CN220711132U - Portable aircraft DC external power supply - Google Patents
Portable aircraft DC external power supply Download PDFInfo
- Publication number
- CN220711132U CN220711132U CN202320753082.1U CN202320753082U CN220711132U CN 220711132 U CN220711132 U CN 220711132U CN 202320753082 U CN202320753082 U CN 202320753082U CN 220711132 U CN220711132 U CN 220711132U
- Authority
- CN
- China
- Prior art keywords
- power supply
- battery pack
- external power
- lithium battery
- display screen
- 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
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 27
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 27
- 239000002253 acid Substances 0.000 description 6
- 238000010248 power generation Methods 0.000 description 6
- 238000012423 maintenance Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The utility model relates to the field of design of aircraft power supply systems, in particular to a portable aircraft direct-current external power supply, which comprises an output interface, a circuit breaker, a display screen, a lithium battery pack and a display screen button, wherein the positive end of the output interface is connected to the positive end of the lithium battery pack through the circuit breaker, the negative end of the output interface is connected to the negative end of the lithium battery pack, and the display screen button are connected in parallel at the two ends of the lithium battery pack after being connected in series.
Description
Technical Field
The utility model relates to the field of design of aircraft power supply systems, in particular to a portable aircraft direct-current external power supply.
Background
At present, an airplane adopting a low-voltage direct-current 28V power supply system needs direct-current ground power supply to supply power before ground overhaul or take-off, the current ground power supply adopts a universal PJ500A connector, a lead-acid storage battery pack or a ground power generation car is adopted to supply power, and the lead-acid storage battery pack or the ground power generation car is relatively large, is inconvenient to carry and is not suitable for field environment.
Disclosure of Invention
The purpose of the utility model is that: the portable aircraft direct-current external power supply is used for solving the problems that in the prior art, a general PJ500A connector is adopted, a lead-acid storage battery pack or a ground power generation car is used for supplying power, the lead-acid storage battery pack or the ground power generation car is large in size, inconvenient to carry and unsuitable for field environment.
The technical scheme of the utility model is as follows:
the utility model provides a portable aircraft direct current external power source, includes output interface 1, circuit breaker 2, display screen 5, lithium cell group 7 and display screen button 8, output interface 1 positive end is connected to the positive end of lithium cell group 7 through circuit breaker 2, output interface 1 negative terminal is connected to the negative terminal of lithium cell group 7, display screen 5, display screen button 8
And are connected in parallel at two ends of the lithium battery pack 7 after being connected in series.
Further, the lithium battery pack also comprises a charging port 4, wherein the charging port 4 is connected in parallel with two ends of the lithium battery pack 7.
Further, still include the casing, output interface 1, circuit breaker 2, charge mouth 4, display screen 5, lithium cell group 7 and display screen button 8 all set up in the casing.
Further, one end of the shell is provided with a handle 3.
Further, a rope hanging interface 6 is arranged on the shell.
Further, the capacity of the lithium battery 7 was 50Ah.
The utility model has the beneficial effects that: the portable aircraft direct-current external power supply is used for solving the problems that in the prior art, a general PJ500A connector is adopted, a lead-acid storage battery pack or a ground power generation car is used for supplying power, the volume of the lead-acid storage battery pack or the ground power generation car is large, the portable aircraft direct-current external power supply is inconvenient to carry and is not suitable for field environment, and the portable aircraft direct-current external power supply is convenient for ground service portability and is used for on-board power-on overhaul work.
Drawings
FIG. 1 is a schematic view of the portable aircraft DC external power supply;
FIG. 2 is a left side view of the portable aircraft DC external power supply of the present utility model;
fig. 3 is a schematic diagram of the internal circuit structure of the portable aircraft dc external power supply of the present utility model.
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. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
As shown in fig. 2, a portable aircraft dc external power supply includes an output interface 1, a circuit breaker 2, a display screen 5, a lithium battery pack 7 and a display screen button 8, wherein the positive end of the output interface 1 is connected to the positive end of the lithium battery pack 7 through the circuit breaker 2, the negative end of the output interface 1 is connected to the negative end of the lithium battery pack 7, and the display screen 5 and the display screen button 8 are connected in series and then connected in parallel at two ends of the lithium battery pack 7.
