CN103332296A - Power supply for unmanned aerial vehicle - Google Patents
Power supply for unmanned aerial vehicle Download PDFInfo
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- CN103332296A CN103332296A CN2013103007864A CN201310300786A CN103332296A CN 103332296 A CN103332296 A CN 103332296A CN 2013103007864 A CN2013103007864 A CN 2013103007864A CN 201310300786 A CN201310300786 A CN 201310300786A CN 103332296 A CN103332296 A CN 103332296A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical group [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 230000005669 field effect Effects 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 229910044991 metal oxide Inorganic materials 0.000 claims description 3
- 150000004706 metal oxides Chemical class 0.000 claims description 3
- 238000005265 energy consumption Methods 0.000 abstract description 6
- 230000002159 abnormal effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The invention discloses a power supply for an unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles, and comprises a first power module, a second power module, a first voltage sensor, a second voltage sensor and a control module, wherein the first voltage sensor and the second voltage sensor are electrically connected with the first power module and the second power module respectively; the control module is used for controlling the first power module or the second power module to supply power for user equipment, acquiring the voltage detected by the first voltage sensor or the second voltage sensor, controlling the first power module or the second power module to stop supplying power and controlling the second power module or the first power module to supply power for the user equipment if the voltage detected by the first voltage sensor or the second voltage sensor is abnormal; the first power module and the second power module are arranged at the two ends of an aerial vehicle frame respectively. According to the technical scheme provided by the invention, the control precision is high, the flying action amplitude is small, the energy consumption is low, and the redundant backup of the power supply can be realized.
Description
Technical field
The present invention relates to the unmanned plane field, particularly a kind of unmanned plane power supply.
Background technology
Depopulated helicopter is called for short unmanned plane, is a kind of new ideas aircraft that is in developing rapidly, and it has maneuverability, reaction is quick, nobody flies, operation requires low advantage.Unmanned plane can be realized image real-time Transmission, high-risk regional detecting function by carrying multiclass sensor, is that the strong of satellite remote sensing and traditional air remote sensing replenishes.At present, the range of use of unmanned plane has been widened military affairs, scientific research, civilian three big fields, specifically in electric power, communication, meteorology, agricultural, ocean, exploration, photograph, prevent and reduce natural disasters, fields such as crops the yield by estimation, drug law enforcement anti-smuggling, border patrol, public security anti-terrorism use very wide.
Power supply is the important component part of unmanned plane, and power supply is usually designed to a standalone module in the prior art, is placed on the middle part of frame.
In realizing process of the present invention, the contriver finds that there is following problem at least in prior art:
Head will sink when unmanned plane accelerated, head will be faced upward during deceleration, power supply is installed in frame central, can makes that then the head of unmanned plane and tail weight are lighter, cause in the flight course, unmanned plane can obtain bigger angle and be used for adjusting and face upward or sink angle under air resistance and effect of inertia, therefore unmanned plane slow down or accelerator in, face upward or the angle of sinking need repeatedly be adjusted in order to reach suitable, control accuracy is low, the flare maneuver amplitude is big, the energy consumption height; When power supply breaks down, will cause unmanned plane to run out of steam simultaneously, and then bring danger such as air crash.
Summary of the invention
Higher in order to solve in the prior art unmanned plane energy consumption, and the low problem of control accuracy, the embodiment of the invention provides a kind of unmanned plane power supply.Described technical scheme is as follows:
The embodiment of the invention provides a kind of unmanned plane power supply, and described power supply comprises:
First power module is used to the consumer power supply of described unmanned plane;
The second source module is used to the consumer power supply of described unmanned plane;
First voltage sensor and second voltage sensor that is electrically connected with first power module and second source module respectively;
Control module, being used for control first power module or second source module is described user equipment power supply, and obtain the voltage that first voltage sensor or second voltage sensor senses arrive, when electric voltage exception that first voltage sensor that gets access to or second voltage sensor senses arrive, control first power module or the second source module is stopped power supply, and control second source module or first power module are described user equipment power supply;
Described first power module and described second source module are located at the two ends of frame respectively, and described consumer comprises motor, signal transmitting apparatus, cloud platform control system and flight control system.
In a kind of implementation of the embodiment of the invention, described first power module is identical with described second source module weight.
In the another kind of implementation of the embodiment of the invention, described first power module and described second source module include some series connected battery.
In the another kind of implementation of the embodiment of the invention, described battery is lithium cell.
In the another kind of implementation of the embodiment of the invention, described control module comprises programmable logic controller (PLC).
In the another kind of implementation of the embodiment of the invention, described power supply also comprises: two switches, the input end of two switches is electrically connected with described first power module and described second source module respectively, the control end of described two switches is electrically connected with described control module, and the mouth of described two switches is electrically connected with described consumer.
In the another kind of implementation of the embodiment of the invention, described switch is the metal-oxide half field effect transistor switch.
In the another kind of implementation of the embodiment of the invention, described power supply also comprises: be used for charging inlet that described first power module and described second source module are charged, described charging inlet is electrically connected with described first power module and described second source module respectively.
The beneficial effect that the technical scheme that the embodiment of the invention provides is brought is:
By the two ends in frame first power module and second source mould are set respectively, thereby make unmanned plane head and tail weight bigger, because head and the tail weight of unmanned plane are bigger, therefore in flight course, under air resistance and effect of inertia, can obtain less angle and be used for adjusting and face upward or the angle of sinking, so unmanned plane slow down or accelerator in, face upward or the angle of sinking only need be adjusted on a small quantity in order to reach suitable, the control accuracy height, the flare maneuver amplitude is little, and energy consumption is low; Simultaneously, be the user equipment power supply by one of them that control two power modules, and whether the voltage that detects this power module in real time is unusual, when electric voltage exception, switch the power module of power supply, realized the redundancy backup of power supply, avoided under the situation of a power module, when power supply breaks down, the danger that will cause unmanned plane to run out of steam.
Description of drawings
In order to be illustrated more clearly in the technical scheme in the embodiment of the invention, the accompanying drawing of required use is done to introduce simply in will describing embodiment below, apparently, accompanying drawing in describing below only is some embodiments of the present invention, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of the unmanned plane power supply that provides of the embodiment of the invention;
Fig. 2 is the structural representation of the unmanned plane power supply that provides of the embodiment of the invention.
The specific embodiment
For making the purpose, technical solutions and advantages of the present invention clearer, embodiment of the present invention is described further in detail below in conjunction with accompanying drawing.
Embodiment
The embodiment of the invention provides a kind of unmanned plane power supply, and referring to Fig. 1～2, described power supply comprises:
52 of first power module 51 and second source moulds are located at the two ends (being head and tail) of frame 6 respectively, and above-mentioned consumer includes but not limited to motor 1, signal transmitting apparatus 2, cloud platform control system 3 and flight control system 4.That is to say first power module 51 and second source mould 52 are separately positioned on head and tail, thereby make unmanned plane head and tail weight bigger, because head and the tail weight of unmanned plane are bigger, therefore in flight course, can obtain less angle under air resistance and effect of inertia is used for adjusting and faces upward or sink angle, therefore unmanned plane is in deceleration or accelerator, face upward or the angle of sinking only need be adjusted on a small quantity in order to reach suitable, the control accuracy height, the flare maneuver amplitude is little, energy consumption is low, realizes redundancy backup simultaneously under the control of control module 55.
Wherein, first power module 51 is equal in weight with second source module 52.
Particularly, first power module 51 and second source module 52 comprise the battery of equal number, and when the quantity of battery in first power module 51 greater than 1 the time, the battery series connection in first power module 51, the battery series connection in the second source module 52.For example, first power module 51 and second source module 52 include 6 batteries, these 6 battery series connection.In addition, the model of battery also can be identical in first power module 51 and the second source module 52.
Preferably, above-mentioned battery can be lithium cell.
Preferably, control module 55 can comprise programmable logic controller (PLC).
Further, power supply also comprises: two switches 56, the input end of two switches 56 is connected with the mouth of first power module 51 and second source module 52 respectively, and the control end of two switches 56 is electrically connected with control module 55, and the mouth of two switches 56 is electrically connected with consumer.
Preferably, above-mentioned switch can be the metal-oxide half field effect transistor switch.
Further, this power supply also comprises some filter circuits, and some filter circuits are located between first power module 51 and the consumer respectively and between second source module 52 and the consumer.Except above-mentioned filter circuit, between power supply and consumer, circuit components such as some electric capacity, inductance can also be set, be used for circuit is protected.
Further, this power supply also comprises: be used for charging inlet that first power module 51 and second source module 52 are charged, charging inlet is electrically connected with first power module 51 and second source module 52 respectively.
Further, above-mentioned electric voltage exception refers to the output voltage of first power module 51 or second source module 52 not in the range of nominal tension, causes that the reason of electric voltage exception comprises that power module damages, the power module electric weight is used up etc.
The embodiment of the invention arranges first power module and second source mould respectively by the two ends in frame, thereby make unmanned plane head and tail weight bigger, because head and the tail weight of unmanned plane are bigger, therefore in flight course, can obtain less angle under air resistance and effect of inertia is used for adjusting and faces upward or sink angle, therefore unmanned plane is in deceleration or accelerator, face upward or the angle of sinking only need be adjusted on a small quantity in order to reach suitable, the control accuracy height, the flare maneuver amplitude is little, and energy consumption is low; Simultaneously, be the user equipment power supply by one of them that control two power modules, and whether the voltage that detects this power module in real time is unusual, when electric voltage exception, switch the power module of power supply, realized the redundancy backup of power supply, avoided under the situation of a power module, when power supply breaks down, the danger that will cause unmanned plane to run out of steam.
The above only is preferred embodiment of the present invention, and is in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of doing, is equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (8)
1. a unmanned plane power supply is characterized in that, described power supply comprises:
First power module is used to the consumer power supply of described unmanned plane;
The second source module is used to the consumer power supply of described unmanned plane;
First voltage sensor and second voltage sensor that is electrically connected with described first power module and described second source module respectively;
Control module, being used for described first power module of control or described second source module is described user equipment power supply, and obtain the voltage that described first voltage sensor or described second voltage sensor senses arrive, when electric voltage exception that described first voltage sensor that gets access to or described second voltage sensor senses arrive, control described first power module or described second source module is stopped power supply, and control described second source module or described first power module is described user equipment power supply;
Described first power module and described second source module are located at the two ends of frame respectively, and described consumer comprises motor, signal transmitting apparatus, cloud platform control system and flight control system.
2. power supply according to claim 1 is characterized in that, described first power module is identical with described second source module weight.
3. power supply according to claim 1 and 2 is characterized in that, described first power module and described second source module include some series connected battery.
4. power supply according to claim 3 is characterized in that, described battery is lithium cell.
5. power supply according to claim 1 is characterized in that, described control module comprises programmable logic controller (PLC).
6. power supply according to claim 1, it is characterized in that, described power supply also comprises: two switches, the input end of two switches is connected with the mouth of described first power module and described second source module respectively, the control end of described two switches is electrically connected with described control module, and the mouth of described two switches is electrically connected with described consumer.
7. power supply according to claim 6 is characterized in that, described switch is the metal-oxide half field effect transistor switch.
8. power supply according to claim 1, it is characterized in that, described power supply also comprises: be used for charging inlet that described first power module and described second source module are charged, described charging inlet is electrically connected with described first power module and described second source module respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310300786.4A CN103332296B (en) | 2013-07-17 | 2013-07-17 | Power supply for unmanned aerial vehicle |
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| CN201310300786.4A CN103332296B (en) | 2013-07-17 | 2013-07-17 | Power supply for unmanned aerial vehicle |
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| CN103332296B CN103332296B (en) | 2017-02-08 |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104166355A (en) * | 2014-07-16 | 2014-11-26 | 深圳市大疆创新科技有限公司 | Electric unmanned aerial vehicle and intelligent electric quantity protection method |
| WO2015081636A1 (en) * | 2013-12-06 | 2015-06-11 | SZ DJI Technology Co., Ltd | Battery and unmanned aerial vehicle with the battery |
| WO2016008125A1 (en) * | 2014-07-16 | 2016-01-21 | 深圳市大疆创新科技有限公司 | Electric unmanned aerial vehicle and intelligent electric quantity protection method therefor |
| CN105656366A (en) * | 2016-02-26 | 2016-06-08 | 北京臻迪机器人有限公司 | Motor control device and motor control method |
| CN106334322A (en) * | 2015-07-16 | 2017-01-18 | 深圳曼塔智能科技有限公司 | Aircraft and power supply management system |
| CN106458324A (en) * | 2015-04-18 | 2017-02-22 | Adtex公司 | Unmanned Flying Body And Control Apparatus Therefor |
| US9592744B2 (en) | 2013-12-06 | 2017-03-14 | SZ DJI Technology Co., Ltd | Battery and unmanned aerial vehicle with the battery |
| CN106628215A (en) * | 2017-01-18 | 2017-05-10 | 广东容祺智能科技有限公司 | Alarming system for motor abnormity of unmanned aerial vehicle |
| WO2017113338A1 (en) * | 2015-12-31 | 2017-07-06 | SZ DJI Technology Co., Ltd. | Uav hybrid power systems and methods |
| WO2018027925A1 (en) * | 2016-08-12 | 2018-02-15 | 张琬彬 | Voltage distribution method and system for multiple motors of 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 |
| CN112769224A (en) * | 2021-02-22 | 2021-05-07 | 广东汇天航空航天科技有限公司 | Aircraft and flight control system's control circuit thereof |
| US11174021B2 (en) | 2016-03-24 | 2021-11-16 | Flir Detection, Inc. | Persistent aerial reconnaissance and communication system |
| US11368002B2 (en) | 2016-11-22 | 2022-06-21 | Hydro-Quebec | Unmanned aerial vehicle for monitoring an electrical line |
| US11417223B2 (en) | 2020-01-19 | 2022-08-16 | Flir Unmanned Aerial Systems Ulc | Flight altitude estimation systems and methods |
| US11423790B2 (en) | 2020-01-19 | 2022-08-23 | Flir Unmanned Aerial Systems Ulc | Tether management systems and methods |
| WO2022174580A1 (en) * | 2021-02-22 | 2022-08-25 | 广东汇天航空航天科技有限公司 | Aircraft, and control circuit of flight control system thereof |
| US11977395B2 (en) | 2016-03-24 | 2024-05-07 | Teledyne Flir Defense, Inc. | Persistent aerial communication and control system |
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Cited By (32)
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| US9592744B2 (en) | 2013-12-06 | 2017-03-14 | SZ DJI Technology Co., Ltd | Battery and unmanned aerial vehicle with the battery |
| WO2015081636A1 (en) * | 2013-12-06 | 2015-06-11 | SZ DJI Technology Co., Ltd | Battery and unmanned aerial vehicle with the battery |
| US10625613B2 (en) | 2013-12-06 | 2020-04-21 | SZ DJI Technology Co., Ltd. | Battery and unmanned aerial vehicle with the battery |
| US10525832B2 (en) | 2013-12-06 | 2020-01-07 | SZ DJI Technology Co., Ltd. | Battery and unmanned aerial vehicle with the battery |
