CN207291732U - A kind of wireless charging device based on multi-rotor aerocraft - Google Patents
A kind of wireless charging device based on multi-rotor aerocraft Download PDFInfo
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- CN207291732U CN207291732U CN201721352878.7U CN201721352878U CN207291732U CN 207291732 U CN207291732 U CN 207291732U CN 201721352878 U CN201721352878 U CN 201721352878U CN 207291732 U CN207291732 U CN 207291732U
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- module
- electrically connected
- rotor aerocraft
- electromagnetic launching
- output terminal
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Abstract
The utility model discloses a kind of wireless charging device based on multi-rotor aerocraft, and in particular to wireless power transmission field.Including power supply module, Electromagnetic Launching module and electromagnetism receiving module, wherein, the Electromagnetic Launching module includes Electromagnetic Launching circuit and Electromagnetic Launching coil, the Electromagnetic Launching circuit includes high-frequency inverter and power amplifier module, the input terminal of the high-frequency inverter is electrically connected with the output terminal of power supply module, the output terminal of the high-frequency inverter is electrically connected with the input terminal of the power amplifier module, the output terminal of the power amplifier module is electrically connected with the Electromagnetic Launching coil, the Electromagnetic Launching coil passes through electromagnetic wave wireless connection with the electromagnetism receiving module.The public wireless charging device based on multi-rotor aerocraft of utility model, can improve the cruising ability of multi-rotor aerocraft, increase line walking scope, improve work efficiency.
Description
Technical field
Wireless power transmission field is the utility model is related to, particularly a kind of wireless charging Denso based on multi-rotor aerocraft
Put.
Background technology
Electrical equipment needs periodically to carry out inspection, and the mode for the manual inspection taken in the past is time-consuming and laborious, some scattered cloth
Put the important electrical in remote mountain areas to monitor in time, some important electrical equipments can install on-line monitoring dress
Put, but some erroneous judgements and maloperation usually occurs in the On-line Fault Detection of single source sensor, causes damages.More rotations
Rotor aircraft is currently meet the composite requests such as polling transmission line carrier highly reliable, low point of danger, high efficiency, low cost optimal
Selection, is with a wide range of applications.
However, the multi-rotor aerocraft applied to electric system line walking uses storage battery power supply, continuous working period at present
About 30-50min, charging will be returned after a period of time that works, especially in the ultra-high-tension power transmission line line walking of remote mountain areas,
The low work efficiency for greatly reducing multi-rotor aerocraft of cruising ability.Currently on the market mainly by increasing the capacity of storage battery
To improve the cruising ability of aircraft, but this inevitably causes additionally to bear a heavy burden to aircraft again, thus the method is also difficult
To tackle the problem at its root.
Utility model content
The utility model technical issues that need to address are that the multi-rotor aerocraft of electric system line walking is supplied using storage battery
Electricity, cruising ability is low, greatly reduces the work efficiency of multi-rotor aerocraft, and then provides one kind and can be used for multi-rotor aerocraft
Wireless charging device.
In order to solve the above technical problems, technical solution adopted in the utility model is as follows：
A kind of wireless charging device based on multi-rotor aerocraft, including power supply module, Electromagnetic Launching module and electricity
Magnetic receiving module, wherein, the Electromagnetic Launching module includes Electromagnetic Launching circuit and Electromagnetic Launching coil, the Electromagnetic Launching electricity
Road includes high-frequency inverter and power amplifier module, the input terminal of the high-frequency inverter and the output terminal electricity of power supply module
Connection, the output terminal of the high-frequency inverter are electrically connected with the input terminal of the power amplifier module, the power amplifier module
Output terminal be electrically connected with the Electromagnetic Launching coil, the electromagnetism receiving coil and the electromagnetism receiving module pass through electromagnetic wave
Wireless connection.
Further, the power supply module includes solar cell module, storage battery and controller, the solar energy
The output terminal of battery component is electrically connected with the input terminal of storage battery and the input terminal of controller respectively, the output terminal of the storage battery
It is electrically connected with the input terminal of the controller；The input of the output terminal of the controller and the high-frequency inverter of Electromagnetic Launching circuit
End is electrically connected.
Further, the electromagnetism receiving module receives circuit and electromagnetism receiving coil including electromagnetism, and the electromagnetism receives
Circuit includes current rectifying and wave filtering circuit, DC-DC power module, the input terminal of the electromagnetism receiving coil and the current rectifying and wave filtering circuit
It is electrically connected, the output terminal of the current rectifying and wave filtering circuit is electrically connected with the input terminal of the DC-DC power module, the DC-DC electricity
The output terminal of source module is electrically connected with the battery in multi-rotor aerocraft.
