WO2018205167A1 - 电池管理系统、电池和无人飞行器 - Google Patents

电池管理系统、电池和无人飞行器 Download PDF

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Publication number
WO2018205167A1
WO2018205167A1 PCT/CN2017/083786 CN2017083786W WO2018205167A1 WO 2018205167 A1 WO2018205167 A1 WO 2018205167A1 CN 2017083786 W CN2017083786 W CN 2017083786W WO 2018205167 A1 WO2018205167 A1 WO 2018205167A1
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WIPO (PCT)
Prior art keywords
interface
battery
management system
circuit
aerial vehicle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2017/083786
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English (en)
French (fr)
Inventor
罗昊
郑大阳
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to PCT/CN2017/083786 priority Critical patent/WO2018205167A1/zh
Priority to CN201780006395.8A priority patent/CN108778929A/zh
Publication of WO2018205167A1 publication Critical patent/WO2018205167A1/zh
Priority to US16/677,046 priority patent/US20200076205A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/60—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/425—Structural combination with electronic components, e.g. electronic circuits integrated to the outside of the casing
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/44—Methods for charging or discharging
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or discharging batteries or for supplying loads from batteries
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or discharging batteries or for supplying loads from batteries
    • H02J7/50—Circuit arrangements for charging or discharging batteries or for supplying loads from batteries acting upon multiple batteries simultaneously or sequentially
    • H02J7/52—Circuit arrangements for charging or discharging batteries or for supplying loads from batteries acting upon multiple batteries simultaneously or sequentially for charge balancing, e.g. equalisation of charge between batteries
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2200/00—Type of vehicles
    • B60L2200/10—Air crafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/425—Structural combination with electronic components, e.g. electronic circuits integrated to the outside of the casing
    • H01M2010/4271—Battery management systems including electronic circuits, e.g. control of current or voltage to keep battery in healthy state, cell balancing
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2220/00—Batteries for particular applications
    • H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2105/00—Networks for supplying or distributing electric power characterised by their spatial reach or by the load
    • H02J2105/30—Networks for supplying or distributing electric power characterised by their spatial reach or by the load the load networks being external to vehicles, i.e. exchanging power with vehicles
    • H02J2105/32—Networks for supplying or distributing electric power characterised by their spatial reach or by the load the load networks being external to vehicles, i.e. exchanging power with vehicles for aircrafts
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or discharging batteries or for supplying loads from batteries
    • H02J7/865—Battery or charger load switching, e.g. concurrent charging and load supply
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/70—Energy storage systems for electromobility, e.g. batteries
    • 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
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/10—Technologies relating to charging of electric vehicles
    • Y02T90/16—Information or communication technologies improving the operation of electric vehicles

Definitions

  • Embodiments of the present invention relate to the field of drone technology, and in particular, to a battery management system, a battery, and an unmanned aerial vehicle.
  • the battery on the UAV has a limited storage capacity, and generally provides an unmanned aerial vehicle for 20-30 minutes of operation.
  • the battery has only one charge and discharge port.
  • the battery power is low, the battery needs to be detached from the unmanned aerial vehicle, and then the battery is charged through the charge and discharge port, because the battery is detached from the unmanned aerial vehicle, The unmanned aerial vehicle cannot be powered during the charging process of the battery, causing the unmanned aerial vehicle to be inoperable.
  • Embodiments of the present invention provide a battery management system, a battery, and an unmanned aerial vehicle for charging and discharging without a battery to extend the life time of the UAV.
  • an embodiment of the present invention provides a battery management system, including: a first interface, a second interface, and a controller; and the controller is respectively connected to the first interface and the second interface; The first interface is for charging and discharging, and the second interface is for charging.
  • One end of the first interface is used for connection with an external power supply or an unmanned aerial vehicle, and the other end of the first interface is used for connecting with a battery cell; and one end of the second interface is used for external power supply. Connected, the other end of the second interface is for connecting with the battery cell.
  • the controller is configured to control a circuit guide between the first interface and the battery core when detecting that the first interface is electrically connected to the unmanned aerial vehicle, and the second interface is electrically connected to the external power supply And controlling a circuit between the second interface and the battery cell.
  • a first switch is disposed between the other end of the second interface and the battery cell.
  • the controller is specifically configured to: control closing or opening of the first switch to control the The circuit between the second interface and the battery cell is turned on or off.
  • the first switch is respectively connected to the second interface, and a preset position of a circuit between the first interface and the battery cell.
  • the first switch is a MOS tube or a solid state relay.
  • the MOS transistors are back-to-back MOS tubes.
  • the controller is further configured to control the first interface when detecting that the first interface is electrically connected to the unmanned aerial vehicle, and the second interface is not electrically connected to an external power supply Conducting a circuit between the battery and the battery; and controlling disconnection of the circuit between the second interface and the battery.
  • the controller is further configured to control circuit conduction between the first interface and the battery when detecting that the first interface electrically connects an external power supply, and A circuit between the second interface and the battery cell is controlled to be disconnected.
  • the controller is further configured to: when detecting that the first interface is not electrically connected to an external power supply or an unmanned aerial vehicle, and the second interface is electrically connected to an external power supply, The second interface is electrically connected to the circuit between the cells.
  • a second switch is disposed between the first interface and the battery cell.
  • the controller is specifically configured to: control closing or opening of the second switch to control a circuit between the first interface and the battery cell to be turned on or off.
  • a first switch is disposed between the second interface and the battery, and the first switch is respectively connected to the second interface, and the first interface and the battery core
  • the preset position of the circuit is between; the second switch is located between the battery cell and the preset position.
  • the second switch is a MOS tube or a relay.
  • the MOS transistors are back-to-back MOS tubes.
  • the second interface is for charging only.
  • the second interface is also used for discharging.