| US10906427B2 (en) | 2013-12-06 | 2021-02-02 | SZ DJI Technology Co., Ltd. | Battery and unmanned aerial vehicle with the battery |
| US11607972B2 (en) | 2013-12-06 | 2023-03-21 | SZ DJI Technology Co., Ltd. | Battery and unmanned aerial vehicle with battery indicator and venting opening |
| US11853057B2 (en) | 2014-07-16 | 2023-12-26 | SZ DJI Technology Co., Ltd. | Electric unmanned aerial vehicle and an intelligent method of protecting electricity thereof |
| CN104166355A (en) * | 2014-07-16 | 2014-11-26 | 深圳市大疆创新科技有限公司 | Electric unmanned aerial vehicle and intelligent electric quantity protection method |
| US10996670B2 (en) | 2014-07-16 | 2021-05-04 | SZ DJI Technology Co., Ltd. | Electric unmanned aerial vehicle and an intelligent method of protecting electricity thereof |
| WO2016008125A1 (en) * | 2014-07-16 | 2016-01-21 | 深圳市大疆创新科技有限公司 | Electric unmanned aerial vehicle and intelligent electric quantity protection method therefor |
| US10372124B2 (en) | 2014-07-16 | 2019-08-06 | SZ DJI Technology Co., Ltd. | Electric unmanned aerial vehicle and an intelligent method of protecting electricity thereof |
| CN106458324A (en) * | 2015-04-18 | 2017-02-22 | Adtex公司 | Unmanned Flying Body And Control Apparatus Therefor |
| CN106458324B (en) * | 2015-04-18 | 2020-12-15 | Adtex公司 | Unmanned flying object and control device thereof |
| CN106334322A (en) * | 2015-07-16 | 2017-01-18 | 深圳曼塔智能科技有限公司 | Aircraft and power supply management system |
| WO2017113338A1 (en) * | 2015-12-31 | 2017-07-06 | SZ DJI Technology Co., Ltd. | Uav hybrid power systems and methods |
| CN108432076B (en) * | 2015-12-31 | 2020-08-25 | 深圳市大疆创新科技有限公司 | UAV hybrid power system and method |
| CN108432076A (en) * | 2015-12-31 | 2018-08-21 | 深圳市大疆创新科技有限公司 | UAV hybrid power systems and method |
| US10501195B2 (en) | 2015-12-31 | 2019-12-10 | SZ DJI Technology Co., Ltd. | UAV hybrid power systems and methods |
| US11228200B2 (en) | 2015-12-31 | 2022-01-18 | SZ DJI Technology Co., Ltd. | UAV hybrid power systems and methods |
| CN105656366A (en) * | 2016-02-26 | 2016-06-08 | 北京臻迪机器人有限公司 | Motor control device and motor control method |
| CN105656366B (en) * | 2016-02-26 | 2019-04-26 | 北京臻迪机器人有限公司 | A kind of motor control assembly and motor control method |
| US11977395B2 (en) | 2016-03-24 | 2024-05-07 | Teledyne Flir Defense, Inc. | Persistent aerial communication and control system |
| US11174021B2 (en) | 2016-03-24 | 2021-11-16 | Flir Detection, Inc. | Persistent aerial reconnaissance and communication system |
| WO2018027925A1 (en) * | 2016-08-12 | 2018-02-15 | 张琬彬 | Voltage distribution method and system for multiple motors of 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 |
| US11368002B2 (en) | 2016-11-22 | 2022-06-21 | Hydro-Quebec | Unmanned aerial vehicle for monitoring an electrical line |
| CN106628215A (en) * | 2017-01-18 | 2017-05-10 | 广东容祺智能科技有限公司 | Alarming system for motor abnormity of unmanned aerial vehicle |
| US11417223B2 (en) | 2020-01-19 | 2022-08-16 | Flir Unmanned Aerial Systems Ulc | Flight altitude estimation systems and methods |
| US11423790B2 (en) | 2020-01-19 | 2022-08-23 | Flir Unmanned Aerial Systems Ulc | Tether management systems and methods |
| WO2022174580A1 (en) * | 2021-02-22 | 2022-08-25 | 广东汇天航空航天科技有限公司 | Aircraft, and control circuit of flight control system thereof |
| CN112769224B (en) * | 2021-02-22 | 2024-04-26 | 广东汇天航空航天科技有限公司 | Aircraft and control circuit of flight control system thereof |
| CN112769224A (en) * | 2021-02-22 | 2021-05-07 | 广东汇天航空航天科技有限公司 | Aircraft and flight control system's control circuit thereof |
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