In this embodiment, the lithium battery pack further comprises a charging port 4, wherein the charging port 4 is connected in parallel with two ends of the lithium battery pack 7.
As shown in fig. 1, in this embodiment, the battery charger further includes a housing, an output interface 1, a circuit breaker 2, a charging port 4, a display screen 5, a lithium battery pack 7 and a display screen button 8 are all disposed in the housing, one end of the housing is provided with a handle 3, and a rope hanging port 6 is further disposed on the housing.
The weight of the utility model is estimated to be 14.28kg when the design is carried out, and the concrete composition is as follows:
1) The capacity of the lithium battery pack 7 was 50Ah, and the predicted weight was 13kg;
2) The weight of the breaker 2 is 50g;
3) The weight of the charging port socket 4 is 30g;
4) The weight of the output interface 1 is 500g;
5) The weight of the shell (comprising the handle 3 and the rope hanging opening 6) is 500g;
6) The weight of the display screen button 8 and the display screen 5 is 100g;
7) The weight of the circuit was 100g.
The portable aircraft direct-current external power supply has the advantages of light weight, small volume and portability, and is suitable for field environment.
The application method of the utility model comprises the following steps:
during normal use, the ground service personnel presses the button 8 of the external power supply display screen first, the external power supply voltage and the capacity are displayed on the display screen 5, and when the voltage and the capacity meet the use requirements, the ground service personnel places the ground service personnel at the position of the handle 3 and holds the ground service personnel to the plane. When the position of the external power supply socket on the airplane is reached, the external power supply socket cover is opened, the portable external power supply output interface 1 is connected with the socket on the airplane forcibly, and the breaker 2 is pressed to output a direct current power supply for on-board power supply and maintenance.
When the portable external power supply is stopped, the breaker 2 is pulled out, and then the portable external power supply is pulled out from the on-board socket interface.
When the portable external power supply voltage and capacity are low, the ground staff uses a special charger to connect with the portable external power supply charging port 4 for charging.
In addition, the external power socket is also provided with a rope hanging interface 6 which can be used for installing a rope for convenient carrying, and the portable external power supply can be fixed on an airplane by using the rope for long-time power on or maintenance so as to ensure safety.
The foregoing is merely a detailed description of the utility model, which is not a matter of routine skill in the art. However, the scope of the present utility model is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present utility model should be included in the scope of the present utility model. The protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims (4)
1. The portable aircraft direct-current external power supply is characterized by comprising an output interface (1), a circuit breaker (2), a display screen (5), a lithium battery pack (7) and a display screen button (8), wherein the positive end of the output interface (1) is connected to the positive end of the lithium battery pack (7) through the circuit breaker (2), the negative end of the output interface (1) is connected to the negative end of the lithium battery pack (7), the display screen (5) and the display screen button (8) are connected in series and then are connected to the two ends of the lithium battery pack (7) in parallel, the portable aircraft direct-current external power supply further comprises a shell, and the output interface (1), the circuit breaker (2), a charging port (4), the display screen (5), the lithium battery pack (7) and the display screen button (8) are all arranged in the shell; the shell is also provided with a rope hanging interface (6).
2. The portable aircraft direct current external power supply according to claim 1, further comprising a charging port (4), wherein the charging port (4) is connected in parallel to two ends of the lithium battery pack (7).
3. A portable aircraft dc external power supply according to claim 1, characterized in that the housing is provided with a handle (3) at one end.
4. A portable aircraft dc external power supply according to claim 1, characterized in that the lithium battery pack (7) has a capacity of 50Ah.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320753082.1U CN220711132U (en) | 2023-04-07 | 2023-04-07 | Portable aircraft DC external power supply |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320753082.1U CN220711132U (en) | 2023-04-07 | 2023-04-07 | Portable aircraft DC external power supply |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220711132U true CN220711132U (en) | 2024-04-02 |
Family
ID=90438581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320753082.1U Active CN220711132U (en) | 2023-04-07 | 2023-04-07 | Portable aircraft DC external power supply |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220711132U (en) |
-
2023
- 2023-04-07 CN CN202320753082.1U patent/CN220711132U/en active Active
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |