120. a charging current trimming potentiometer; 130. a charging current measuring hole; 140. a charging voltage display; 150. a charge indicator light; 160. a charging switch; 170. a battery access hole; 180. a charging voltage measurement hole; 190. a power switch; 191. a power indicator light; 192. a DC power supply input port; 200. a case; 210. a handle; 220. a heat radiation fan; 230. a power input end of the cooling fan; 240. a DC power supply input hole; 250. and (5) power supply safety.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. Examples of the embodiments are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present utility model and should not be construed as limiting the utility model.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "examples," "particular examples," "one particular embodiment," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, schematic representations of terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Referring to fig. 1, 2, 3, 4 and 5, the multi-channel parallel constant current charging device for the aircraft battery comprises a box body and a hollow cavity. The first panel 100 is arranged at one end of the box body, and a battery charging area is arranged on one side, close to the box body, of the first panel 100, and can be used for simultaneously constantly charging multiple aircraft batteries. The first panel 100 is further provided with an external dc power supply access area, which is disposed on the same side as the battery charging area of the first panel 100, for accessing external current of the first panel 100. The utility model solves the problem that a plurality of direct current power supplies are needed when the current battery is charged, and can realize the constant current charging of a plurality of aircraft batteries at the same time by only connecting one direct current power supply, thereby greatly reducing the charging cost and improving the power utilization rate.
The utility model adopts a 4U standard chassis, and wiring holes, switches, indicator lamps, nixie tube displays, potentiometers and the like are arranged on front and rear panels of the chassis. The front panel is divided into 6 areas, the functions of the left 5 areas are the same, and the front panel is a battery charging area, so that at most 5 paths of aircraft batteries can be charged at the same time in a constant current manner.
In some embodiments, the battery charging area of the first panel 100 includes a plurality of charging units, and the plurality of charging units are sequentially arranged on the first panel 100.
In some embodiments, the charging unit includes a battery access port 170, a charging switch 160, a charging indicator light 150, a charging voltage measurement aperture 130, a charging voltage display 110, a charging current trimming potentiometer 120, a charging current display 140, and a charging current measurement aperture 180. The battery access 170, the charging switch 160, the charging indicator light 150, the charging voltage measuring hole 180, the charging voltage display 140, the charging current trimming potentiometer 120, the charging current display 140 and the charging current measuring hole 130 are electrically connected in sequence.
The battery charging function is mainly realized by a charging circuit board in the case, the charging circuit board is connected with direct-current voltage input by a direct-current power supply, a reference charging current is formed through voltage stabilization, following and sampling, and the battery is charged through a field effect tube.
In some embodiments, the external dc power access area includes a dc power input aperture 240, a power switch 190, and a power indicator 191. The dc power input hole 240, the power switch 190, and the power indicator 150 are electrically connected in this order.
In some embodiments, the heat sink further includes a second panel disposed on a side of the case remote from the first panel 100 for dissipating heat from the case.
In some embodiments, the second panel is provided with a dc power input hole 192, a power supply safety 250, and a radiator fan power input 230. The dc power input hole 240, the power supply safety 250 and the cooling fan power input terminal 230 are electrically connected.
In some embodiments, the heat dissipation device further includes a heat dissipation fan 220, the heat dissipation fan 220 is disposed on the second panel, and the heat dissipation fan 220 is electrically connected to the heat dissipation fan power input terminal 230.
In some embodiments, each charging unit charges an aircraft battery.
In some embodiments, the handle 210 is further included and disposed on a side of the first panel remote from the case.
IN this embodiment, 5 or less aircraft batteries are respectively connected to BAT 1-BAT 5 charging-potential BAT IN battery access holes, a direct-current power supply is connected to a DCIN direct-current power supply input hole of the front panel or the rear panel, a DCIN power switch is turned ON, and a corresponding indicator light is turned ON to represent that the aircraft battery charging device is powered. The back panel 220VAC is connected to the commercial power, the AC power switch is turned on, and the cooling fan is operated. The aircraft battery CHG switch is turned ON and battery charging begins. The BAT VOLT nixie tube indicates the current battery voltage, and the battery voltage can also be measured by a multimeter through the BAT VOLT measuring hole. The ICHG nixie tube indicates the current charge current, and the current charge measurement can also be performed through the ICHG measurement hole using a multimeter voltage rail. The charging current can be fine-tuned by means of an IADJ potentiometer.
By adopting the technical scheme disclosed by the utility model, the following beneficial effects are obtained:
the utility model solves the problem that a plurality of direct current power supplies are needed when the current battery is charged, and can realize constant current charging of at most 5 aircraft batteries by only connecting one direct current power supply, thereby greatly reducing the charging cost and improving the power utilization rate.
The foregoing is merely a preferred embodiment of the present utility model and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present utility model, which is also intended to be covered by the present utility model.
Claims (9)
1. The utility model provides an aircraft battery multichannel parallel constant current charging device which characterized in that includes:
a box body, a hollow cavity;
the first panel is arranged at one end of the box body, and a battery charging area is arranged at one side of the first panel, which is close to the box body, and can charge a plurality of aircraft batteries in a constant-voltage mode at the same time;
the first panel is also provided with an external direct current power supply access area which is arranged on the same side as the battery charging area of the first panel and used for accessing external current of the first panel.
2. The aircraft battery multi-path parallel constant current charging device according to claim 1, wherein,
the battery charging area of the first panel comprises a plurality of charging units, and the charging units are sequentially arranged on the first panel.
3. The aircraft battery multi-path parallel constant current charging device according to claim 2, wherein,
the charging unit includes: the charging device comprises a battery access port, a charging switch, a charging indicator lamp, a charging voltage measuring hole, a charging voltage display, a charging current trimming potentiometer, a charging current display and a charging current measuring hole; the battery access port, the charging switch, the charging indicator lamp, the charging voltage measuring hole, the charging voltage display, the charging current trimming potentiometer, the charging current display and the charging current measuring hole are electrically connected in sequence.
4. The aircraft battery multi-path parallel constant current charging device according to claim 2, wherein,
the external direct-current power supply access area comprises a direct-current power supply input hole, a power switch and a power indicator lamp; the direct current power supply input hole, the power switch and the power indicator lamp are electrically connected in sequence.
5. The aircraft battery multi-path parallel constant current charging device of claim 1, further comprising:
the second panel is arranged on one side, away from the first panel, of the box body and is used for radiating heat for the box body.
6. The multi-channel parallel constant current charging device for the aircraft battery according to claim 5, wherein,
the second panel is provided with a direct-current power supply input hole, a power supply safety device and a power supply input end of the cooling fan; the direct current power input hole, the power supply protector and the power supply input end of the cooling fan are electrically connected.
7. The aircraft battery multi-path parallel constant current charging device of claim 5, further comprising:
the cooling fan is arranged on the second panel and is electrically connected with the power input end of the cooling fan.
8. A multi-path parallel constant current charging device for aircraft batteries according to claim 3, wherein each charging unit charges one aircraft battery.
9. The aircraft battery multi-path parallel constant current charging device according to claim 3, further comprising:
the handle is arranged on one side, far away from the box body, of the first panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322486294.0U CN220775438U (en) | 2023-09-13 | 2023-09-13 | Multipath parallel constant current charging device for aircraft battery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322486294.0U CN220775438U (en) | 2023-09-13 | 2023-09-13 | Multipath parallel constant current charging device for aircraft battery |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220775438U true CN220775438U (en) | 2024-04-12 |
Family
ID=90618298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322486294.0U Active CN220775438U (en) | 2023-09-13 | 2023-09-13 | Multipath parallel constant current charging device for aircraft battery |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220775438U (en) |
-
2023
- 2023-09-13 CN CN202322486294.0U patent/CN220775438U/en active Active
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