CN205248837U - Power supply unit and unmanned aerial vehicle - Google Patents
Power supply unit and unmanned aerial vehicle Download PDFInfo
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- CN205248837U CN205248837U CN201520954157.8U CN201520954157U CN205248837U CN 205248837 U CN205248837 U CN 205248837U CN 201520954157 U CN201520954157 U CN 201520954157U CN 205248837 U CN205248837 U CN 205248837U
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- switch
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- supply unit
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Abstract
The utility model discloses a power supply unit and unmanned aerial vehicle, power supply unit are used for supplying power for the main circuit via the output, include: fuel cell, the DC -DC converter, be used for with fuel cell's power output transform is charging current, and the DC -DC converter with a plurality of battery branch roads that connect in parallel between the output, wherein, a plurality of battery branch roads are respectively including first switch, chargeable call and the second switch of establishing ties in proper order, first switch is connected to the DC -DC converter, the second switch is connected to the output, at the power supply in -process, the second switch of at least one battery branch road of a plurality of battery branch roads is closed. This power supply unit can improve unmanned aerial vehicle's time of endurance to the redundant backup of power has been realized. The utility model provides an use above -mentioned power supply unit's unmanned aerial vehicle.
Description
Technical field
The utility model relates to unmanned plane technical field, particularly, relates to the unmanned plane of supply unit and use supply unit.
Background technology
Unmanned plane is the aircraft that utilizes radio robot and the presetting apparatus of providing for oneself to handle, and comprises depopulated helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship etc. The power set that adopt comprise aero-engine (for example piston-mode motor, vortex-spraying type engine, fanjet) or motor. Unmanned plane has fast, the unmanned flight of maneuverability, reaction speed, the advantage such as can accurately control and operation requirements is low. By carrying various kinds of sensors and capture apparatus, unmanned plane can be carried out filming image and transmission, high-risk regional detecting function. At present, unmanned plane is in various fields extensive use.
The supply unit of unmanned plane is its important component part. Supply unit is main control module and peripheral circuit power supply. The power set of SUAV are motor, thereby supply unit also needs for motor power supply. In existing unmanned plane, supply unit is generally rechargeable battery, for example lithium battery. It is limited that rechargeable battery exists energy density, the problem that cruising time is short. If awing rechargeable battery lost efficacy, unmanned plane may crash, and exists safety issue.
Utility model content
In view of this, the utility model provides a kind of supply unit and unmanned plane, can improve the cruising time of unmanned plane, and has realized the redundancy backup of power supply.
According to one side of the present utility model, a kind of supply unit is provided, for being main circuit power supply via output, it is characterized in that, comprising: fuel cell; DC-DC converter, for being transformed to charging current by the power stage of described fuel cell; And multiple battery branch roads of parallel connection between described DC-DC converter and described output, wherein, described multiple battery branch road comprises respectively the first switch, rechargeable battery and the second switch of series connection successively, described the first switch is connected to described DC-DC converter, described second switch is connected to described output, in power supply process, the second switch closure of at least one battery branch road of described multiple battery branch roads.
Preferably, also comprise power management module, described power management module monitors the electric weight of the rechargeable battery in described multiple battery branch roads, and controls disconnection and the closure of the switch in described multiple battery branch road.
Preferably, the electric weight of the rechargeable battery of described battery management module in the battery branch road detecting in described multiple battery branch road during higher than first threshold, disconnects the first switch of a described battery branch road and second switch closure.
Preferably, the electric weight of the rechargeable battery of described battery management module in two or more battery branch roads that detect in described multiple battery branch road is during higher than first threshold, the first switch of a battery branch road in described two or more battery branch roads is disconnected and second switch closure, and the first switch and the second switch of all the other the battery branch roads in described two or more battery branch roads are all disconnected.
Preferably, the electric weight of the rechargeable battery of described battery management module in the battery branch road detecting in described multiple battery branch road during lower than first threshold, disconnects the first switch closure of a described battery branch road and second switch.
Preferably, described battery management module, disconnects the first switch of described multiple battery branch roads and second switch closure during all lower than first threshold at the electric weight that the rechargeable battery in described multiple battery branch road detected.
Preferably, described battery management module at the electric weight that the rechargeable battery in described multiple battery branch road detected all lower than first threshold, and when the electric weight of the rechargeable battery in multiple battery branch roads equates, the first switch of described multiple battery branch roads is disconnected and second switch closure.
Preferably, described rechargeable battery is lithium ion battery.
According on the other hand of the present utility model, a kind of unmanned plane is provided, comprising: supply unit as above, power set and main circuit, wherein said supply unit is at least one power supply in described power set and described main circuit.
Preferably, described unmanned plane is multi-rotor aerocraft, and wherein, described power set are motor.
Supply unit of the present utility model, is unmanned plane power supply by multiple rechargeable batteries are set, and in the cruising time of having improved unmanned plane, has realized the redundancy backup of battery simultaneously, has improved safety and stability.
Brief description of the drawings
By the description to the utility model embodiment referring to accompanying drawing, above-mentioned and other objects, features and advantages of the present utility model will be more clear.
Fig. 1 is according to the schematic block diagram of the drive circuit of the multi-rotor aerocraft of prior art.
Fig. 2 is according to the schematic block diagram of the supply unit of the utility model embodiment.
Detailed description of the invention
Based on embodiment, the utility model is described below, but the utility model is not restricted to these embodiment. In below details of the present utility model being described, detailed some specific detail sections of having described. Do not have for a person skilled in the art the description of these detail sections can understand the utility model completely yet. For fear of obscuring essence of the present utility model, known method, process, flow process, element and circuit do not describe in detail.
In addition, it should be understood by one skilled in the art that the accompanying drawing providing at this is all for illustrative purposes, and accompanying drawing not necessarily in proportion draw.
, should be appreciated that in the following description, " circuit " refers to the galvanic circle being connected and composed by electrical connection or electromagnetism by least one element or electronic circuit meanwhile. In the time claiming that element or circuit " are connected to " another element or claim that element/circuit " is connected to " between two nodes, it can be directly couple or be connected to another element or can have intermediary element, and the connection between element can be physically, in logic or its combination. On the contrary, when claiming element " to be directly coupled to " or when " being directly connected to " another element, meaning that both do not exist intermediary element.
Unless context explicitly calls for, otherwise the implication that " comprising ", " comprising " etc. in whole description and claims, similar word should be interpreted as comprising instead of exclusive or exhaustive implication; That is to say, be the implication of " including but not limited to ".
In description of the present utility model, it will be appreciated that, term " first ", " second " etc. are only for describing object, and can not be interpreted as instruction or hint relative importance. In addition,, in description of the present utility model, except as otherwise noted, the implication of " multiple " is two or more.
Fig. 1 is according to the schematic block diagram of the drive circuit of the multi-rotor aerocraft of prior art. This multi-rotor aerocraft is as an example of unmanned plane. The drive circuit of multi-rotor aerocraft comprises main control module 101. Main control module 101 is powered by supply unit 102, for example lithium battery. Main control module 101 is from receiver 103 receiving remote control instructions or passback data, and generation control signal, provides respectively to electronic speed regulation module 104a-104d to control the rotating speed of motor M 1-M4. Blade is connected with motor, forms together screw. Can realize all directions and freely become rail and attitude adjustment by controlling the rotating speed of each screw.
In working order, many rotor systems change gyroplane rotate speed by the rotating speed that regulates motor M 1-M4, thereby realize lift variation and control heading. At floating state, the rotating speed of motor M 1-M4 remains on balancing speed, and the lift that rotor is produced equals the deadweight of aircraft. While movement in vertical direction, realize vertical lifting by the rotating speed that increases motor M 1-M4 simultaneously, realize vertical decline by reduce the rotating speed of motor M 1-M4 simultaneously. While movement in the horizontal direction, reduce along the rotating speed of preceding first motor of the direction of motion, increase along the rotating speed of posterior second motor of the direction of motion, maintain the balancing speed of all the other two motors simultaneously, make aircraft that inclination to a certain degree first occur, then produce proal thrust.