  • the controller is further configured to control a circuit between the first interface and the battery core when detecting that the first interface is electrically connected to the unmanned aerial vehicle, and the second interface is electrically connected to the external power supply Disconnecting; and controlling circuit conduction between the second interface and the first interface.
  • an embodiment of the present invention provides a battery, including: a battery core, and the battery management system according to any one of the embodiments of the present invention.
  • the battery management system is configured to control charging and discharging of the battery cells.
  • an embodiment of the present invention provides an unmanned aerial vehicle, including: a rack, a power system, and a battery.
  • the battery management system of any one of the embodiments of the present invention is provided in the rack; the battery is disposed in a battery compartment of the rack; and the battery management system is configured to control power of the battery Charge and discharge of the core.
  • an embodiment of the present invention provides an unmanned aerial vehicle, including: a rack, a power system, and a battery according to the second aspect of the present invention.
  • the battery is disposed within a battery compartment of the rack.
  • an embodiment of the present invention provides a computer readable storage medium, which enables a battery management system to perform the battery management system according to the first aspect of the present application when the instructions in the storage medium are executed by the battery management system. Program.
  • the battery management system, the battery and the unmanned aerial vehicle provided by the embodiments of the present invention control the first interface and the battery core when the first interface is electrically connected to the unmanned aerial vehicle and the second interface is electrically connected to the external power supply.
  • the circuit is turned on, and the circuit between the second interface and the battery cell is controlled to be turned on. Therefore, in this embodiment, the discharge function of the first interface and the charging function of the second interface are simultaneously realized, so that the external power supply supplies power to the battery core.
  • the battery core discharges to the unmanned aerial vehicle. Therefore, when the battery is exhausted, it is not necessary to take out the battery from the unmanned aerial vehicle, thereby increasing the length of time that the battery continues to supply power to the unmanned aerial vehicle, thereby extending the unmanned aerial vehicle. Life time improves the user experience.
  • FIG. 1 is a schematic structural diagram of a battery management system according to Embodiment 1 of the present invention.
  • FIG. 2 is a schematic structural diagram of a battery management system according to Embodiment 2 of the present invention.
  • FIG. 3 is a schematic structural diagram of a battery management system according to Embodiment 3 of the present invention.
  • FIG. 4 is a schematic structural diagram of a battery management system according to Embodiment 4 of the present invention.
  • FIG. 5 is a schematic structural diagram of a battery management system according to Embodiment 5 of the present invention.
  • FIG. 6 is a schematic structural diagram of a battery according to an embodiment of the present invention.
  • FIG. 7 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 8 is a schematic structural diagram of an unmanned aerial vehicle according to another embodiment of the present invention.
  • the battery management system of this embodiment may include: a first interface 110, a second interface 120, and a controller 130.
  • the controller 130 is communicably connected to the first interface 110 and the second interface 120 respectively.
  • the first interface 110 is used for charging and discharging, that is, a charging and discharging interface.
  • the second interface 120 is used for charging, that is, a charging interface.
  • one end of the first interface 110 is used for connection with an external power supply or an unmanned aerial vehicle, and the other end of the first interface 110 is used for connection with a battery cell of the battery. Therefore, when the other end of the first interface is connected to the battery cell, and one end of the first interface 110 is connected to an external power source, the first interface 110 can be used for charging. When the other end of the first interface 110 is connected to the battery cell, and one end of the first interface 110 is connected to the UAV, the first interface 110 can be used for discharging.
  • one end of the second interface 120 is for connection with an external power source, and the other end of the second interface 120 is for connection with a battery cell of the battery.
  • the second interface 120 can be used for charging when one end of the second interface 120 is connected to an external power source and the other end of the second interface 120 is connected to the battery cells.
  • the controller 130 is configured to control between the first interface 110 and the battery core when detecting that the first interface 110 is electrically connected to the unmanned aerial vehicle, and the second interface 120 is electrically connected to the external power supply.
  • the circuit is turned on; and the circuit between the second interface 120 and the cell is controlled to be turned on.
  • the controller 130 can detect whether the first interface 110 is electrically connected to the unmanned aerial vehicle.
  • the battery can discharge the unmanned aerial vehicle through the first interface 110.
  • the embodiment controls the circuit between the first interface 110 and the cell to be turned on, for example, the control cell is turned on to the discharge circuit of the first interface 110, and the circuit between the cell and the first interface 110 is turned on.
  • the first interface 110 is connected to the UAV, Therefore, the battery core discharges to the unmanned aerial vehicle through the first interface 110, and the discharge function of the first interface 110 is realized.
  • the controller 130 can also detect whether the second interface 120 is electrically connected to the external power supply.
  • the battery When detecting that the second interface 120 is electrically connected to the external power supply, the battery can be charged through the second interface 120, and then the second interface is controlled by the embodiment.
  • the circuit between the 120 and the battery cell is turned on, for example, the second interface is controlled to be electrically connected to the charging circuit of the battery cell, and in the case where the circuit between the battery cell and the second interface 120 is turned on, and the second interface 120 is The external power supply is connected, so that the battery core is charged through the second interface 120, and the charging function of the second interface 120 is realized.
  • the present embodiment simultaneously realizes the discharge function of the first interface and the charging function of the second interface, so that the external power supply supplies power to the battery core while the battery core discharges to the unmanned aerial vehicle.
  • the battery is exhausted, it is not necessary to take the battery out of the unmanned aerial vehicle, which increases the length of time the battery continues to supply power to the unmanned aerial vehicle. Therefore, the life of the unmanned aerial vehicle is extended and the user experience is improved.
  • the controller 130 is further configured to control the first interface and the battery core when detecting that the first interface 110 is electrically connected to the unmanned aerial vehicle, and the second interface 120 is not electrically connected to the external power supply.
  • the circuit between the electrodes is turned on; and the circuit between the second interface and the cell is controlled to be disconnected.
  • the controller 130 of the embodiment can detect that the first interface 110 is electrically connected.
  • the human aircraft indicates that the battery can discharge the unmanned aerial vehicle through the first interface 110, and then the embodiment controls the circuit between the first interface 110 and the battery core to be turned on, for example, the discharge circuit of the control battery to the first interface 110.
  • the circuit between the battery cell and the first interface 110 is turned on, and the first interface 110 is connected to the UAV, the battery cell is discharged to the UAV through the first interface 110.
  • the discharge function of the first interface 110 is performed.
  • the controller 130 of the embodiment can also detect that the second interface 120 is not electrically connected to the external power supply, indicating that the battery core does not need to be charged through the second interface 120, and then the embodiment controls the second interface 120 and the battery core.
  • the circuit is disconnected, for example, by controlling the second interface to disconnect the charging circuit of the battery cell, and in the case where the circuit between the battery cell and the second interface 120 is disconnected, the occurrence of a short circuit is avoided.
  • the cells can be discharged only at the same time.
  • the controller 130 is further configured to: when detecting that the first interface 110 is electrically connected to an external power supply, control circuit conduction between the first interface 110 and the battery cell, and control the second The interface 120 is disconnected from the circuit between the cells.
  • the controller 130 of the embodiment can detect that the first interface 110 is electrically connected to the unmanned aerial vehicle, and the battery can be charged through the first interface 110. Then, the embodiment controls the circuit between the first interface 110 and the cell to be turned on, for example, the first interface 110 is controlled to conduct the charging circuit of the cell, and the circuit between the cell and the first interface 110 is turned on. Next, the first interface 110 is connected to an external power supply, so that the electric core is charged through the first interface 11, and the charging function of the first interface 110 is realized.
  • the battery when the first interface 110 is electrically connected to the external power supply, the battery does not need to be charged through the second interface 120, regardless of whether the second interface 120 is electrically connected to the external power supply, and then the second interface 120 is controlled by the current embodiment.
  • the circuit between the cores is broken, for example, the charging circuit of the second interface 120 is controlled to be disconnected from the battery cell, and in the case where the circuit between the battery cell and the second interface 120 is disconnected, the occurrence of a short circuit is avoided.
  • the controller 130 is further configured to: when detecting that the first interface 110 is not electrically connected to an external power supply or an unmanned aerial vehicle, and the second interface 120 is electrically connected to an external power supply, control the second interface The circuit between the cells is electrically connected.
  • the controller 130 of the embodiment can detect that the first interface 110 is not electrically connected to the UAV, nor Electrically connecting the external power supply, indicating that the battery core does not need to be charged through the first interface 110, and does not need to be discharged through the first interface 110, and then the embodiment can control the circuit disconnection between the first interface 110 and the battery core, or The circuit between the first interface 110 and the battery cell is controlled to be turned on. Since the first interface 110 is a charging and discharging interface and has a secure connector, there is no risk of short circuit.
  • the controller 130 of the embodiment further detects that the second interface 120 is electrically connected to the external power supply, indicating that the battery core can be charged through the second interface 120, and then the embodiment controls the circuit between the second interface 120 and the battery core. Turning on, for example, controlling the second interface 120 to conduct the charging circuit of the battery cell, in the case where the circuit between the battery cell and the second interface 120 is turned on, and the second interface 120 is connected to the external power supply, The battery core is charged through the second interface 120 to implement the charging function of the second interface 120.
  • the battery cells can be charged through only one charging interface at the same time.
  • FIG. 2 is a schematic structural diagram of a battery management system according to Embodiment 2 of the present invention, as shown in FIG. 2,
  • the battery management system of the present embodiment is based on the embodiment shown in FIG. 1.
  • the first switch 121 is disposed between the other end of the second interface 120 of the present embodiment and the battery core.
  • the first switch 121 can be used to control the conduction or disconnection of the circuit between the second interface 120 and the cell.
  • one implementation manner of the controller 130 controlling the circuit between the second interface and the battery cell is that the controller 130 controls the closing or opening of the first switch 121.
  • the controller 130 controls the first switch 121 to close when it is required to control the conduction between the second interface 120 and the battery cell.
  • the first switch 121 is controlled to be turned off.
  • the first switch 121 is respectively connected to the second interface 120, and a preset position of a circuit between the first interface 110 and the battery cell. That is, the other end of the second interface 120 is for connecting a preset position of the circuit between the first interface and the battery cell.
  • the controller controls the first switch 121, the circuit between the battery cell and the first interface 110 is not affected.
  • the first switch 121 is a MOS tube or a solid state relay.
  • the first switch 121 when the first switch 121 is a MOS tube, the first switch 121 can be a single MOS tube, so that when the battery core is not charged through the second interface 120, the second interface 120 can be exposed outside, so that the battery
  • the battery charging application scenario is more convenient, and has safe and reliable characteristics to avoid the occurrence of short circuit.
  • the first switch 121 when the first switch 121 is a MOS transistor, the first switch 121 may be a back-to-back MOS tube, so that current backflow can be prevented.
  • FIG. 3 is a schematic structural diagram of a battery management system according to Embodiment 3 of the present invention. As shown in FIG. 3, the battery management system of this embodiment is based on any of the foregoing embodiments.
  • a second switch 111 is disposed between the cores. The second switch 111 can be used to control the conduction or disconnection of the circuit between the first interface 110 and the battery cells.
  • one implementation manner of the controller 130 controlling the circuit between the first interface 110 and the battery cell is that the controller 130 controls the closing or opening of the second switch 111.
  • the controller 130 controls the second switch 111 to close when it is required to control the conduction between the first interface 110 and the battery cell.
  • the second switch 111 is controlled to be turned off.
  • the second switch 111 is controlled to be disconnected, it is possible to control the first interface 110 to stop charging the battery and stop discharging the battery to ensure the safety of the battery.
  • FIG. 4 is a schematic structural diagram of a battery management system according to Embodiment 4 of the present invention. As shown in FIG. 4, the battery management system of this embodiment is based on the embodiment shown in FIG. A first switch 121 is disposed between the cores, and the first switch 121 is respectively connected to the second interface 120, and a preset position of the circuit between the first interface 110 and the battery cell; The second switch 111 is located between the battery core and the preset position.
  • the first switch 121 is controlled to be closed, and the second switch 111 is controlled to be turned off.
  • the first switch 121 is controlled to be closed, and the second switch 111 is controlled to be closed.
  • the battery can be discharged through the first interface 110 at this time.
  • the second switch 111 is a MOS tube or a solid state relay.
  • the second switch 111 when the second switch 111 is a MOS transistor, the second switch 111 may be a single MOS transistor.
  • the second switch 111 when the second switch 111 is a MOS transistor, the second switch 111 may be a back-to-back MOS tube, which prevents current from flowing back.
  • the first switch 121 when the second switch 111 is a back-to-back MOS transistor, the first switch 121 may be a separate MOS transistor.
  • the battery management system of the embodiment of the present invention includes two charging interfaces (P1+, P2+), wherein P1+ has a charging and discharging function, and P2+ has a charging function.
  • the P2+ is controlled by a single MOS transistor. In the non-charging mode, the P2+ can be exposed, which makes the charging application scene more convenient, and has safe and reliable characteristics, avoiding the occurrence of short circuit.
  • the specific working process is as follows: When charging the battery core with P1+, S2 and S3 are turned on, and S1 is turned off. At this time, P2+ has no voltage to prevent external short circuit; when using P2+ for charging, S1, S2, and S3 are all turned on. At this time, P1+ can be used to supply power to the outside (such as an unmanned aerial vehicle). Since the P1+ is an ordinary charging/discharging interface, it is usually designed with a safety connector and there is no risk of short circuit.
  • the foregoing second interface 120 is only used for charging. That is, the second interface 120 does not have a function of discharging the battery, so that the second interface 120 is a dedicated charging port.
  • the second interface 120 of the embodiment may be a bare metal device.
  • the second interface 120 is further used for discharging in an application scenario.
  • the controller 130 is further configured to detect that the first interface 110 is electrically connected to the unmanned aerial vehicle. And controlling the circuit between the first interface 110 and the battery cell to be disconnected when the second interface 120 is electrically connected to the external power supply; and controlling the second interface 120 and the first interface 110 The circuit is turned on.
  • the UAV When the first interface 110 is connected to the UAV and the second interface 120 is connected to the external power supply, the UAV can be powered by the first interface 110, and the second interface 120 has a discharge function, which is equivalent to The external power supply is discharged through the second interface 120. Therefore, the first interface 110 and the second interface 120 can realize direct power supply to the unmanned aerial vehicle by the external power supply without passing through the battery cells. Therefore, the controller 130 of the embodiment controls the circuit between the first interface 110 and the battery cell to be disconnected. Therefore, the battery core does not supply power to the unmanned aerial vehicle through the first interface 110, and the controller 130 of the embodiment further The circuit between the second interface 120 and the first interface 110 is controlled to be turned on, which is equivalent to turning on the circuit between the external power supply and the unmanned aerial vehicle. At this time, the external power supply can directly supply power to the unmanned aerial vehicle. Through the above scheme, the external power supply directly supplies power to the unmanned aerial vehicle through the first interface and the second interface.
  • the external power supply may be a charging treasure, that is, a charging treasure of the unmanned aerial vehicle.
  • a charging treasure that is, a charging treasure of the unmanned aerial vehicle.
  • FIG. 6 is a schematic structural diagram of a battery according to an embodiment of the present invention.
  • the battery of this embodiment may include: a battery management system 100 and a battery core 200, wherein the battery management system 100 is used. The charging and discharging of the battery cell 200 are controlled.
  • the battery management system 100 can adopt the structure of any device embodiment of FIG. 1 to FIG. 5, and the implementation principle and technical effects are similar, and details are not described herein again.
  • FIG. 7 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.
  • the unmanned aerial vehicle 1000 of the present embodiment includes a rack 1100, a power system 1200, and a battery 1300.
  • a battery management system 1110 is disposed in the rack 1100; the battery 1300 is disposed in a battery compartment of the rack 1100; and the battery management system 1110 is configured to control charging and discharging of the battery cells of the battery 1300.
  • the battery management system 1110 can adopt the structure of any device embodiment of FIG. 1 to FIG. 5, and the implementation principle and technical effects are similar, and details are not described herein again.
  • FIG. 8 is a schematic structural diagram of an unmanned aerial vehicle according to another embodiment of the present invention.
  • the unmanned aerial vehicle 2000 of the present embodiment includes: a rack 2100, a power system 2200, and a battery 2300.
  • the battery 2300 is disposed within a battery compartment of the rack 2100.
  • the battery 2300 can adopt the structure of the device embodiment shown in FIG. 6, and the implementation principle and technical effects are similar, and details are not described herein again.
  • the above power system may include: an electric adjustment, a motor and a propeller, and the ESC is electrically connected to the flight controller and the motor in the rack respectively; thereby providing power to the UAV for flight.
  • the foregoing program may be stored in a computer readable storage medium, and the program is executed when executed.
  • the foregoing storage medium includes: read-only memory (ROM), random access memory (RAM), magnetic disk or optical disk, and the like, which can store program codes. Medium.

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Abstract

一种电池管理系统、电池和无人飞行器，电池管理系统包括：第一接口(110)、第二接口(120)和与第一接口(110)、第二接口(120)通信连接的控制器(130)。第一接口(110)的一端与外部供电源连接或无人飞行器连接，另一端与电池的电芯连接。第二接口(120)的一端与外部供电源连接，另一端与电芯连接。控制器(130)在检测到第一接口(110)电连接无人飞行器，且第二接口(120)电连接外部供电源时，控制第一接口(110)与电芯之间的电路以及第二接口(120)与电芯之间的电路导通，使得外部供电源向电芯供电时电芯向无人飞行器放电；在电池的电量耗尽时无需将电池从无人飞行器中取出充电，以提高电池持续向无人飞行器供电的时长，延长无人飞行器的续航时间，改善用户体验。

Description

电池管理系统、电池和无人飞行器 技术领域
本发明实施例涉及无人机技术领域，尤其涉及一种电池管理系统、电池和无人飞行器。
背景技术
目前的无人飞行器通过其上承载的电池来提供电能，以助于无人飞行器上电工作。但是目前，无人飞行器上的电池的蓄电能力有限，一般能提供无人飞行器工作20-30分钟的电量。目前，电池只有一个充放电口，在电池的电量低时，需要将电池从无人飞行器中脱离出，然后通过该充放电口对电池进行充电将，由于电池从无人飞行器中脱离，所以在电池的充电过程中无法对无人飞行器供电，造成无人飞行器无法工作。
发明内容
本发明实施例提供一种电池管理系统、电池和无人飞行器，用于使得无电池同时充电和放电，以延长无人飞行器的续航时间。
第一方面，本发明实施例提供一种电池管理系统，包括：第一接口、第二接口和控制器；所述控制器分别与所述第一接口、所述第二接口通信连接；所述第一接口用于充电和放电，所述第二接口用于充电。
所述第一接口的一端用于与外部供电源连接或者无人飞行器连接，所述第一接口的另一端用于与电池的电芯连接；所述第二接口的一端用于与外部供电源连接，所述第二接口的另一端用于与所述电芯连接。
所述控制器，用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通；以及控制所述第二接口与所述电芯之间的电路导通。
在一种可能的设计中，所述第二接口的另一端与所述电芯之间设置有第一开关。
所述控制器，具体用于：控制所述第一开关的闭合或者断开，以控制所 述第二接口与所述电芯之间的电路导通或断开。
在一种可能的设计中，所述第一开关分别连接于所述第二接口，以及所述第一接口与所述电芯之间的电路的预设位置。
在一种可能的设计中，所述第一开关为MOS管或者固态继电器。
在一种可能的设计中，所述MOS管为背对背的MOS管。
在一种可能的设计中，所述控制器，还用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口未电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通；以及控制所述第二接口与所述电芯之间的电路断开。
在一种可能的设计中，所述控制器，还用于在检测到所述第一接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通，以及控制所述第二接口与所述电芯之间的电路断开。
在一种可能的设计中，所述控制器，还用于在检测到所述第一接口未电连接外部供电源或无人飞行器，所述第二接口电连接外部供电源时，控制所述第二接口与所述电芯之间的电路导通。
在一种可能的设计中，所述第一接口与所述电芯之间设置有第二开关。
所述控制器，具体用于：控制所述第二开关的闭合或者断开，以控制所述第一接口与所述电芯之间的电路导通或断开。
在一种可能的设计中，在第二接口与电芯之间设置有第一开关，且所述第一开关分别连接于所述第二接口，以及所述第一接口与所述电芯之间的电路的预设位置时；所述第二开关位于所述电芯与所述预设位置之间。
在一种可能的设计中，所述第二开关为MOS管或者继电器。
在一种可能的设计中，所述MOS管为背对背的MOS管。
在一种可能的设计中，所述第二接口仅用于充电。
在一种可能的设计中，所述第二接口还用于放电。
所述控制器，还用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路断开；以及控制所述第二接口与所述第一接口之间的电路导通。
第二方面，本发明实施例提供一种电池，包括：电芯和第一方面本发明实施例任一所述的电池管理系统。
其中，所述电池管理系统，用于控制所述电芯的充放电。
第三方面，本发明实施例提供一种无人飞行器，包括：机架、动力系统和电池。
所述机架内设置有第一方面本发明实施例任一所述的电池管理系统；所述电池设置在所述机架的电池仓内；所述电池管理系统用于控制所述电池的电芯的充放电。
第四方面，本发明实施例提供一种无人飞行器，包括：机架、动力系统和第二方面本发明实施例所述的电池。所述电池设置在所述机架的电池仓内。
第五方面，本发明实施例提供一种计算机可读存储介质，当存储介质中的指令由电池管理系统执行时，使得电池管理系统能够执行第一方面本申请实施例所述的电池管理系统的方案。
本发明实施例提供的电池管理系统、电池和无人飞行器，通过在检测到第一接口电连接无人飞行器，以及第二接口电连接外部供电源时，控制第一接口与电芯之间的电路导通，以及控制第二接口与电芯之间的电路导通，因此，本实施例同时实现了第一接口的放电功能以及第二接口的充电功能，使得外部供电源向电芯供电的同时电芯向无人飞行器放电，因此，在电池的电量耗尽时，无需将电池从无人飞行器中取出充电，提高了电池持续向无人飞行器供电的时长，因此，延长了无人飞行器的续航时间，改善了用户体验。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作一简单地介绍，显而易见地，下面描述中的附图是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1为本发明实施例一提供的电池管理系统的结构示意图；
图2为本发明实施例二提供的电池管理系统的结构示意图；
图3为本发明实施例三提供的电池管理系统的结构示意图；
图4为本发明实施例四提供的电池管理系统的结构示意图；
图5为本发明实施例五提供的电池管理系统的结构示意图；
图6为本发明一实施例提供的电池的结构示意图；
图7为本发明一实施例提供的无人飞行器的结构示意图；
图8为本发明另一实施例提供的无人飞行器的结构示意图。
具体实施方式
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
图1为本发明实施例一提供的电池管理系统的结构示意图，如图1所示，本实施例的电池管理系统可以包括：第一接口110、第二接口120和控制器130。其中，控制器130分别与第一接口110、第二接口120通信连接。第一接口110用于充电和放电，即为充放电接口。第二接口120用于充电，即为充电接口。
而且，第一接口110的一端用于与外部供电源连接或者无人飞行器连接，第一接口110的另一端用于与电池的电芯连接。因此，在第一接口的另一端与电池的电芯连接时，且第一接口110的一端与外部供电源连接时，第一接口110可以用于充电。在第一接口110的另一端与电池的电芯连接时，且第一接口110的一端与无人飞行器连接时，第一接口110可以用于放电。
而且，第二接口120的一端用于与外部供电源连接，第二接口120的另一端用于与电池的电芯连接。在第二接口120的一端与外部供电源连接时，而第二接口120的另一端与电池的电芯连接时，第二接口120可以用于充电。
控制器130，用于在检测到所述第一接口110电连接无人飞行器，以及所述第二接口120电连接外部供电源时，控制所述第一接口110与所述电芯之间的电路导通；以及控制所述第二接口120与所述电芯之间的电路导通。
本实施例中，控制器130可以检测第一接口110是否电连接无人飞行器，当检测到第一接口110电连接无人飞行器时，说明电芯通过第一接口110可以对无人飞行器进行放电，然后本实施例控制第一接口110与电芯之间的电路导通，例如控制电芯对第一接口110的放电电路导通，在电芯与第一接口110之间的电路导通的情况下，而且，第一接口110是与无人飞行器连接， 因此电芯通过第一接口110向无人飞行器进行放电，实现了第一接口110的放电功能。控制器130还可以检测第二接口120是否电连接外部供电源，在检测到第二接口120电连接外部供电源时，说明电芯通过第二接口120可以充电，然后本实施例控制第二接口120与电芯之间的电路导通，例如控制第二接口对电芯的充电电路导通，在电芯与第二接口120之间的电路导通的情况下，而且，第二接口120是与外部供电源连接，因此电芯通过第二接口120向进行充电，实现了第二接口120的充电功能。通过上述方案，电芯可以同时充电以及放电。
本实施例中，通过在检测到第一接口电连接无人飞行器，以及第二接口电连接外部供电源时，控制第一接口与电芯之间的电路导通，以及控制第二接口与电芯之间的电路导通，因此，本实施例同时实现了第一接口的放电功能以及第二接口的充电功能，使得外部供电源向电芯供电的同时电芯向无人飞行器放电，因此，在电池的电量耗尽时，无需将电池从无人飞行器中取出充电，提高了电池持续向无人飞行器供电的时长，因此，延长了无人飞行器的续航时间，改善了用户体验。
其中，控制器130，还用于在检测到所述第一接口110电连接无人飞行器，以及所述第二接口120未电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通；以及控制所述第二接口与所述电芯之间的电路断开。
本实施例中，若将第一接口110与无人飞行器连接时，且将第二接口120未与任何外部供电源连接时，本实施例的控制器130可以检测到第一接口110电连接无人飞行器，说明电芯通过第一接口110可以对无人飞行器进行放电，然后本实施例控制第一接口110与电芯之间的电路导通，例如控制电芯对第一接口110的放电电路导通，在电芯与第一接口110之间的电路导通的情况下，而且，第一接口110是与无人飞行器连接，因此电芯通过第一接口110向无人飞行器进行放电，实现了第一接口110的放电功能。另外，本实施例的控制器130还可以检测到第二接口120未电连接外部供电源，说明电芯无需通过第二接口120进行充电，然后本实施例控制第二接口120与电芯之间的电路断开，例如控制第二接口对电芯的充电电路断开，在电芯与第二接口120之间的电路断开的情况下，避免了短路的情况发生。通过上述方案，电芯可以在同一时间只进行放电。
其中，控制器130，还用于在检测到所述第一接口110电连接外部供电源时，控制所述第一接口110与所述电芯之间的电路导通，以及控制所述第二接口120与所述电芯之间的电路断开。
本实施例中，若将第一接口110与外部供电源连接时，本实施例的控制器130可以检测到第一接口110电连接无人飞行器，说明电芯通过第一接口110可以进行充电，然后本实施例控制第一接口110与电芯之间的电路导通，例如控制第一接口110对电芯的充电电路导通，在电芯与第一接口110之间的电路导通的情况下，而且，第一接口110是与外部供电源连接，因此电民芯通过第一接口11进行充电，实现了第一接口110的充电功能。另外，在第一接口110与外部供电源电连接时，无论第二接口120是否电连接到外部供电源，电芯无需通过第二接口120进行充电，然后本实施例控制第二接口120与电芯之间的电路断开，例如控制第二接口120对电芯的充电电路断开，在电芯与第二接口120之间的电路断开的情况下，避免了短路的情况发生。通过上述方案，电芯在同一时间只通过一个充放电接口进行充电。
其中，所述控制器130，还用于在检测到所述第一接口110未电连接外部供电源或无人飞行器，所述第二接口120电连接外部供电源时，控制所述第二接口与所述电芯之间的电路导通。
