WO2019172060A1 - Batterie et chargeur - Google Patents

Batterie et chargeur Download PDF

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Publication number
WO2019172060A1
WO2019172060A1 PCT/JP2019/007743 JP2019007743W WO2019172060A1 WO 2019172060 A1 WO2019172060 A1 WO 2019172060A1 JP 2019007743 W JP2019007743 W JP 2019007743W WO 2019172060 A1 WO2019172060 A1 WO 2019172060A1
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WO
WIPO (PCT)
Prior art keywords
battery
sensor
memory
charger
drone
Prior art date
Application number
PCT/JP2019/007743
Other languages
English (en)
Japanese (ja)
Inventor
千大 和氣
洋 柳下
渡辺　均
長野　博之
竹田　和弘
Original Assignee
株式会社ナイルワークス
マクセルホールディングス株式会社
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 株式会社ナイルワークス, マクセルホールディングス株式会社 filed Critical 株式会社ナイルワークス
Priority to JP2020504961A priority Critical patent/JP7036393B2/ja
Priority to CN201980005797.5A priority patent/CN111357147A/zh
Priority to CN202310191120.3A priority patent/CN116154913A/zh
Publication of WO2019172060A1 publication Critical patent/WO2019172060A1/fr
Priority to JP2021153243A priority patent/JP7093958B2/ja

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Classifications

    • 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
    • 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
    • B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
    • B60L53/20—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by converters located in the vehicle
    • 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
    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
    • B60L58/10—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
    • 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
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • 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
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H5/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal non-electric working conditions with or without subsequent reconnection
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
    • H02H7/18—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for batteries; for accumulators
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H02J7/0031—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using battery or load disconnect circuits
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
    • 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
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/37—Charging when not in flight