Further, the Electromagnetic Launching circuit further includes overcurrent protective device, the overcurrent protective device and the work(
Rate amplification module is electrically connected.
Further, the electromagnetism receives circuit and further includes protection apparatus preventing reverse connection, the protection apparatus preventing reverse connection and institute
State DC-DC power module electrical connection.
Further, the working frequency of the high-frequency inverter is 600KHZ.
Further, the electromagnetism receives circuit and is arranged at multi-rotor aerocraft inside chassis, the electromagnetism receiving coil
It is arranged on the alighting carriage of multi-rotor aerocraft.
Further, charging platform is set on power transmission tower, power supply module and electromagnetism are set on the charging platform
Transmitting module.
As a result of above technical scheme, technological progress acquired by the utility model is as follows：
（1）Wireless charging device described in the utility model based on multi-rotor aerocraft, by set power supply module,
Electromagnetic Launching module and electromagnetism receiving module, are Electromagnetic Launching module for power supply by power supply module, form electromagnetic wave, electromagnetism
Receiving module receives electromagnetic wave and is converted into electric energy, carries out wireless charging for multi-rotor aerocraft, this charging modes overcome only
The deficiency to be charged using electric power storage, can improve the cruising ability of multi-rotor aerocraft, increase line walking scope, improve work efficiency.
（2）Wireless charging device described in the utility model based on multi-rotor aerocraft, is further limited on power transmission tower
Charging platform is set, power supply module and Electromagnetic Launching module are set on the charging platform, aircraft in long-range line walking,
When running into battery capacity deficiency, you can automatic charging on to the charging platform of power transmission tower nearby, then take off line walking again, so that
Avoid the problems such as backhaul charging, time-consuming and laborious, line walking scope are limited repeatedly in the past, further, nothing described in the utility model
The diameter of electromagnetism receiving coil is smaller in line receiving module, can be directly arranged on the alighting carriage of multi-rotor aerocraft, electricity
Magnetic receives circuit and is arranged at multi-rotor aerocraft inside chassis, and wireless reception coil flies after being arranged at alighting carriage easy to more rotors
When row device lands, electromagnetism receiving coil is accurately located on Electromagnetic Launching coil, carries out wireless charging.
（3）Wireless charging device described in the utility model based on multi-rotor aerocraft, further limits the power supply electricity
Source module is made of solar panel, storage battery and controller, and such solar cell can exist unnecessary energy storage
In storage battery, from regardless of whether weather conditions how, the power supply all can be multi-rotor aerocraft provide electric energy.
（4）Wireless charging device described in the utility model based on multi-rotor aerocraft, further, Electromagnetic Launching module
Built-in overcurrent protective device, can to avoid system output power it is excessive when, cause electric current excessive, damage element.Further, since connect
It is electrically connected all the time with aircraft battery by coil, electromagnetism receiving module is connected to protection apparatus preventing reverse connection, can so prevent more
Rotor craft does not charge, its battery gives coil power supply in turn, causes power attenuation, or even detonator circuit failure；In addition it is more
The electromagnetism receiving coil diameter of rotor craft about only has the half of Electromagnetic Launching coil, so if when aircraft does not drop to
During transmitting coil center, it still can ensure higher charge efficiency.
Brief description of the drawings
Fig. 1 is the structure diagram of the utility model：
Fig. 2 is the structure diagram of the utility model；
Fig. 3 is the structure diagram of the utility model；
Fig. 4 is the structure diagram of the utility model；
Reference numeral：
1. power supply module；11. solar cell module；12. storage battery；13. controller；2. Electromagnetic Launching module；
21. Electromagnetic Launching circuit；211. high-frequency inverter；212. power amplifier module；213. overcurrent protective device；22. Electromagnetic Launching
Coil；3. electromagnetism receiving module；31 electromagnetism receive circuit；311. current rectifying and wave filtering circuit；312.DC-DC power module；It is 313. anti-
Reverse protection device；32. electromagnetism receiving coil.
Embodiment
The utility model is further elaborated below in conjunction with the drawings and specific embodiments.
