CN203638098U - Wired power multi-rotor unmanned aerial vehicle - Google Patents
Wired power multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN203638098U CN203638098U CN201420016027.5U CN201420016027U CN203638098U CN 203638098 U CN203638098 U CN 203638098U CN 201420016027 U CN201420016027 U CN 201420016027U CN 203638098 U CN203638098 U CN 203638098U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model relates to a wired power multi-rotor unmanned aerial vehicle comprising a multi-rotor unmanned aerial vehicle body and a ground power supplying device. The multi-rotor unmanned aerial vehicle body is provided with a power converting system used for converting high-voltage alternating current of the ground power supplying device into low-voltage direct current adaptive to the multi-rotor unmanned aerial vehicle body. The power converting system is electrically connected to the ground power supplying device through a cable and is provided with a power supply assembly used for distributing power for each functional module of the multi-rotor unmanned aerial vehicle body. Compared with the flying scheme of an existing multi-rotor unmanned aerial vehicle carrying batteries, the wired power multi-rotor unmanned aerial vehicle has the advantages that a wired power supply scheme is adopted, the flying time of the aerial vehicle can be increased greatly; and the flying time can be prolonged almost unlimitedly in the withstand ranges of an aerial vehicle motor and other equipment.
Description
Technical field
The utility model relates to aircraft power equipment supply technical field, the many rotor unmanned aircrafts of especially a kind of cable power.
Background technology
The many rotor unmanned aircrafts of multiaxis are more and more in field application such as civilian and engineerings, due to the airworthiness of many rotor unmanned aircrafts of multiaxis uniqueness, determined that this type of aircraft is suitable for taking photo by plane in the air and monitoring etc.But the many rotor unmanned aircrafts of current multiaxis also have its drawback, existing product and design all adopt lithium cell etc. to power to such aircraft, because the lift of multiaxis multi-rotor aerocraft is provided by electrical motor completely, so the large power consumption of energy consumption is very fast.The capacity of cell of carrying more capacity weight is fewer, the flight time of the many rotor unmanned aircrafts of multiaxis of the prior art is generally 5-10 minute, the flight time of Fixed Wing AirVehicle can reach 20 minutes even longer, flight time is so short, is difficult to complete in flight the aerial mission setting.So how to improve flight time and the capacity weight of multiaxis multi-rotor aerocraft, become this area institute problem in urgent need to solve.
China Patent No. ZL 201210510858.3 discloses a kind of many rotor unmanned aircrafts mooring system, comprises many rotor unmanned aircrafts, heaving pile and ground installation as tethered platform, and described heaving pile connects described many rotor unmanned aircrafts and described ground installation; Described many rotor unmanned aircrafts comprise mooring supply unit, and described heaving pile comprises power transmission cable, and described ground installation comprises floor power supply device, and described mooring supply unit connects described floor power supply device by the power transmission cable in described heaving pile.This application by heaving pile by the power delivery on ground to unmanned vehicle, the electric supply installation of ground installation is direct current (DC), large electric current in the time transmitting electricity is larger, because power transmission cable has resistance, therefore power supply voltage step-down is obvious, for making aircraft takeoff obtain larger lift, needs further to increase electric current in the time taking off, to guarantee the power supply voltage of unmanned vehicle, after entering stabilized conditions, reduces again by aircraft electric current to working current.In unmanned vehicle, comprise the electronic devices and components such as more high precision, highly sensitive electrical motor, larger to its impact when electric current is larger, therefore this method has larger drawback.
Utility model content
Technical problem to be solved in the utility model is: a power supply difficult problem that overcomes many rotor unmanned aircrafts in prior art, provide a kind of cable power many rotor unmanned aircrafts, adopt cable power power supply plan, the flight time of aircraft is increased greatly, in the scope that can bear at aircraft electrical motivation and other equipment, almost can infinitely extend the flight time, can make unmanned vehicle have the sufficient time to execute the task.