Definitions

  • the present invention relates to a battery with improved safety and a charger equipped with this battery.
  • drones unmanned air vehicles
  • spraying of chemicals such as agricultural chemicals and liquid fertilizers on farmland, that is, fields (for example, see Patent Document 1).
  • fields for example, see Patent Document 1
  • drug spraying by drone is more suitable than drug spraying by manned airplanes and helicopters.
  • the drone can know the absolute position of the aircraft accurately in centimeters while flying. Therefore, even in a narrow and complex terrain farmland, which is typical in Japan, autonomous flight reduces maneuvering by manpower and enables efficient and accurate drug spraying.
  • QZSS Quasi-Zenith Satellite System
  • RTK-GPS RadioTK-GPS
  • a drone generally uses an electric motor as a drive source, and a battery is mounted as a power source for driving the electric motor. Therefore, in the drone in which safety is strictly required as described above, it is required to prevent the battery from malfunctioning and to prevent the battery malfunction from causing the malfunction as a drone.
  • the battery according to the present invention is intended to prevent a functional failure of a device using the battery by making it unusable when a phenomenon that causes a functional failure is detected.
  • the charger according to the present invention aims to prevent the occurrence of a malfunction caused by a malfunction of a battery.
  • the battery according to the present invention is A battery pack having battery cells; A sensor that detects a phenomenon that impedes battery function; A memory for storing the detection signal of the sensor; A shut-off circuit that shuts off an output line from the battery pack according to the detection signal; It has the most important feature.
  • the charger according to the present invention is a charger for charging a battery that can be mounted on an unmanned air vehicle, and has a diagnostic circuit for diagnosing whether or not the battery functions normally, and the battery functions normally If the diagnostic circuit determines that the battery cannot be charged, charging of the battery is prohibited.
  • the battery according to the present invention when a phenomenon causing a failure in the function of the battery occurs, this is detected by a sensor, and this detection signal is stored in a memory and the output of the battery pack is cut off by the detection signal. Therefore, thereafter, the battery having a high possibility of causing a functional failure becomes unusable, and the failure of the battery can be prevented from reaching the function of the external device.
  • the drone 2 includes a plurality of (four in the illustrated example) rotating blades 101 that are driven to rotate about an axis.
  • Each of the rotor blades 101 is rotationally driven by an individual motor 21 to generate axial thrust by generating the axial air flow.
  • the rotor blades 101 are attached together with the motor 21 to the tip portions of the four arms extending from the main body 104 of the drone 2.
  • the drone 2 has a flight control unit 30 (see FIG. 8) in the main body 104 that individually controls the rotation speed and rotation direction of each of the rotor blades 101.
  • the flight control unit 30 is necessary as the drone 2 such as take-off and landing, forward, backward, ascending, descending, moving left and right, hovering, etc. Various operations can be performed.
  • the flight controller shown in FIG. 8 constitutes the flight control unit 30.
  • FIG. 8 shows a control object whose operation is controlled by a signal input element to the flight control unit 30 and an output signal of the flight control unit 30 with the flight control unit 30 as a center.
  • signal input elements and controlled objects those directly related to the present invention will be mainly described.
  • the flight control unit 30 is input with a command signal transmitted from the tablet 40, detection signals from various sensors, and the like.
  • the flight control unit 30 controls power supply to each motor 21 that rotationally drives each rotary wing 101 based on the various input signals, and controls the rotation speed of each rotary wing 101.
  • the drone 2 is an autonomous drone that operates according to a program set by the tablet 40 while confirming a position based on GPS data or the like and confirming signals from various sensors.
  • FIG. 7 shows four rotor blades 101, another rotor blade is arranged on the extension of the rotating shaft of each rotor blade 101, and a total of eight rotor blades are arranged.
  • FIG. 8 shows eight motors 21 that individually rotate and drive eight rotor blades. The two rotor blades arranged on the same axis are driven to rotate in opposite directions, and the torsion directions of the rotor blades are opposite to each other so that thrust is generated in the same direction.
  • the number of the rotor blades 101 is arbitrary, and whether the single-axis rotor blade is single or plural is arbitrary.
  • the drone 2 can be equipped with a battery 1 that drives each motor 21.
  • the battery 1 includes a battery pack 11, and power is supplied from the battery pack 11 to each motor 21 via a drive unit controlled by the flight control unit 30.
  • the battery 1 includes a cutoff circuit 20 having a switch 16 and a switch control unit that controls on / off of the switch 16.
  • the switch 16 is an open / close switch connected in series to the power supply line from the battery pack 11 and is normally controlled by the switch control unit to maintain the on state.
  • the battery pack 11 is composed of, for example, a lithium ion type rechargeable battery cell or a plurality of battery cells.
  • the battery 1 includes a detection unit that detects a phenomenon that causes a failure in a function such as the drone 2 that is a load of the battery 1 and outputs a signal when the phenomenon occurs. Yes.
  • the switch control unit included in the cutoff circuit 20 switches the switch 16 off when the detection signal of the detection unit is input.
  • a detailed configuration of the battery 1 and on / off control of the switch 16 by the power control unit will be described.
  • reference numeral 1 denotes a battery.
  • the battery 1 is a rechargeable battery such as a lithium ion battery.
  • the battery 1 includes a battery pack 11 having one or a plurality of battery cells.
  • the battery pack 11 serves as a driving power source for driving various devices, and is provided with a switch 16 for turning on and off the power output line from the battery pack 11.
  • the battery 1 shown in FIG. 1 has a switch 16, sensors 12 and 13 that detect a phenomenon that causes a failure in the function of the battery 1, a memory 14, and a switch control unit 15 that controls on / off of the switch 16. Is.
  • an impact sensor 12 and a submergence sensor 13 are provided as sensors for detecting a phenomenon that causes a failure in the function of the battery 1.
  • the battery 1 is, for example, a lithium ion battery
  • a failure such as a rise in temperature or ignition may occur.
  • the cause of such a failure is detected by the impact sensor 12.
  • the battery 1 when the battery 1 is submerged, the battery 1 cannot exhibit sufficient performance, and there is a possibility that an operation of a device that uses the battery 1 as a drive power source may be obstructed. The cause of such a failure is detected by the submergence sensor 13.
  • Sensors that detect a phenomenon that causes a failure in the function of the battery 1 are not limited to the impact sensor 12 and the submergence sensor 13.
  • a temperature sensor may be provided if it has a history of being exposed to extremely high or low temperatures and may cause a failure in the function of the battery 1.
  • the detection signals of the impact sensor 12 and the submergence sensor 13, that is, signals indicating troubles are temporarily input to the memory 14, and the troubles are recorded in the memory 14 as the history of the battery 1.
  • the memory 14 inputs the detection signal to the switch control unit 15.
  • the switch control unit 15 switches the switch 16 off when the detection signal is input.
  • the switch control unit 15 and the switch 16 constitute a cut-off circuit that cuts off the output of the battery pack 11 based on detection signals from the impact sensor 12 and the submergence sensor 13.
  • the memory 14 stores the detection signals of the impact sensor 12 and the submergence sensor 13 and inputs the detection signal to the cutoff circuit.
  • the detection signals of the sensors 12 and 13 may be input to the memory 14 and directly to the switch control unit 15.
  • the switch 16 is turned on so that power can be supplied to the external device from the power output line, and operating power is supplied to the memory 14 and the switch control unit 15 in the battery 1.
  • the switch control unit 15 may be configured to self-hold the switch 16 in a normal state and release the self-holding of the switch 16 by a detection signal of the impact sensor 12 or the submergence sensor 13.
  • the battery 1 can be mounted on various devices and used as a power source for various devices.
  • a drone 2 that is an unmanned air vehicle is connected to the power output line and the driving power is supplied to the drone 2.
  • the charger 3 can be connected to the power output line.
  • the AC power source is rectified and converted into a DC power source having a predetermined voltage, and the battery pack 11 is charged.
  • the internal configuration of the charger 3 includes, for example, a smoothing circuit, a voltage control circuit, and a current control circuit as necessary, in addition to the rectifier circuit, as in the known internal configuration of the charger.
  • a backflow prevention diode 31 is connected to the output line of the charger 3.
  • the battery pack 11 can be charged by connecting the output line of the charger 3 to the power output line while the battery 1 is in a normal state, that is, the switch 16 is on.
  • the battery 1 described above when a phenomenon that impedes the function of the battery 1, for example, when an impact force is applied or submerged, the output line from the battery pack 11 is cut off, and the battery 1 itself cannot be used. If it is possible to use the battery 1 while the battery 1 that cannot exhibit the original performance as the driving power source of the drone 2 is mounted on the drone 2, a serious trouble may occur in the drone 2. However, if the battery 1 has a history that may cause a failure in its function, the battery 1 itself becomes unusable. Therefore, even if the battery 1 is mounted on the drone 2, the drone 2 can operate. Therefore, the serious trouble of the drone 2 can be prevented beforehand.
  • a shut-off circuit that shuts off the output of the battery pack 11 with detection signals from the impact sensor 12 and the submergence sensor 13 may be provided on the unmanned air vehicle side such as the drone 2. Embodiments of the unmanned air vehicle according to the present invention will be described below.