Wireless charging device based on multi-rotor aerocraft described in present embodiment, as shown in Figure 1 and Figure 2 and Figure 3, bag
Include power supply module 1, Electromagnetic Launching module 2 and electromagnetism receiving module 3, it is preferable that charging platform is set on power transmission tower, is supplied
Power supply module 1, Electromagnetic Launching module 2 are arranged on the charging platform, and the Electromagnetic Launching module 2 includes Electromagnetic Launching electricity
Road 21 and Electromagnetic Launching coil 22, the Electromagnetic Launching circuit 21 include high-frequency inverter 211 and power amplifier module 212, this
The working frequency of the preferred high-frequency inverter is 600KHZ, the input terminal of the high-frequency inverter 211 and confession in embodiment
The output terminal of power supply module 1 is electrically connected, the output terminal of the high-frequency inverter 211 is defeated with the power amplifier module 212
Enter end to be electrically connected, the output terminal of the power amplifier module 212 is electrically connected with the Electromagnetic Launching coil 22, the Electromagnetic Launching
Coil 22 passes through electromagnetic wave wireless connection with the electromagnetism receiving module 3；
In present embodiment, further, the electromagnetic wave receiving module 3 receives circuit 31 including electromagnetism and electromagnetism receives
Coil 32, the electromagnetism, which receives circuit 31, includes current rectifying and wave filtering circuit 311, DC-DC power module 312, the electromagnetism acceptance line
Circle 32 is electrically connected with the input terminal of the current rectifying and wave filtering circuit 311, output terminal and the DC- of the current rectifying and wave filtering circuit 311
The input terminal of DC power module 312 is electrically connected, the electricity in the output terminal and multi-rotor aerocraft of the DC-DC power module 312
Pond is electrically connected.Present embodiment, which also defines the electromagnetism and receives circuit, is arranged at multi-rotor aerocraft inside chassis, the electricity
Magnetic receiving coil is arranged on the alighting carriage of multi-rotor aerocraft；
In present embodiment, further, the power supply module includes solar cell module 11,12 and of storage battery
Controller 13, the output terminal of the solar cell module 11 respectively with the input terminal of storage battery 12 and the input terminal of controller 13
It is electrically connected, the output terminal of the storage battery 12 is electrically connected with the input terminal of the controller 13；The output terminal of the controller 13
It is electrically connected with the input terminal of the high-frequency inverter 211 of Electromagnetic Launching circuit.
The above embodiment when in use, pilot by with multi-rotor aerocraft real-time Communication for Power, monitor the electricity of aircraft
Pond balance information, when finding that battery allowance is insufficient, chargin level nearby is flown to by remote control control by multi-rotor aerocraft
On platform, the alighting carriage of multi-rotor aerocraft is controlled to drop on the Electromagnetic Launching coil of charging platform, radio energy passes at this time
The switch of defeated system automatically opens up, and electric energy is transferred to electricity by power supply module by high-frequency inverter and power amplifier module
The electric energy received is converted into electromagnetic wave by magnetic transmitting coil, Electromagnetic Launching coil, is transferred to electromagnetism receiving coil, and electromagnetism receives
The electromagnetic wave received is converted into electric energy by coil, DC-DC power module is transferred to after being handled by current rectifying and wave filtering circuit, then
Charge to multi-rotor aerocraft.Wait that multi-rotor aerocraft is fully charged when leaving, radio energy transmission system is according to capture
Information, automatic cut-off switch, complete a wireless charging.
It is different from the embodiment described above in present embodiment as the further preferred scheme of the above embodiment,
As shown in figure 4, the Electromagnetic Launching circuit further includes overcurrent protective device 213, the overcurrent protective device is put with the power
Big module is electrically connected, and the electromagnetism receives circuit and further includes protection apparatus preventing reverse connection 313, the protection apparatus preventing reverse connection 313 with
The DC-DC power module electricity 312 connects.In addition, in present embodiment, can also the further preferred Electromagnetic Launching coil
A diameter of 200mm, it is 60mm × 40mm that the high-frequency inverter, power amplifier module and overcurrent protective device, which are integrated in the length of side,
Pcb board on；A diameter of 90mm of the electromagnetism receiving coil, the current rectifying and wave filtering circuit, DC-DC power module and anti-reverse
Protective device is integrated on the pcb board that the length of side is 50mm × 35mm.
When in use, when the electric current of power amplifier module transmission is less than 4A, wireless charging system is just for the above embodiment
Often work, blue lamp is bright on pcb board, and when the electric current of power amplifier module transmission is excessive, PCB when reds, show output power mistake
Greatly, electric current has exceeded limit value, and overcurrent protective device starts at this time, when avoiding system output power excessive, causes electric current excessive,
Damage element；DC-DC power module is connected to protection apparatus preventing reverse connection, management role of having charged to multi-rotor aerocraft battery, when
When aircraft does not charge, since receiving coil is electrically connected with aircraft battery all the time, which can be to avoid
Aircraft battery gives coil power supply in turn, causes power attenuation, or even detonator circuit failure.
Only the utility model and embodiments thereof are described above, this describe it is no restricted, shown in attached drawing
Be also the utility model one of embodiment, actual structure is not limited thereto, if those skilled in the art by
It is enlightened, and without deviating from the purpose of the present invention, is designed and the technical solution phase without creative
As structure and embodiments thereof, should all be when belonging to the scope of protection of the utility model.
Claims (8)
- A kind of 1. wireless charging device based on multi-rotor aerocraft, it is characterised in that：Including power supply module, Electromagnetic Launching Module and electromagnetism receiving module, wherein, the Electromagnetic Launching module includes Electromagnetic Launching circuit and Electromagnetic Launching coil, the electricity Magnetic radiating circuit includes high-frequency inverter and power amplifier module, input terminal and the power supply module of the high-frequency inverter Output terminal is electrically connected, the output terminal of the high-frequency inverter is electrically connected with the input terminal of the power amplifier module, the power The output terminal of amplification module is electrically connected with the Electromagnetic Launching coil, and the Electromagnetic Launching coil leads to the electromagnetism receiving module Cross electromagnetic wave wireless connection.
- 2. the wireless charging device based on multi-rotor aerocraft according to claim 1, it is characterised in that：The power supply Module includes solar cell module, storage battery and controller, the output terminal of the solar cell module respectively with storage battery Input terminal and the input terminal of controller be electrically connected, the output terminal of the storage battery is electrically connected with the input terminal of the controller； The output terminal of the controller is electrically connected with the input terminal of the high-frequency inverter of Electromagnetic Launching circuit.
- 3. the wireless charging device according to claim 1 or claim 2 based on multi-rotor aerocraft, it is characterised in that：The electromagnetism Receiving module receives circuit and electromagnetism receiving coil including electromagnetism, and the electromagnetism, which receives circuit, includes current rectifying and wave filtering circuit, DC-DC Power module, the electromagnetism receiving coil are electrically connected with the input terminal of the current rectifying and wave filtering circuit, the current rectifying and wave filtering circuit Output terminal is electrically connected with the input terminal of the DC-DC power module, the output terminal of the DC-DC power module and more rotor flyings Battery in device is electrically connected.
- 4. the wireless charging device based on multi-rotor aerocraft according to claim 1, it is characterised in that：The Electromagnetic Launching Circuit further includes overcurrent protective device, and the overcurrent protective device is electrically connected with the power amplifier module.
- 5. the wireless charging device based on multi-rotor aerocraft according to claim 3, it is characterised in that：The electromagnetism receives Circuit further includes protection apparatus preventing reverse connection, and the protection apparatus preventing reverse connection is electrically connected with the DC-DC power module.
- 6. according to the wireless charging device based on multi-rotor aerocraft described in claim 1 or 2 or 4 or 5, it is characterised in that：Institute The working frequency for stating high-frequency inverter is 600KHZ.
- 7. the wireless charging device based on multi-rotor aerocraft according to claim 3, it is characterised in that：The electromagnetism receives Circuit is arranged at multi-rotor aerocraft inside chassis, and the electromagnetism receiving coil is arranged at the alighting carriage of multi-rotor aerocraft On.
- 8. the wireless charging device based on multi-rotor aerocraft according to claim 7, it is characterised in that：Set on power transmission tower Charging platform is put, power supply module and Electromagnetic Launching module are set on the charging platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721352878.7U CN207291732U (en) | 2017-10-20 | 2017-10-20 | A kind of wireless charging device based on multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721352878.7U CN207291732U (en) | 2017-10-20 | 2017-10-20 | A kind of wireless charging device based on multi-rotor aerocraft |
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| Publication Number | Publication Date |
|---|---|
| CN207291732U true CN207291732U (en) | 2018-05-01 |
Family
ID=62272234
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721352878.7U Expired - Fee Related CN207291732U (en) | 2017-10-20 | 2017-10-20 | A kind of wireless charging device based on multi-rotor aerocraft |
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| Country | Link |
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| CN (1) | CN207291732U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639330A (en) * | 2018-06-20 | 2018-10-12 | 智飞智能装备科技东台有限公司 | A kind of air traffic air route prospecting unmanned plane |
-
2017
- 2017-10-20 CN CN201721352878.7U patent/CN207291732U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639330A (en) * | 2018-06-20 | 2018-10-12 | 智飞智能装备科技东台有限公司 | A kind of air traffic air route prospecting unmanned plane |
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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: 20180501 Termination date: 20181020 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |