CN204992697U - Battery -powered many rotor crafts charger of live that needs car - Google Patents
Battery -powered many rotor crafts charger of live that needs car Download PDFInfo
- Publication number
- CN204992697U CN204992697U CN201520704911.2U CN201520704911U CN204992697U CN 204992697 U CN204992697 U CN 204992697U CN 201520704911 U CN201520704911 U CN 201520704911U CN 204992697 U CN204992697 U CN 204992697U
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- charger
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- charging
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Abstract
The utility model discloses a battery -powered many rotor crafts charger of live that needs car, including DCDC boost circuit module, input voltage protective film piece and charge indicator module, its special character lies in: vehicle -mounted storage battery is connected to the input of DCDC boost circuit module, the output of DCDC boost circuit module is aircraft lithium batteries, and it has the input voltage protective film piece to connect in parallel between DCDC boost circuit module and the vehicle -mounted storage battery, it has the charge indicator module to connect in parallel between DCDC boost circuit module and the aircraft lithium cell, the aircraft charger still includes steady voltage constant -current module to realize the constant voltage constant current charging of charger. Can carry out the quick charge to the lithium cell, the vehicle -mounted storage battery overdischarge can be protected to the input voltage protective film piece in the charging process simultaneously, and the charge indicator module can prevent overcharging to the lithium cell.
Description
Technical field
The utility model relates to multi-rotor aerocraft charger field, especially relates to the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric.
Background technology
Lithium battery has the advantages such as volume is little, capacity is large, without memory, and on multi-rotor aerocraft, lithium battery has been widely used as power supply, and the general three joint cells in series that adopt become 12.6V as power supply.Although using lithium battery as the power source of multi-rotor aerocraft, but still there is the drawback that the flight time is short, cruising time is not enough, when using especially out of doors, to prepare organize reserve battery due to the requirement of aircraft flying for long time can not be met more, add use cost.
The utility model, in order to overcome above-mentioned defect, has carried out useful improvement.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provides the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric.
To achieve these goals, the utility model is by the following technical solutions:
The battery-powered multi-rotor aerocraft charger of one vehicle mounted electric, comprise DC/DC booster circuit module, input voltage protection module and charging indicator light module, its special character is: the input of described DC/DC booster circuit module connects Vehicular accumulator cell, the output of described DC/DC booster circuit module is aircraft lithium cell charging, input voltage protection module is parallel with between described DC/DC booster circuit module and Vehicular accumulator cell, charging indicator light module is parallel with between described DC/DC booster circuit module and aircraft lithium battery, described aircraft charger also comprises pressure-stabilizing constant flow module, described pressure-stabilizing constant flow module comprises Voltage stabilizing module and constant flow module, voltage feedback loop in described Voltage stabilizing module regulates output voltage, current feedback loop in described constant flow module regulates output current, to realize the constant voltage constant current charging of charger.
Further, described DC/DC booster circuit module comprises the booster driving circuit, metal-oxide-semiconductor Q, voltage stabilizing didoe D and the inductance L that are made up of boost pressure controller LM3488, one end of wherein said inductance L is connected with Vehicular accumulator cell, the other end is connected with voltage stabilizing didoe D, metal-oxide-semiconductor Q and booster driving circuit in turn, described boost pressure controller LM3488 exports PWM ripple driven MOS pipe Q, realizes boost function;
Further, between the output that described Voltage stabilizing module and constant flow module are connected in parallel on DC/DC booster circuit module respectively and booster driving circuit, described charging indicator light module one end connects aircraft lithium battery, the other end connects boost pressure controller LM3488, after aircraft lithium cell charging completes, charging indicator light is bright, and charging indicator light module is by signal feedback to boost pressure controller LM3488 simultaneously, and charger stops charging;
Further, described input voltage protection module comprises input low-voltage variation module, and described input low-voltage variation module one end connects Vehicular accumulator cell, and the other end connects booster driving circuit, Real-Time Monitoring battery tension in charging process;
Further, the control interface of described boost pressure controller LM3488 is connected be connected with Voltage stabilizing module by resistance R2, diode D1, adjustable resistance VR1 successively, also be connected with constant flow module by diode D2, adjustable resistance VR2, IN282 current monitor successively, wherein said boost pressure controller LM3488 and IN282 current monitor are powered by Vehicular accumulator cell simultaneously.