  • the battery 1-1 has a battery pack 11, an impact sensor 12, a submergence sensor 13, and a memory 14 as in the case of the battery 1 shown in FIG. Yes.
  • the battery 1-1 is different from the battery 1 shown in FIG. 1 in that a cutoff circuit including a switch control unit 25 and a switch 26 is provided on the drone 2-1 side.
  • the data stored in the memory 14 of the battery 1-1 is input to the interlock command unit 17 in the battery 1-1.
  • the output signal of the interlock command unit 17 is received by the receiving unit 27 on the drone 2-1 side and input to the switch control unit 25.
  • the interlock command unit 17 generates an interlock command signal from the stored data when the detection signals of the impact sensor 12 and the submergence sensor 13 are stored in the memory 14.
  • the interlock command signal is a signal for cutting off the output from the battery pack 11 and making it impossible to use the battery 1-1.
  • the output line from the battery pack 11 is connected to the drone 2-1 side through an appropriate connector so that power is supplied to the drive unit 22 of the drone 2-1.
  • the drive unit 22 controls the power supply to the motors 21 to exert the function as the drone 2-1.
  • a switch 26 On the output line from the battery pack 11 on the drone 2-1 side, a switch 26 that constitutes the cutoff circuit is arranged.
  • the interlock command signal generated by the interlock command unit 17 is received by the receiving unit 27 of the drone 2-1 via an appropriate connector and is input to the switch control unit 25.
  • the signal transmission between the battery and the drone is performed by the interlock command unit 17 and the receiving unit 27, whereby the signal transmission can be simplified. If the data in the memory is to be transmitted, there is a problem that the data structure becomes complicated.
  • the charger 3 can be connected to the output line from the battery pack 11 of the battery 1-1 through an appropriate connector instead of the drone 2-1.
  • a backflow preventing diode 31 is connected to the output line of the charger 3.
  • the battery pack 11 can be charged by connecting the charger 3 to the battery 1-1.
  • the cutoff circuit on the drone 2-1 side is connected to the battery pack.
  • the output line from 11 is cut off. That is, the detection signal from the sensor 12 or the sensor 13 is recorded in the memory 14 on the battery 1-1 side, and the cutoff circuit on the drone 2-1 side is connected to the drone 2-1 from the battery pack 11 by this detection signal. Shut off the power supply. Accordingly, the reuse of the defective battery 1-1 is prohibited, and an accident caused by the drone 2-1 falling out of control due to the malfunction of the battery 1-1 can be prevented.
  • the battery 1-1 in the above embodiment does not have the circuit for interrupting the battery pack described with reference to FIG. 1, but has an interlock command unit 17 that outputs an interlock command signal to the outside.
  • the interlock command unit 17 constitutes a command signal output unit that the output from the battery pack 11 should be cut off, and prohibits the reuse of the battery when the specific battery is unsuitable for use. .
  • a plurality of batteries are prepared for each drone. Therefore, by simplifying the battery configuration as described above, cost reduction and space saving can be achieved.
  • FIG. 3 shows a second embodiment of a drone that is an unmanned air vehicle.
  • the battery 1-2 has a charge recording unit 18.
  • a charger is connected to the battery 1-2, a charging voltage is applied and a charging current flows to charge the battery 1-2, the charging recording unit 18 counts and records the number of times of charging.
  • the charging recording unit 18 reaches a predetermined number of times of charging that affects the life of the battery 1, the charging recording unit 18 operates the switch control unit 25 that constitutes the cutoff circuit on the drone 2-2 side, and turns off the switch 26. Switch to.
  • the configuration on the drone 2-2 side is almost the same as the configuration of the drone 2-1 shown in FIG. 2, but the output signal of the charging recording unit 18 is sent to the switch control unit 25 on the drone 2-2 side via a connector or the like.
  • the point that is input to is different.
  • the charging recording unit 18 counts the number of times of charging and records the count value.
  • the charging recording unit 18 sends a signal to the switch control unit 25 on the drone 2-2 side.
  • the switch control unit 25 switches off the switch 26 and cuts off the output line from the battery pack 11.
  • the interlock command unit 17 in the embodiment shown in FIG. 2 may be provided on the battery 1-2 side, and the receiving unit 27 may be provided on the drone side.
  • the drone 2-3 shown in FIG. 4 is different from the drone 2-2 shown in FIG. 3 in that an impact sensor 23 and a submergence sensor 24 are used as sensors for detecting a phenomenon that the drone 2-3 itself impairs the function of the battery. It is a point.
  • the impact sensor 23 and the submergence sensor 24 are sensors similar to the impact sensor 12 and the submergence sensor 13 provided on the battery side. Detection signals from the impact sensor 23 and the submergence sensor 24 on the drone 2-3 side are input to the switch control unit 25.
  • the switch control unit 25 performs on / off control of the output line from the battery pack 11 of the battery 1-3.
  • the detection signals of the impact sensor 23 and the aircraft-side submergence sensor 24 are transmitted to the memory 14 included in the battery 1-3.
  • a detection signal is output from the sensor 23 or the sensor 24, and the detection signal is recorded in the memory 14. That is, the memory 14 records a trouble, and inputs the recorded detection signal of the sensor 23 or the sensor 24 to the switch control unit 25 on the drone 2-3 side.
  • the switch control unit 25 turns off the switch 26 on the output line from the battery pack 11 of the battery 1-3 and cuts off the power supply line.
  • the drone 2-3 has a plurality of propellers as well known, and has a plurality of motors 21 that individually rotate and drive the propellers.
  • Each motor 21 is supplied with power from the battery 1-3 via the motor drive unit 22.
  • the number of motors 21 in this embodiment is four, it is not limited to this and may be four or more or four or less.
  • the number of motors is twice the number of shafts.
  • the motor drive unit 22 controls the rotation of each motor 21 by, for example, a preset program, and performs operations necessary as a drone such as ascending, descending, advancing, retreating, and hovering of the drone 2-3.
  • the drone 2-3 is usually equipped with a 6-axis acceleration sensor to control the attitude.
  • An acceleration sensor and an angular velocity sensor are mounted on the roll axis, the pitch axis, and the yaw axis, respectively, and these are collectively referred to as a six-axis acceleration sensor.
  • These acceleration sensors and angular velocity sensors output an abnormal signal in response to an abnormal impact force that cannot be a normal flight on the drone 2-3.
  • the 6-axis acceleration sensor can be used as the unmanned air vehicle side impact sensor 23.
  • the drone 2-3 is provided with a propeller guard to prevent the propeller from coming into contact with an obstacle and to prevent the propeller from coming into contact with the human body and the like to damage the human body.
  • a propeller guard to prevent the propeller from coming into contact with an obstacle and to prevent the propeller from coming into contact with the human body and the like to damage the human body.
  • the detection signal of the impact sensor 23 or the submergence sensor 24 on the drone 2-3 side is transmitted to the battery 1-3 side, and the output line of the battery pack 11 is cut off. Thereafter, the battery 1-3 cannot be used, and the malfunction of the drone 2 caused by the malfunction of the battery 1-3 can be prevented in advance.
  • the interlock command section 17 in the embodiment shown in FIG. 2 may be provided on the battery 1-2 side, and the receiving section 27 may be provided on the drone side.
  • FIG. 5 shows a fourth embodiment of the drone as an unmanned air vehicle.
  • the battery 1-4 is assigned an ID for identifying each individual, and this ID signal is transmitted to the drone 2-4 side. is there.
  • an aircraft-side memory 28 is provided on the drone 2-4 side. The ID signal transmitted from the battery 1-4 side to the drone 2-4 side is recorded in the flying object side memory 28.
  • the flying object side memory 28 also records detection signals from the flying object side impact sensor 23 and the flying object side submerged sensor 24.
  • the vehicle-side memory 28 stores the detection signals of the sensors 23 and 24 in association with the ID of the battery 1-4 used at that time, so that the specific battery 1-4 identified by the ID It is possible to record a history of whether the output is cut off. If it is found that the battery 1-4 used has been cut off in the past, the memory 28 transmits a signal to the switch control unit 15 of the battery 1-4. Upon receiving this signal, the switch control unit 15 turns off the switch 16 to disable the battery 1-4.
  • the interruption circuit of the battery 1-4 is connected to the battery.
  • the output of the pack 11 is shut off. Accordingly, it is possible to prevent a functional failure of the drone 2-4 caused by a failure of the battery 1-4 during the operation of the drone 2-4.
  • the interlock command section 17 in the embodiment shown in FIG. 2 may be provided on the battery 1-2 side, and the receiving section 27 may be provided on the drone side.
  • shut-off circuit of the drone 2-4 The power supply line may be cut off.
  • the switch control unit, the switch opened and closed by the switch control unit, and the memory may be provided only on the drone side, and may be omitted from the battery side.
  • Agricultural drones are quite large so that as many drugs as possible can be loaded, battery capacity is considerably large, and costs are high. Therefore, it is desirable that the number of members attached to the battery be as small as possible to reduce the size and reduce the cost.
  • the switch control unit, the switch, and the memory on the battery side, it is possible to reduce the size and cost of the battery.
  • FIG. 6 shows an embodiment of a charger having a function of automatically diagnosing whether or not the battery is normal when charging the battery according to the present invention.
  • the charger 3 has a charging circuit 32 and a diagnostic circuit 33.
  • the charging circuit 32 rectifies and smoothes the commercial AC power supply 4 to convert it to an appropriate DC voltage, and supplies a charging current to the battery pack 11 of the battery 1-5 via the backflow prevention diode 31.