The utility model solves the technical scheme that its technical matters adopts: the many rotor unmanned aircrafts of a kind of cable power, comprise many rotor unmanned aircrafts and floor power supply device, on described many rotor unmanned aircrafts, be equipped with the power conversion system that the High Level AC Voltage of floor power supply device is converted to the applicable DC low-voltage electricity of many rotor unmanned aircrafts, between described power conversion system and floor power supply device, be electrically connected by cable, the each functional module of promising many rotor unmanned aircrafts is also set on described power conversion system and distributes the power supply assembly of electric energy.Floor power supply device by cable by delivery of electrical energy to power conversion system, power conversion system by alternating current be converted to 24V 48V 72V direct current (DC) (vary in size and determine according to type), then by power supply assembly all consumers of aircraft are powered.
As preferably, described floor power supply device is 220V civil power or 110V civil power or alternating current generator.220V civil power is the supply standard voltage that China adopts, and 110V civil power is the supply standard voltage that the states such as Japan adopt.
Further, described ac generator is that output voltage is the mobile generator of 220V or 110V.For improving travelling performance, user can move with unmanned vehicle by Portable mobile electrical generator.
In order to prevent that floor power supply device from losing suddenly electric power; on described many rotor unmanned aircrafts, emergency source of electrical power is installed; the electrode coupling end of described emergency source of electrical power is provided with battery protection module; between the charging end of described battery protection module and floor power supply device, be connected by cable, between the discharge end of battery protection module and power supply assembly, be connected by wire.Emergency source of electrical power can be powered in the time of floor power supply device fault temporarily, provides the electric power of short time continuation flight to complete aerial mission, or guarantees that unmanned vehicle energy safe falling prevents from falling.Battery protection module charges in the time of emergency battery short of electricity, is full of can automatically stop charging after electricity and play protection galvanic action.
As preferably, described emergency source of electrical power is lithium cell.Lithium cell volume is little, lightweight, capacity is suitable for greatly unmanned vehicle.
Concrete, described power supply assembly comprises system power supply circuit, electrical motor feed circuit and task system feed circuit, described system power supply circuit comprises that it is the first Voltage stabilizing module that flight control system is powered that DC low-voltage electricity is converted to 5V direct current (DC); Described electrical motor feed circuit comprise the electronic governor that regulates motor current; Described task system feed circuit comprise that it is the second Voltage stabilizing module that task system is powered that DC low-voltage electricity is converted to 12V direct current (DC).Flight control system needs the direct current (DC) of 5V, need to give the different electric current of electrical motor according to state of flight, take off, move, rise, decline or turn to thereby control it, on aircraft, also can carry some task systems, as camera head, graphic transmission equipment, communication device etc.
The beneficial effects of the utility model are, the many rotor unmanned aircrafts of cable power of the present utility model, compared with the flight scheme battery-mounted with existing many rotor unmanned aircrafts, the utility model has used cable power power supply plan, can make the flight time of aircraft greatly increase, in the scope that can bear at aircraft electrical motivation and other equipment, almost the flight time can infinitely be extended.Make the fields such as aircraft low latitude monitoring when long, signal relaying, on-the-spot broadcasting, long task consuming time, archaeology, mine locating can bring into play larger effect.And supply current, voltage are more stable, ensure the normal work of high precision, highly sensitive equipment on aircraft, make state of flight more stable, and be conducive to extend the service life of each equipment.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is the block diagram of many rotor unmanned aircrafts of cable power preferred embodiment of the present utility model;
Fig. 2 is the schematic circuit diagram of the many rotor unmanned aircrafts of cable power of the present utility model.
In figure: 1. rotor unmanned aircraft more than, 2. floor power supply device, 3. power conversion system, 4. cable.
The specific embodiment
By reference to the accompanying drawings the utility model is described in further detail now.These accompanying drawings are the schematic diagram of simplification, and basic structure of the present utility model is only described in a schematic way, and therefore it only shows the formation relevant with the utility model.
As shown in Fig. 1 or 2, the many rotor unmanned aircrafts of a kind of cable power of the present utility model, comprise many rotor unmanned aircrafts 1 and floor power supply device 2, on described many rotor unmanned aircrafts 1, be equipped with the power conversion system 3 that the High Level AC Voltage of floor power supply device 2 is converted to the applicable DC low-voltage electricity of many rotor unmanned aircrafts 1, between described power conversion system 3 and floor power supply device 2, be electrically connected by cable 4, the power supply assembly that the each functional module of promising many rotor unmanned aircrafts 1 is distributed electric energy is also set on described power conversion system 3.Floor power supply device 2 by cable 4 by delivery of electrical energy to power conversion system 3, power conversion system 3 by alternating current be converted to 24V 48V 72V direct current (DC) (vary in size and determine according to type), then by power supply assembly all consumers of aircraft are powered.
As preferably, described floor power supply device 2 is 220V civil power or 110V civil power or alternating current generator.220V civil power is the supply standard voltage that China adopts, and 110V civil power is the supply standard voltage that the states such as Japan adopt.
Further, described ac generator is that output voltage is the mobile generator of 220V or 110V.For improving travelling performance, user can move with unmanned vehicle by Portable mobile electrical generator.
In order to prevent that floor power supply device 2 from losing suddenly electric power; on described many rotor unmanned aircrafts, emergency source of electrical power is installed; the electrode coupling end of described emergency source of electrical power is provided with battery protection module; between the charging end of described battery protection module and floor power supply device 2, be connected by cable 4, between the discharge end of battery protection module and power supply assembly, be connected by wire.Emergency source of electrical power can be powered in the time of floor power supply device 2 fault temporarily, provides the electric power of short time continuation flight to complete aerial mission, or guarantees that unmanned vehicle energy safe falling prevents from falling.Battery protection module can make emergency source of electrical power discharge and recharge safely with balance to discharge and recharge, equilibrium charging, battery just can be in the time of charging the life-span reduce.
As preferably, described emergency source of electrical power is lithium cell.Lithium cell volume is little, lightweight, capacity is suitable for greatly unmanned vehicle.
Concrete, described power supply assembly comprises system power supply circuit, electrical motor feed circuit and task system feed circuit, described system power supply circuit comprises that it is the first Voltage stabilizing module that flight control system is powered that DC low-voltage electricity is converted to 5V direct current (DC); Described electrical motor feed circuit comprise the electronic governor that regulates motor current; Described task system feed circuit comprise that it is the second Voltage stabilizing module that task system is powered that DC low-voltage electricity is converted to 12V direct current (DC).Flight control system needs the direct current (DC) of 5V, need to give the different electric current of electrical motor according to state of flight, takes off, moves, rises, declines or turn to thereby control it, also can carry some task systems, as camera head, communication device etc. on aircraft.
The cable that the utility model adopts can be selected 50-150 rice length, the highest flying height that is unmanned vehicle can reach 50-150 rice, flying height is relevant with the length of cable, the heavy burden of longer aircraft is larger, the aircraft lift needing is larger, needs to adopt the larger electrical motor of specification, can select as required suitable cable length, coordinate suitable electrical motor, to reduce costs.On unmanned vehicle, camera head be can carry, monitoring, on-the-spot broadcasting carried out; Also can carry communication apparatus, hover in the air, realize signal relay function, as built interim communication base station in earthquake areas, long-time hovering is aerial, as signal base station; Also can carry detector, for archaeology and mine locating.
Take above-mentioned foundation desirable embodiment of the present utility model as enlightenment, by above-mentioned description, relevant staff can, not departing from the scope of this utility model technological thought, carry out various change and modification completely.The technical scope of this utility model is not limited to the content on specification sheets, must determine its technical scope according to claim scope.
Claims (6)
1. the many rotor unmanned aircrafts of cable power, comprise many rotor unmanned aircrafts and floor power supply device, it is characterized in that: on described many rotor unmanned aircrafts, be equipped with the power conversion system that the High Level AC Voltage of floor power supply device is converted to the applicable DC low-voltage electricity of many rotor unmanned aircrafts, between described power conversion system and floor power supply device, be electrically connected by cable, the power supply assembly that the each functional module of promising many rotor unmanned aircrafts is distributed electric energy is also set on described power conversion system.
2. the many rotor unmanned aircrafts of cable power as claimed in claim 1, is characterized in that: described floor power supply device is 220V civil power or 110V civil power or alternating current generator.
3. the many rotor unmanned aircrafts of cable power as claimed in claim 2, is characterized in that: described ac generator is that output voltage is the mobile generator of 220V or 110V.
4. the many rotor unmanned aircrafts of cable power as claimed in claim 1; it is characterized in that: on described many rotor unmanned aircrafts, emergency source of electrical power is installed; the electrode coupling end of described emergency source of electrical power is provided with battery protection module; between the charging end of described battery protection module and floor power supply device, be connected by cable, between the discharge end of battery protection module and power supply assembly, be connected by wire.
5. the many rotor unmanned aircrafts of cable power as claimed in claim 4, is characterized in that: described emergency source of electrical power is lithium cell.
6. the many rotor unmanned aircrafts of cable power as claimed in claim 1, it is characterized in that: described power supply assembly comprises system power supply circuit, electrical motor feed circuit and task system feed circuit, described system power supply circuit comprises that it is the first Voltage stabilizing module that flight control system is powered that DC low-voltage electricity is converted to 5V direct current (DC); Described electrical motor feed circuit comprise the electronic governor that regulates motor current; Described task system feed circuit comprise that it is the second Voltage stabilizing module that task system is powered that DC low-voltage electricity is converted to 12V direct current (DC).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420016027.5U CN203638098U (en) | 2014-01-10 | 2014-01-10 | Wired power multi-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420016027.5U CN203638098U (en) | 2014-01-10 | 2014-01-10 | Wired power multi-rotor unmanned aerial vehicle |
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| CN203638098U true CN203638098U (en) | 2014-06-11 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754373A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Wired power multiple rotor wing unmanned aerial vehicle |
| CN105217044A (en) * | 2015-09-18 | 2016-01-06 | 上海长语信息科技有限公司 | Multi-axis aircraft DC machine speed regulation method in parallel and product |
| CN106532828A (en) * | 2016-11-28 | 2017-03-22 | 车以能 | Active multi-rotor unmanned aerial vehicle power supply system |
| CN115649460A (en) * | 2022-09-09 | 2023-01-31 | 国网山东省电力公司潍坊供电公司 | Unmanned aerial vehicle high altitude searchlighting system |
-
2014
- 2014-01-10 CN CN201420016027.5U patent/CN203638098U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754373A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Wired power multiple rotor wing unmanned aerial vehicle |
| CN105217044A (en) * | 2015-09-18 | 2016-01-06 | 上海长语信息科技有限公司 | Multi-axis aircraft DC machine speed regulation method in parallel and product |
| CN106532828A (en) * | 2016-11-28 | 2017-03-22 | 车以能 | Active multi-rotor unmanned aerial vehicle power supply system |
| CN115649460A (en) * | 2022-09-09 | 2023-01-31 | 国网山东省电力公司潍坊供电公司 | Unmanned aerial vehicle high altitude searchlighting system |
| CN115649460B (en) * | 2022-09-09 | 2023-09-19 | 国网山东省电力公司潍坊供电公司 | Unmanned aerial vehicle high altitude searchlighting system |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170106 Address after: 510030 Yuexiu District, Guangzhou, Jiefang South Road, No. 3712, room 39, Guangzhou flying over the Model Co., Ltd. Patentee after: Guangzhou flying model Co., Ltd. Address before: Suzhou City, Jiangsu Province, Zhangjiagang free trade zone 215635 emerging industry incubation center building A room 210A Jiangsu AI retech UAV Technology Co. Ltd. Patentee before: Ai Rui Tyke, Jiangsu unmanned vehicle Science and Technology Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140611 Termination date: 20200110 |
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| CF01 | Termination of patent right due to non-payment of annual fee |