The beneficial effects of the utility model: this charger can carry out quick charge to lithium battery; in charging process, input voltage protection module can protect Vehicular accumulator cell overdischarge simultaneously; charging indicator light module can prevent the overcharge to lithium battery; it is the defect that power supply can solve outdoor use aircraft electrical quantity not sufficient that this charger passes through with Vehicular accumulator cell; once the flying power of aircraft was added; and it is easy to carry; there is good practicality; and there is the advantages such as good reliability, stable row is high, cost of manufacture is low, there is certain practicality and economic implications.
Accompanying drawing explanation
Fig. 1 is the utility model structure principle chart.
Fig. 2 is the utility model circuit connection structure figure.
Fig. 3 is the utility model LM3488 control interface figure.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the utility model is further described.
Embodiment of the present utility model is with reference to shown in figure 1-3, the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric, comprise DC/DC booster circuit module, input voltage protection module and charging indicator light module, the input of described DC/DC booster circuit module connects Vehicular accumulator cell, the output of described DC/DC booster circuit module is aircraft lithium cell charging, input voltage protection module is parallel with between described DC/DC booster circuit module and Vehicular accumulator cell, charging indicator light module is parallel with between described DC/DC booster circuit module and aircraft lithium battery, described aircraft charger also comprises pressure-stabilizing constant flow module, described pressure-stabilizing constant flow module comprises Voltage stabilizing module and constant flow module, voltage feedback loop in described Voltage stabilizing module regulates output voltage, current feedback loop in described constant flow module regulates output current, to realize the constant voltage constant current charging of charger, first the voltage of storage battery 10V-12V is raised to rated no-load voltage 13V by the DC/DC boost module of circuit, respectively output voltage and output current are regulated by the voltage feedback loop of circuit and current feedback loop again, realize constant current and the constant voltage charge of charger.In charging process, input voltage protection module can be real-time the terminal voltage of detection storage battery, when battery tension is lower than operating voltage, input voltage protection module will start, red led is bright simultaneously, charger stops charging, prevents storage battery to produce infringement because of overdischarge, protects storage battery; When lithium cell charging completes, charging indicator light is shown as charging complete state by charged state, and charger stops charging simultaneously, prevents over-charge of lithium battery electricity.
Described DC/DC booster circuit module comprises the booster driving circuit, metal-oxide-semiconductor Q, voltage stabilizing didoe D and the inductance L that are made up of boost pressure controller LM3488, one end of wherein said inductance L is connected with Vehicular accumulator cell, the other end is connected with voltage stabilizing didoe D, metal-oxide-semiconductor Q and booster driving circuit in turn, described boost pressure controller LM3488 exports PWM ripple driven MOS pipe Q, realize boost function, battery feed is powered for boost pressure controller LM3488, IN282 current monitor simultaneously, boost module exports PWM ripple driven MOS pipe Q by integrated chip LM3488, realizes boost function.Storage battery connects input low-voltage variation module; Real-Time Monitoring battery tension in charging process; when battery tension is lower than operating voltage, input low-voltage protection circuit feeds back to LM3488 output, and LM3488 stops exporting PWM ripple; metal-oxide-semiconductor turns off; charger stops charging, and when lithium cell charging completes, charging indicator light is bright; charging completion signal is fed back to LM3488, charger stops charging simultaneously.
Described input voltage protection module comprises input low-voltage variation module; described input low-voltage variation module one end connects Vehicular accumulator cell; the other end connects booster driving circuit; Real-Time Monitoring battery tension in charging process; the control interface of boost pressure controller LM3488 is connected be connected with Voltage stabilizing module by resistance R2, diode D1, adjustable resistance VR1 successively, is also connected with constant flow module by diode D2, adjustable resistance VR2, IN282 current monitor successively simultaneously.