In many rotor systems of prior art, supply unit 102 comprises rechargeable battery, for example lithium battery. In this system, supply unit 102 is the whole system power supply that comprises power set. In the time that the electric weight of rechargeable battery exhausts, multi-rotor aerocraft may be owing to running out of steam or out of hand crash. Therefore, be subject to the appearance quantitative limitation of rechargeable battery the cruising time of multi-rotor aerocraft.
Fig. 2 is according to the schematic block diagram of the supply unit 102 of the utility model embodiment. Supply unit 102 is for being that main circuit 1000 is powered via output. With reference to Fig. 2, the supply unit 102 of the utility model embodiment is hybrid power source system, comprise power management module 1021, fuel cell 1022, DC-DC converter 1023, the first battery branch road and the second battery branch road, wherein, the first battery branch road and the second battery branch circuit parallel connection are between DC-DC converter 1023 and output. The first battery branch road comprises switch 1024, the first rechargeable battery 1026 and the switch 1028 of series connection successively; The second battery branch road comprises switch 1025, the second rechargeable battery 1027 and the switch 1029 of series connection successively.
Supply unit 102 is that main circuit 1000 is powered via output. Under the situation that is multi-rotor aerocraft at the unmanned plane that uses this supply unit 102, main circuit 1000 comprises the main control module 101 shown in Fig. 1, receiver 103, electronic speed regulation module 104a-104d. If multi-rotor aerocraft carries capture apparatus, capture apparatus can be arranged on The Cloud Terrace. Supply unit 102 is The Cloud Terrace power supply, utilizes the rotation sweep monitor area of The Cloud Terrace.
Fuel cell 1022 is for example the hydrogen fuel cell of high-energy-density, comprises fuel cell detection control apparatus, fuel cell auxiliary equipment and fuel cell pack. Fuel cell 1022 is not directly to load supplying.
The power stage of fuel cell 1022 is transformed to direct current output by DC-DC converter 1023, charges to the first rechargeable battery 1026 and the second rechargeable battery 1027.
The first rechargeable battery 1026 and the second rechargeable battery 1027 are connected in parallel between DC-DC converter 1023 and main circuit 1000, for main circuit 1000 is powered.
Switch 1024 is arranged between DC-DC converter 1023 and the first rechargeable battery 1026. Switch 1025 is arranged between DC-DC converter 1023 and the second rechargeable battery 1027. Switch 1028 is arranged between main circuit 1000 and the first rechargeable battery 1026. Switch 1029 is arranged between main circuit 1000 and the second rechargeable battery 1027.
Power management module 1021 is for monitoring the first rechargeable battery 1026 and the second rechargeable battery 1027, and disconnection and the closure of gauge tap 1024, switch 1025, switch 1028 and switch 1029. In the multi-rotor aerocraft shown in Fig. 1, if main control module 101 is carried out the function of power management module 1021, can save independent power management module 1021.
In the time that this supply unit 102 is worked, if the first rechargeable battery 1026 and the second rechargeable battery 1027 are all higher than first threshold (first threshold be for example Full Charge Capacity 20%), the first rechargeable battery 1026 is main circuit power supply, wherein, switch 1028 closures, switch 1024, switch 1025 and switch 1029 disconnect.
When power management module 1021 monitors the first rechargeable battery 1026 electric weight lower than first threshold, the second rechargeable battery 1027 electric weight are during higher than first threshold, gauge tap 1024 and switch 1029 closures, and switch 1025 and switch 1028 disconnect. The second rechargeable battery 1027 is main circuit power supply, and fuel cell 1022 charges to the first rechargeable battery 1026 simultaneously.
When power management module 1021 monitors the second rechargeable battery 1027 electric weight lower than first threshold, the first rechargeable battery 1026 electric weight are during higher than first threshold, gauge tap 1025 and switch 1028 closures, and switch 1024 and switch 1029 disconnect. The first rechargeable battery 1026 is main circuit power supply, and fuel cell 1021 charges to the second rechargeable battery 1027 simultaneously.
Supply unit switches between the first rechargeable battery 1026 and the second rechargeable battery 1027, can extend the time to main circuit power supply, improves cruising time.
The electric weight that monitors the first rechargeable battery 1026 and the second rechargeable battery 1027 when power management module 1021 is during all lower than first threshold, gauge tap 1024, switch 1025, switch 1028 and switch 1029 closures. The first rechargeable battery 1026 and the second rechargeable battery 1027 are powered to main circuit simultaneously, fuel cell 1022 charges to the first rechargeable battery 1026 and the second rechargeable battery 1027 simultaneously simultaneously, reduce single rechargeable battery unit interval energy output, make full use of rechargeable battery energy, extend cruising time.
In a preferred embodiment, the electric weight that monitors the first rechargeable battery 1026 and the second rechargeable battery 1027 when power management module 1021 is lower than first threshold, and when the electric weight of the first rechargeable battery 1026 and the second rechargeable battery 1027 equates, gauge tap 1024, switch 1025, switch 1028 and switch 1029 closures. The first rechargeable battery 1026 and the second rechargeable battery 1027 are simultaneously to main circuit power supply, and fuel cell 1022 charges to the first rechargeable battery 1026 and the second rechargeable battery 1027 simultaneously simultaneously.
Further, the utility model also provides a kind of unmanned plane, and this unmanned plane comprises the supply unit of above-mentioned arbitrary embodiment.
It should be noted that, fuel cell is due to the characteristic of its chemical reaction, specified or peak power is conventionally not high, and the power supply of unmanned plane is will be to motor power supplying to drive unmanned plane lift-off and flight, conventionally need higher instantaneous electric power, meet and this point fuel cell is more difficult. Meanwhile, fuel cell but has very high energy density.
Supply unit of the present utility model, comprises fuel cell and two rechargeable batteries of a high-energy-density. Wherein, rechargeable battery is main circuit power supply in turn, or is main circuit power supply simultaneously, and fuel cell is rechargeable battery charging. This supply unit has improved the cruising time of unmanned plane, and two rechargeable batteries redundancy backup each other is simultaneously stablized and safety UAS operation more.
In further improved embodiment, this supply unit can comprise the rechargeable battery of greater number, further improves the total capacity of rechargeable battery, extends cruising time and improves redundancy.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, to those skilled in the art, the utility model can have various changes and variation. All any amendments of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model within spirit of the present utility model and principle.
Claims (10)
1. a supply unit, for being main circuit power supply via output, is characterized in that, comprising:
Fuel cell;
DC-DC converter, for being transformed to charging current by the power stage of described fuel cell; And
Multiple battery branch roads of parallel connection between described DC-DC converter and described output,
Wherein, described multiple battery branch roads comprise respectively the first switch, rechargeable battery and the second switch of series connection successively, and described the first switch is connected to described DC-DC converter, and described second switch is connected to described output,
In power supply process, the second switch closure of at least one battery branch road of described multiple battery branch roads.
2. supply unit according to claim 1, it is characterized in that, also comprise power management module, described power management module monitors the electric weight of the rechargeable battery in described multiple battery branch roads, and controls disconnection and the closure of the switch in described multiple battery branch road.
3. supply unit according to claim 2, it is characterized in that, the electric weight of the rechargeable battery of described battery management module in the battery branch road detecting in described multiple battery branch road during higher than first threshold, disconnects the first switch of a described battery branch road and second switch closure.
4. supply unit according to claim 2, it is characterized in that, the electric weight of the rechargeable battery of described battery management module in two or more battery branch roads that detect in described multiple battery branch road is during higher than first threshold, the first switch of a battery branch road in described two or more battery branch roads is disconnected and second switch closure, and the first switch and the second switch of all the other the battery branch roads in described two or more battery branch roads are all disconnected.
5. supply unit according to claim 2, it is characterized in that, the electric weight of the rechargeable battery of described battery management module in the battery branch road detecting in described multiple battery branch road during lower than first threshold, disconnects the first switch closure of a described battery branch road and second switch.