  • the voltage of the battery pack 11 is applied to the diagnostic circuit 33, and the history data of the battery 1-5 stored in the memory 14 of the battery 1-5 is stored in the interlock command unit 17 on the battery 1-5 side. Are input via the receiver 27 on the charger 3 side.
  • the diagnostic data of the diagnostic circuit 33 is input and stored in the memory 14.
  • the diagnostic circuit 33 also includes a temperature sensor necessary for diagnosis of the battery 1-5, a periodic voltage amplitude generation circuit for analysis using impedance, and the like.
  • 1. Number of impacts, number of submergence: According to history data stored in the memory 14.
  • Degradation due to the number of charge / discharge cycles, internal resistance, and the interrelationship between battery temperature, voltage and charge.
  • Impedance analysis The battery temperature is measured by applying a periodic voltage signal to the battery. The temperature of the battery can be measured by contacting the thermometer built in the diagnostic circuit 33 with the battery 1-5, or by measuring with infrared rays.
  • a cutoff circuit comprising the switch control unit 15 and the switch 16 cuts off the output line from the battery pack 11 and disables the battery 1-5. That is, the battery 1-5 is interlocked, and the battery 1-5 becomes non-reusable.
  • the diagnostic circuit 33 determines that the battery is normal, the battery 1-5 is charged, and diagnostic data indicating that the battery is normal is input to the memory 14 of the battery 1-5 and stored.
  • a cutoff circuit composed of the switch control unit 15 and the switch 16 turns on the output line from the battery pack 11 and permits the use of the battery 1-5.
  • the diagnosis circuit 33 Depending on the diagnosis item by the diagnosis circuit 33, there is an item that is not a fundamental failure of the battery 1-5 but is recovered by charging. For example, the above-described internal resistance, the case of the correlation between the battery temperature, the voltage, and the charge amount, or the diagnosis by impedance analysis.
  • the diagnostic circuit 33 transmits diagnostic data indicating that the battery 1-5 is normal to the memory 14 of the battery 1-5.
  • the memory 14 clears data that made it impossible to use the battery 1-5 when the diagnostic data is input.
  • the switch control unit 15 constituting the cutoff circuit returns the switch 16 to ON so that the battery 1-5 can be used.
  • a memory that stores a detection signal of the sensor may be provided on the charger side.
  • an ID for identifying the battery for each individual is stored, and when the battery identified by the ID has a history of shutting off the output, charging of the battery is prohibited. Good.
  • the battery has a history of damage such as impact or submergence, charging the battery or discharging it with a load may cause problems such as overheating or ignition.
  • the charger By configuring the charger as described above, it is possible to substantially prohibit reuse of a battery that may cause a malfunction, and to prevent a drone malfunction due to a malfunction of the battery. it can.
  • the battery, unmanned air vehicle and charger according to the present invention may be modified as follows.
  • the mobile body may be on land, water, or water. It may be a manned mobile body.
  • the switch that cuts off the battery output may be provided on both sides of the battery and the unmanned air vehicle.
  • the switch control units may be provided on both sides of the battery and the unmanned air vehicle, or the switches on both sides may be controlled by the switch control unit provided on one side.
  • Rechargeable batteries tend to have a shorter life due to overcharge or overdischarge. Therefore, overcharge or overdischarge is detected and recorded in the memory, and the allowable number of charges is reduced for a battery having an overcharge or overdischarge history. Thereby, the trouble occurrence probability of various devices caused by a battery trouble can be reduced.
  • Some chargers have a circuit that prevents overcharging of the battery. Therefore, an overcharge history may be stored in the battery memory using an overcharge prevention circuit of the charger.
  • ⁇ Power is supplied from the drone battery to the drone PMU (Step Down Divider) at a relatively high terminal voltage.
  • the PMU steps down the battery terminal voltage to a voltage suitable for each part of the drone and distributes power to each part. Therefore, the PMU may be provided with a function as a shut-off circuit that shuts off power distribution to each part. That is, when it is detected that the battery mounted on the drone is inappropriate, the output line from the battery pack is cut off by the function of the PMU as the cut-off circuit, and the battery cannot be used substantially. Like that.
  • the battery itself may include a display unit, and the history or stored contents of the battery stored in the memory may be displayed on the display unit.
  • This display unit displays the current status of the battery as “normal”, “failed”, and “self-protecting (interlock)” by lighting, blinking, color coding, etc. depending on the display element. It is good to display.
  • the display element include an LED, an organic EL element, and a liquid crystal display element.
  • the battery is mounted on the drone or the charger, in all cases, it is advisable to provide a memory that stores data relating to the battery history and battery status. If the data stored in the memory is data that is unsuitable for use by a specific battery, the output from the battery pack is cut off to make the battery unusable.