本实施例中，若将第一接口110不与外部供电源连接，也不与无人飞行器连接时，本实施例的控制器130可以检测到第一接口110未电连接无人飞行器，也未电连接外部供电源，说明电芯无需通过第一接口110进行充电，也无需通过第一接口110进行放电，然后本实施例可以控制第一接口110与电芯之间的电路断开，也可以控制第一接口110与电芯之间的电路导通，由于第一接口110为充放电接口，具有安全的接插件，不会存在短路的风险。另外，本实施例的控制器130还检测到第二接口120与外部供电源电连接，说明电芯通过第二接口120可以充电，然后本实施例控制第二接口120与电芯之间的电路导通，例如控制第二接口120对电芯的充电电路导通，在电芯与第二接口120之间的电路导通的情况下，而且，第二接口120是与外部供电源连接，因此电芯通过第二接口120向进行充电，实现了第二接口120的充电功能。通过上述方案，电芯可以同一时间只通过一个充电接口进行充电。
图2为本发明实施例二提供的电池管理系统的结构示意图，如图2所示， 本实施例的电池管理系统在图1所示实施例的基础上，本实施例的第二接口120的另一端与电芯之间设置有第一开关121。第一开关121可以用于控制第二接口120与电芯之间的电路的导通或断开。
本实施例中，控制器130控制第二接口与电芯之间的电路的一种实现方式为：控制器130控制上述第一开关121的闭合或者断开。控制器130在需要控制第二接口120与电芯之间的电路导通时，控制第一开关121闭合。而在需要控制第二接口120与电芯之间的电路断开时，控制第一开关121断开。
可选地，所述第一开关121分别连接于所述第二接口120，以及所述第一接口110与所述电芯之间的电路的预设位置。即，第二接口120的另一端用于连接在第一接口与电芯之间的电路的预设位置。这样控制器在控制第一开关121时，不会影响到电芯与第一接口110之间的电路。
可选地，第一开关121为MOS管或者固态继电器。
可选地，第一开关121为MOS管时，第一开关121可以为一个单独的MOS管，这样在电芯不通过第二接口120充电时，第二接口120可以裸露在外面，使得电池的电芯充电应用场景更加方便，同时具有安全、可靠的特性，避免了短路的发生。
可选地，第一开关121为MOS管时，第一开关121可以为背对背的MOS管，这样可以防止电流倒灌。
图3为本发明实施例三提供的电池管理系统的结构示意图，如图3所示，本实施例的电池管理系统在上述任一实施例的基础上，本实施例的第一接口110与电芯之间设置有第二开关111。第二开关111可以用于控制第一接口110与电芯之间的电路的导通或断开。
本实施例中，控制器130控制第一接口110与电芯之间的电路的一种实现方式为：控制器130控制上述第二开关111的闭合或者断开。控制器130在需要控制第一接口110与电芯之间的电路导通时，控制第二开关111闭合。而在需要控制第一接口110与电芯之间的电路断开时，控制第二开关111断开。在控制第二开关111断开时，即可实现控制第一接口110停止对电芯充电，以及停止对电芯放电，以实现保证电池的安全。
图4为本发明实施例四提供的电池管理系统的结构示意图，如图4所示，本实施例的电池管理系统在图3所示实施例的基础上，在第二接口120与电 芯之间设置有第一开关121，且所述第一开关121分别连接于所述第二接口120，以及所述第一接口110与所述电芯之间的电路的预设位置时；所述第二开关111位于所述电芯与所述预设位置之间。
其中，第一开关121的相关描述可以参见上述实施例中的相关描述，此处不再赘述。
因此，在通过第一接口110对电芯进行充电时，控制第一开关121闭合，以及控制第二开关111断开。在通过第二接口120对电芯进行充电时，控制第一开关121闭合，以及控制第二开关111闭合，另外，此时还可以通过第一接口110对电芯进行放电。
可选地，第二开关111为MOS管或者固态继电器。
可选地，第二开关111为MOS管时，第二开关111可以为一个单独的MOS管。
可选地，第二开关111为MOS管时，第二开关111可以为背对背的MOS管，这样可以防止电流倒灌。在第二开关111为背对背的MOS管时，第一开关121可以为单独的MOS管。
如图5所示，P1+为第一接口，P2+为第二接口，B+为电芯，S1为第一开关，S2和S3为第二开关，而且S2和S3为背对背的MOS。因此，本发明实施例的电池管理系统包括两个充电接口(P1+、P2+)，其中P1+具有充放电功能，P2+具有充电功能。P2+用一个单独MOS管控制，在非充电模式下，P2+可裸露在外，这样使充电应用场景更加方便，同时具有安全、可靠的特性，避免了短路的发生。具体工作过程如下：当使用P1+对电芯进行充电时，S2、S3导通，S1断开，此时P2+无电压，防止外部短路；当使用P2+进行充电时S1、S2、S3均导通，此时可同时使用P1+给外部(例如无人飞行器)供电。由于P1+为普通的充/放电接口，通常设计有安全的接插件，无短路风险。
在上述各实施例的基础上，在一种应用场景下，上述的第二接口120仅用于充电。也就是，第二接口120不具有对电芯放电的功能，这样第二接口120为专用的充电口，为方便使用，本实施例的第二接口120可以为裸露的金属装置。
在上述各实施例的基础上，在一种应用场景下，第二接口120还用于放电；所述控制器130，还用于在检测到所述第一接口110电连接无人飞行器， 以及所述第二接口120电连接外部供电源时，控制所述第一接口110与所述电芯之间的电路断开；以及控制所述第二接口120与所述第一接口110之间的电路导通。
在将第一接口110与无人飞行器连接，而且将第二接口120与外部供电源连接时，说明可以通过第一接口110对无人飞行器供电，而且第二接口120具有放电功能，相当于可以通过第二接口120对外部供电源进行放电，因此，通过第一接口110与第二接口120可以实现用外部供电源对无人飞行器直接供电，无需经过电池的电芯。所以，本实施例的控制器130控制第一接口110与电芯之间的电路断开，因此，电芯不会通过第一接口110向无人飞行器供电，而且本实施例的控制器130还控制第二接口120与第一接口110之间的电路导通，相当于导通了外部供电源与无人飞行器之间的电路，此时，外部供电源可直接对无人飞行器进行供电。通过上述方案，通过第一接口和第二接口实现外部供电源对无人飞行器直接供电。
另外，上述的外部供电源可以为充电宝，即为无人飞行器的充电宝，对于充电宝的描述可以参见相关技术中的描述，此处不再赘述。