6. supply unit according to claim 2, it is characterized in that, described battery management module, disconnects the first switch of described multiple battery branch roads and second switch closure during all lower than first threshold at the electric weight that the rechargeable battery in described multiple battery branch road detected.
7. supply unit according to claim 6, it is characterized in that, described battery management module at the electric weight that the rechargeable battery in described multiple battery branch road detected all lower than first threshold, and when the electric weight of the rechargeable battery in multiple battery branch roads equates, the first switch of described multiple battery branch roads is disconnected and second switch closure.
8. supply unit according to claim 1, is characterized in that, described rechargeable battery is lithium ion battery.
9. a unmanned plane, is characterized in that, comprising: supply unit, power set and main circuit described in claim 1-8 any one, wherein said supply unit is at least one power supply in described power set and described main circuit.
10. unmanned plane according to claim 9, is characterized in that, described unmanned plane is multi-rotor aerocraft, and wherein, described power set are motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520954157.8U CN205248837U (en) | 2015-11-25 | 2015-11-25 | Power supply unit and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520954157.8U CN205248837U (en) | 2015-11-25 | 2015-11-25 | Power supply unit and unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN205248837U true CN205248837U (en) | 2016-05-18 |
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| CN201520954157.8U Expired - Fee Related CN205248837U (en) | 2015-11-25 | 2015-11-25 | Power supply unit and unmanned aerial vehicle |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105977560A (en) * | 2016-07-22 | 2016-09-28 | 珠海银通农业科技有限公司 | Fuel cell system used in unmanned aerial vehicle |
| CN106043712A (en) * | 2016-06-23 | 2016-10-26 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle and starting method thereof |
| CN106410242A (en) * | 2016-11-02 | 2017-02-15 | 上海钧希新能源科技有限公司 | Monitoring system based on fuel cells |
| WO2018045848A1 (en) * | 2016-09-07 | 2018-03-15 | 亿航智能设备（广州）有限公司 | Feedback control method and device for power supply of multi-rotor manned aircraft |
| WO2018103576A1 (en) * | 2016-12-05 | 2018-06-14 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN108565506A (en) * | 2017-12-18 | 2018-09-21 | 广州亿航智能技术有限公司 | Unmanned plane battery and unmanned plane |
| CN108988470A (en) * | 2017-06-05 | 2018-12-11 | 深圳市道通智能航空技术有限公司 | Battery redundant circuit, unmanned vehicle and its battery powered control method |
-
2015
- 2015-11-25 CN CN201520954157.8U patent/CN205248837U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043712A (en) * | 2016-06-23 | 2016-10-26 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle and starting method thereof |
| CN106043712B (en) * | 2016-06-23 | 2023-12-08 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle and starting method thereof |
| CN105977560A (en) * | 2016-07-22 | 2016-09-28 | 珠海银通农业科技有限公司 | Fuel cell system used in unmanned aerial vehicle |
| WO2018045848A1 (en) * | 2016-09-07 | 2018-03-15 | 亿航智能设备（广州）有限公司 | Feedback control method and device for power supply of multi-rotor manned aircraft |
| CN106410242A (en) * | 2016-11-02 | 2017-02-15 | 上海钧希新能源科技有限公司 | Monitoring system based on fuel cells |
| WO2018103576A1 (en) * | 2016-12-05 | 2018-06-14 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| US10266264B2 (en) | 2016-12-05 | 2019-04-23 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10407171B2 (en) | 2016-12-05 | 2019-09-10 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10906643B2 (en) | 2016-12-05 | 2021-02-02 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US11498677B2 (en) | 2016-12-05 | 2022-11-15 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN108988470A (en) * | 2017-06-05 | 2018-12-11 | 深圳市道通智能航空技术有限公司 | Battery redundant circuit, unmanned vehicle and its battery powered control method |
| CN108565506A (en) * | 2017-12-18 | 2018-09-21 | 广州亿航智能技术有限公司 | Unmanned plane battery and unmanned plane |
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| CF01 | Termination of patent right due to non-payment of annual fee |