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Emergency Management (AREA)
  • Business, Economics & Management (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)
  • Secondary Cells (AREA)

Abstract

Le problème décrit par la présente invention est d'obtenir une batterie pouvant être désactivée lorsqu'un phénomène qui peut provoquer un mauvais fonctionnement est détecté, et un chargeur. La solution selon l'invention porte sur une batterie qui comprend : un bloc-batterie 11 qui a des cellules de batterie ; des capteurs 12, 13 qui détectent des phénomènes qui provoquent un dysfonctionnement du bloc-batterie 11 ; une mémoire 14 qui stocke les signaux de détection des capteurs ; et un circuit de coupure 15, 16 qui coupe la sortie du bloc-batterie 11 sur la base du signal de détection. Ce chargeur 3, pour charger une batterie qui peut être montée dans un véhicule aérien sans pilote, a un circuit de diagnostic 33 qui diagnostique si oui ou non la batterie fonctionne normalement, et interdit la charge de la batterie si le circuit de diagnostic détermine que la batterie ne peut pas fonctionner normalement.
PCT/JP2019/007743 2018-03-07 2019-02-28 Batterie et chargeur WO2019172060A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP2020504961A JP7036393B2 (ja) 2018-03-07 2019-02-28 バッテリおよび充電器
CN201980005797.5A CN111357147A (zh) 2018-03-07 2019-02-28 电池以及充电器
CN202310191120.3A CN116154913A (zh) 2018-03-07 2019-02-28 充电器
JP2021153243A JP7093958B2 (ja) 2018-03-07 2021-09-21 充電器

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JP2018041029 2018-03-07
JP2018-041029 2018-03-07

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WO2019172060A1 true WO2019172060A1 (fr) 2019-09-12

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11597295B1 (en) 2022-03-25 2023-03-07 Beta Air, Llc System for monitoring a battery system in-flight and a method for its use
WO2023132185A1 (fr) * 2022-01-07 2023-07-13 株式会社デンソー Bloc-batterie, procédé de configuration, procédé de traitement et programme de traitement
KR102615678B1 (ko) * 2023-04-27 2023-12-20 켄코아에비에이션 주식회사 유무인 비행체용 충전 및 진단 검사 통합 방법, 장치 및 시스템

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09312172A (ja) * 1996-05-22 1997-12-02 Sony Corp バッテリパック、充電器、および充電システム、並びに充電方法
JP2006019194A (ja) * 2004-07-05 2006-01-19 Kokusai Chart Co 携帯用プリンタに使用される二次電池の充電と電池のチェックシステム
JP2008091085A (ja) * 2006-09-29 2008-04-17 Fujitsu Ltd バッテリパック及び電子機器
JP2009259837A (ja) * 2009-05-28 2009-11-05 Makita Corp 二次電池の診断装置とそれに有用な情報収集装置
WO2016006152A1 (fr) * 2014-07-11 2016-01-14 パナソニックＩｐマネジメント株式会社 Bloc-batterie de stockage, et procédé de fonctionnement de bloc-batterie de stockage
WO2017134995A1 (fr) * 2016-02-03 2017-08-10 パナソニックＩｐマネジメント株式会社 Procédé de commande de dispositif serveur, et dispositif serveur
JP2017175736A (ja) * 2016-03-22 2017-09-28 日立マクセル株式会社 二次電池の充電機構、二次電池の充電装置、および、二次電池パック

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3244737B2 (ja) * 1991-12-24 2002-01-07 松下電工株式会社 電池の寿命報知装置
JP2929921B2 (ja) * 1993-12-21 1999-08-03 三菱電機株式会社 電子機器及び電池管理装置及び電池管理方法
JP2003197268A (ja) * 2001-12-28 2003-07-11 Nec Tokin Tochigi Ltd 異常保護回路付電池パック
JP5090119B2 (ja) 2007-09-28 2012-12-05 京セラ株式会社 携帯電子機器
JP5305504B2 (ja) 2008-07-04 2013-10-02 矢崎総業株式会社 充電監視装置
JP2011075458A (ja) * 2009-09-30 2011-04-14 Gs Yuasa Corp バッテリ情報記憶装置、バッテリ診断装置、バッテリ充電装置及びバッテリ情報表示装置
JP5728877B2 (ja) * 2010-10-13 2015-06-03 トヨタ自動車株式会社 電池の故障判定装置
CN107742915B (zh) 2013-12-06 2021-02-19 深圳市大疆创新科技有限公司 电池以及具有该电池的飞行器
KR101583962B1 (ko) * 2014-08-01 2016-01-19 현대자동차주식회사 충전상태 진단 방법
JP6489204B2 (ja) 2015-03-12 2019-03-27 オムロン株式会社 バッテリ、システム、バッテリ管理方法、バッテリ管理プログラムおよび記録媒体
JP6455313B2 (ja) * 2015-05-21 2019-01-23 日産自動車株式会社 バッテリ異常診断装置および異常診断方法
JP6402876B2 (ja) 2015-07-06 2018-10-10 株式会社エアロネクスト 回転翼機着陸装置
CN105244951B (zh) * 2015-10-08 2018-03-06 中国矿业大学 一种带有诊断功能的智能充电器及充电方法
JPWO2017086234A1 (ja) 2015-11-20 2017-12-28 株式会社プロドローン 無人航空機
CN107533724B (zh) 2016-02-24 2022-03-08 松下知识产权经营株式会社 服务器装置及其控制方法

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09312172A (ja) * 1996-05-22 1997-12-02 Sony Corp バッテリパック、充電器、および充電システム、並びに充電方法
JP2006019194A (ja) * 2004-07-05 2006-01-19 Kokusai Chart Co 携帯用プリンタに使用される二次電池の充電と電池のチェックシステム
JP2008091085A (ja) * 2006-09-29 2008-04-17 Fujitsu Ltd バッテリパック及び電子機器
JP2009259837A (ja) * 2009-05-28 2009-11-05 Makita Corp 二次電池の診断装置とそれに有用な情報収集装置
WO2016006152A1 (fr) * 2014-07-11 2016-01-14 パナソニックＩｐマネジメント株式会社 Bloc-batterie de stockage, et procédé de fonctionnement de bloc-batterie de stockage
WO2017134995A1 (fr) * 2016-02-03 2017-08-10 パナソニックＩｐマネジメント株式会社 Procédé de commande de dispositif serveur, et dispositif serveur
JP2017175736A (ja) * 2016-03-22 2017-09-28 日立マクセル株式会社 二次電池の充電機構、二次電池の充電装置、および、二次電池パック

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023132185A1 (fr) * 2022-01-07 2023-07-13 株式会社デンソー Bloc-batterie, procédé de configuration, procédé de traitement et programme de traitement
US11597295B1 (en) 2022-03-25 2023-03-07 Beta Air, Llc System for monitoring a battery system in-flight and a method for its use
US11858376B2 (en) 2022-03-25 2024-01-02 Beta Air, Llc System for monitoring a battery system in-flight and a method for its use
KR102615678B1 (ko) * 2023-04-27 2023-12-20 켄코아에비에이션 주식회사 유무인 비행체용 충전 및 진단 검사 통합 방법, 장치 및 시스템

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CN116154913A (zh) 2023-05-23
JPWO2019172060A1 (ja) 2021-04-22
CN111357147A (zh) 2020-06-30
JP7036393B2 (ja) 2022-03-15
JP7178743B2 (ja) 2022-11-28
JP2022008458A (ja) 2022-01-13
JP2022001483A (ja) 2022-01-06

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