图6为本发明一实施例提供的电池的结构示意图，如图6所示，本实施例的电池可以包括：电池管理系统100和电芯200，其中，其中，所述电池管理系统100，用于控制所述电芯200的充放电。
其中，电池管理系统100可以采用图1-图5任一装置实施例的结构，其实现原理和技术效果类似，此处不再赘述。
图7为本发明一实施例提供的无人飞行器的结构示意图，如图7所示，本实施例的无人飞行器1000包括：机架1100、动力系统1200和电池1300。
所述机架1100内设置电池管理系统1110；所述电池1300设置在所述机架1100的电池仓内；所述电池管理系统1110用于控制所述电池1300的电芯的充放电。
其中，电池管理系统1110可以采用图1-图5任一装置实施例的结构，其实现原理和技术效果类似，此处不再赘述。
图8为本发明另一实施例提供的无人飞行器的结构示意图，如图8所示，本实施例的无人飞行器2000包括：机架2100、动力系统2200和电池2300。所述电池2300设置在所述机架2100的电池仓内。
其中，电池2300可以采用图6所示装置实施例的结构，其实现原理和技术效果类似，此处不再赘述。
其中，上述的动力系统可以包括：电调、电机和螺旋桨，电调分别与机架中的飞行控制器与电机电连接；从而为无人飞行器提供动力以进行飞行。
本领域普通技术人员可以理解：实现上述方法实施例的全部或部分步骤可以通过程序指令相关的硬件来完成，前述的程序可以存储于一计算机可读取存储介质中，该程序在执行时，执行包括上述方法实施例的步骤；而前述的存储介质包括：只读内存(Read-Only Memory，ROM)、随机存取存储器(Random Access Memory，RAM)、磁碟或者光盘等各种可以存储程序代码的介质。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分或者全部技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。

Claims (17)

  1. 一种电池管理系统，其特征在于，包括：第一接口、第二接口和控制器；所述控制器分别与所述第一接口、所述第二接口通信连接；所述第一接口用于充电和放电，所述第二接口用于充电；
    所述第一接口的一端用于与外部供电源连接或者无人飞行器连接，所述第一接口的另一端用于与电池的电芯连接；所述第二接口的一端用于与外部供电源连接，所述第二接口的另一端用于与所述电芯连接；
    所述控制器，用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通；以及控制所述第二接口与所述电芯之间的电路导通。
  2. 根据权利要求1所述的电池管理系统，其特征在于，所述第二接口的另一端与所述电芯之间设置有第一开关；
    所述控制器，具体用于：控制所述第一开关的闭合或者断开，以控制所述第二接口与所述电芯之间的电路导通或断开。
  3. 根据权利要求2所述的电池管理系统，其特征在于，所述第一开关分别连接于所述第二接口，以及所述第一接口与所述电芯之间的电路的预设位置。
  4. 根据权利要求2或3所述的电池管理系统，其特征在于，所述第一开关为MOS管或者固态继电器。
  5. 根据权利要求4所述的电池管理系统，其特征在于，所述MOS管为背对背的MOS管。
  6. 根据权利要求1-5任意一项所述的电池管理系统，其特征在于，所述控制器，还用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口未电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通；以及控制所述第二接口与所述电芯之间的电路断开。
  7. 根据权利要求1-5任意一项所述的电池管理系统，其特征在于，所述控制器，还用于在检测到所述第一接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路导通，以及控制所述第二接口与所述电芯之间的电路断开。
  8. 根据权利要求1-5任意一项所述的电池管理系统，其特征在于，所述 控制器，还用于在检测到所述第一接口未电连接外部供电源或无人飞行器，所述第二接口电连接外部供电源时，控制所述第二接口与所述电芯之间的电路导通。
  9. 根据权利要求1-8任意一项所述的电池管理系统，其特征在于，所述第一接口与所述电芯之间设置有第二开关；
    所述控制器，具体用于：控制所述第二开关的闭合或者断开，以控制所述第一接口与所述电芯之间的电路导通或断开。
  10. 根据权利要求9所述的电池管理系统，其特征在于，在第二接口与电芯之间设置有第一开关，且所述第一开关分别连接于所述第二接口，以及所述第一接口与所述电芯之间的电路的预设位置时；所述第二开关位于所述电芯与所述预设位置之间。
  11. 根据权利要求9或10所述的电池管理系统，其特征在于，所述第二开关为MOS管或者继电器。
  12. 根据权利要求11所述的电池管理系统，其特征在于，所述MOS管为背对背的MOS管。
  13. 根据权利要求1-12任意一项所述的电池管理系统，其特征在于，所述第二接口仅用于充电。
  14. 根据权利要求1-12任意一项所述的电池管理系统，其特征在于，所述第二接口还用于放电；
    所述控制器，还用于在检测到所述第一接口电连接无人飞行器，以及所述第二接口电连接外部供电源时，控制所述第一接口与所述电芯之间的电路断开；以及控制所述第二接口与所述第一接口之间的电路导通。
  15. 一种电池，其特征在于，包括：电芯和权利要求1-14任意一项所述的电池管理系统；
    其中，所述电池管理系统，用于控制所述电芯的充放电。
  16. 一种无人飞行器，其特征在于，包括：机架、动力系统和电池；
    所述机架内设置有权利要求1-14任意一项所述的电池管理系统；所述电池设置在所述机架的电池仓内；所述电池管理系统用于控制所述电池的电芯的充放电。
  17. 一种无人飞行器，其特征在于，包括：机架、动力系统和权利要求 15所述的电池；
    所述电池设置在所述机架的电池仓内。
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