The above execution mode only have expressed a kind of execution mode of the present utility model, but therefore can not be interpreted as the restriction to the utility model scope.It should be pointed out that for the person of ordinary skill of the art, without departing from the concept of the premise utility, can also make some distortion and improvement, these all belong to protection range of the present utility model.
Claims (5)
1. one kind with the battery-powered multi-rotor aerocraft charger of vehicle mounted electric, comprise DC/DC booster circuit module, input voltage protection module and charging indicator light module, it is characterized in that: the input of described DC/DC booster circuit module connects Vehicular accumulator cell, the output of described DC/DC booster circuit module is aircraft lithium cell charging, input voltage protection module is parallel with between described DC/DC booster circuit module and Vehicular accumulator cell, charging indicator light module is parallel with between described DC/DC booster circuit module and aircraft lithium battery, described aircraft charger also comprises pressure-stabilizing constant flow module, described pressure-stabilizing constant flow module comprises Voltage stabilizing module and constant flow module, voltage feedback loop in described Voltage stabilizing module regulates output voltage, current feedback loop in described constant flow module regulates output current, to realize the constant voltage constant current charging of charger.
2. the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric according to claim 1, it is characterized in that: described DC/DC booster circuit module comprises the booster driving circuit, metal-oxide-semiconductor Q, voltage stabilizing didoe D and the inductance L that are made up of boost pressure controller LM3488, one end of wherein said inductance L is connected with Vehicular accumulator cell, the other end is connected with voltage stabilizing didoe D, metal-oxide-semiconductor Q and booster driving circuit in turn, described boost pressure controller LM3488 exports PWM ripple driven MOS pipe Q, realizes boost function.
3. the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric according to claim 2, it is characterized in that: between the output that described Voltage stabilizing module and constant flow module are connected in parallel on DC/DC booster circuit module respectively and booster driving circuit, described charging indicator light module one end connects aircraft lithium battery, the other end connects boost pressure controller LM3488, after aircraft lithium cell charging completes, charging indicator light is bright, charging indicator light module is by signal feedback to boost pressure controller LM3488 simultaneously, and charger stops charging.
4. the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric according to claim 3; it is characterized in that: described input voltage protection module comprises input low-voltage variation module; described input low-voltage variation module one end connects Vehicular accumulator cell; the other end connects booster driving circuit, Real-Time Monitoring battery tension in charging process.
5. the battery-powered multi-rotor aerocraft charger of one vehicle mounted electric according to claim 4, it is characterized in that: the control interface of described boost pressure controller LM3488 is connected be connected with Voltage stabilizing module by resistance R2, diode D1, adjustable resistance VR1 successively, also be connected with constant flow module by diode D2, adjustable resistance VR2, IN282 current monitor successively, wherein said boost pressure controller LM3488 and IN282 current monitor are powered by Vehicular accumulator cell simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520704911.2U CN204992697U (en) | 2015-09-14 | 2015-09-14 | Battery -powered many rotor crafts charger of live that needs car |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520704911.2U CN204992697U (en) | 2015-09-14 | 2015-09-14 | Battery -powered many rotor crafts charger of live that needs car |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204992697U true CN204992697U (en) | 2016-01-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520704911.2U Expired - Fee Related CN204992697U (en) | 2015-09-14 | 2015-09-14 | Battery -powered many rotor crafts charger of live that needs car |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204992697U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107437842A (en) * | 2017-09-29 | 2017-12-05 | 蒙城县永腾微行掌智能科技有限责任公司 | A kind of wind power charging device applied to unmanned plane |
| CN107985614A (en) * | 2017-11-24 | 2018-05-04 | 上海华普汽车有限公司 | Vehicle-mounted flight control system and automobile |
-
2015
- 2015-09-14 CN CN201520704911.2U patent/CN204992697U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107437842A (en) * | 2017-09-29 | 2017-12-05 | 蒙城县永腾微行掌智能科技有限责任公司 | A kind of wind power charging device applied to unmanned plane |
| CN107985614A (en) * | 2017-11-24 | 2018-05-04 | 上海华普汽车有限公司 | Vehicle-mounted flight control system and automobile |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160120 Termination date: 20160914 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |