WO2016059953A1 - Système d'alimentation en énergie électrique - Google Patents

Système d'alimentation en énergie électrique Download PDF

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Publication number
WO2016059953A1
WO2016059953A1 PCT/JP2015/076989 JP2015076989W WO2016059953A1 WO 2016059953 A1 WO2016059953 A1 WO 2016059953A1 JP 2015076989 W JP2015076989 W JP 2015076989W WO 2016059953 A1 WO2016059953 A1 WO 2016059953A1
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WIPO (PCT)
Prior art keywords
power supply
supply system
moving body
power
flight
Prior art date
Application number
PCT/JP2015/076989
Other languages
English (en)
Japanese (ja)
Inventor
鈴木　康輔
正祥 増田
Original Assignee
ソニー株式会社
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Filing date
Publication date
Application filed by ソニー株式会社 filed Critical ソニー株式会社
Publication of WO2016059953A1 publication Critical patent/WO2016059953A1/fr

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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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F3/00—Ground installations specially adapted for captive aircraft
    • B64F3/02—Ground installations specially adapted for captive aircraft with means for supplying electricity to aircraft during flight
    • 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
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • 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
    • 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
    • H02J7/02—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from ac mains by converters
    • H02J7/04—Regulation of charging current or voltage
    • 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
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • 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
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates to a power supply system.
  • a technique relating to a method of taking a photograph in which a camera is attached to a moving body such as a flying body or a robot that can be operated wirelessly and captured by the camera is disclosed (for example, see Patent Document 1).
  • a moving body such as a flying body or a robot that can be operated wirelessly and captured by the camera
  • Patent Document 1 A technique relating to a method of taking a photograph in which a camera is attached to a moving body such as a flying body or a robot that can be operated wirelessly and captured by the camera is disclosed (for example, see Patent Document 1).
  • the cost can be reduced compared to using a real airplane or helicopter, images can be taken safely, images can be taken even in low altitudes and narrow places, and the target is approached.
  • Patent Document 2 discloses a technique that removes the restriction on continuous operation time by supplying power to the flying object by wire.
  • the present disclosure proposes a new and improved power supply system capable of transmitting to the mobile body power that can be operated without limiting the movement of the mobile body.
  • the mobile body includes: a mobile body; a booster that boosts the voltage to a voltage larger than a rating of the mobile body; and a conductor that transmits electric power generated by the voltage boosted by the booster to the mobile body.
  • a power supply system including a step-down unit for stepping down the voltage of the power transmitted through the conducting wire to a rating of the moving body.
  • FIG. 3 is an explanatory diagram illustrating an appearance example of a flying device 100 according to an embodiment of the present disclosure. It is explanatory drawing shown about the discrimination
  • Patent Document 2 described above discloses a technique that removes the restriction of continuous operation time by supplying power to the flying object by wire.
  • the present disclosure has intensively studied a technology that can transmit the electric power that the moving body can operate to the moving body without restricting the movement of the moving body.
  • the present disclosure person can operate the mobile body without restricting the movement of the mobile body by transmitting the power to the mobile body after boosting the voltage above the rated voltage of the mobile body, as will be described below. It came to devise the technology which can transmit electric power to a moving body.
  • FIG. 1 is an explanatory diagram illustrating an overall configuration example of a power supply system according to an embodiment of the present disclosure.
  • FIG. 1 shows a configuration example of an electric power supply system for transmitting electric power that can be operated by a flying object to the flying object, which is an example of a moving object.
  • an overall configuration example of the power supply system according to an embodiment of the present disclosure will be described with reference to FIG.
  • the power supply system 1 includes a power supply device 10 and a flying device 100.
  • the power supply device 10 is a device that supplies power to the flying device 100.
  • the power supply device 10 supplies DC power to the flying device 100.
  • the power supply device 10 is connected to the flying device 100 by a conducting wire 20 when supplying DC power to the flying device 100.
  • the power supply device 10 When supplying DC power to the flying device 100 through the conductor 20, the power supply device 10 supplies DC power boosted to a voltage several tens of times the voltage (rated voltage) used in the flying device 100.
  • the conductive wire 20 be thin and light so that it can withstand transmission of DC power boosted by the power supply device 10 and does not hinder the free flight of the flying device 100.
  • the conductor 20 preferably has a cross-sectional size of approximately 0.125 square and a length of approximately 80 to 100 meters.
  • the size and length of the cross-sectional area of the conducting wire 20 are not limited to this.
  • the conductive wire 20 has a diameter of approximately 0.4 mm, a cross-sectional area of approximately 0.13 mm 2 or less, a mass of approximately 1.1 kg / km, a resistance value of approximately 150 ⁇ / km, and a length of approximately 100 m. It is.
  • the flying device 100 is a device that flies using DC power supplied from the power supply device 10 through the conductor 20 as a power source.
  • the flying device 100 functions to fly based on, for example, a pilot by a user or according to a preset flight path.
  • the flying device 100 includes an imaging device and functions to image roads, bridges, tunnels, and other buildings.
  • the flying device 100 may not include an imaging device.
  • the power supply system 1 supplies DC power through the conductor 20.
  • AC power is transmitted at a high voltage
  • noise is generated around the conducting wire, which affects the operation of the flying device 100 and also affects the operation of other electronic devices.
  • the power supply system 1 according to an embodiment of the present disclosure can significantly reduce noise around the conductor 20.
  • the flying device 100 is a device that flies by rotating a blade (rotor) using a motor.
  • the power supply system 1 according to an embodiment of the present disclosure transmits power from the power supply device 10 to the flying device 100 with a high voltage, so that it is highly resistant to voltage fluctuations even when a load with a large power change such as a motor is used. Stable power supply to the load becomes possible.
  • FIG. 2 is an explanatory diagram illustrating a functional configuration example of the power supply system 1 according to an embodiment of the present disclosure.
  • the power supply device 10 includes a DC power supply 11 and a booster 12.
  • the power supply device 10 boosts the DC power supplied from the DC power supply 11 with the booster 12 and supplies the DC power to the flying device 100 through the conductor 20.
  • the DC power supply 11 may supply DC power having a voltage of 12 V and a current of 12 A, for example.
  • the power supply device 10 supplies the electric power boosted by the booster 12 to a voltage of about 400 V, for example, to the flying device 100 through the conductor 20.
  • the power supply device 10 can reduce the current flowing through the conductor 20 to 0.36 A by increasing the DC power of the voltage 12 V and the current 12 A to about 400 V.
  • the flying device 100 includes a step-down device 160 and a load 170.
  • the step-down device 160 steps down the electric power supplied from the power supply device 10, for example, with a voltage of 400 V to a voltage (rated voltage) used in the flying device 100.
  • the step-down device 160 supplies electric power whose voltage is stepped down to the load 170.
  • the load 170 in the flying device 100 includes, for example, a motor for rotating the rotor, a processor for controlling flight, a memory, and the like. A specific functional configuration example of the flying device 100 will be described later.
  • the power supply device 10 has the DC power supply 11, but the power supply device 10 may have an AC power supply, or may receive power from a commercial AC power supply. .
  • a configuration example in the case where the power supply apparatus 10 has an AC power supply or receives power supply from a commercial AC power supply is shown.
  • FIG. 3 is an explanatory diagram illustrating a functional configuration example of the power supply system 1 according to an embodiment of the present disclosure.
  • the power supply apparatus 10 includes an AC power supply 13 and a booster 14.
  • the power supply device 10 converts the AC power supplied from the AC power supply 13 into DC power in the booster 14, boosts the AC power, and supplies the boosted power to the flying device 100 through the conductor 20.
  • the power supply device 10 supplies the electric power boosted by the booster 14 to a voltage of about 400 V, for example, to the flying device 100 through the conductor 20.
  • the power supply system 1 is not limited to the power of the power source included in the power supply device 10 or the form of power supplied from the outside, and the flying device 100 through the conductor 20. Can be supplied with DC power.
  • the power supply system 1 is capable of flying by making the conductor 20 capable of withstanding transmission of DC power boosted by the power supply device 10 and being thin and light. It is possible to reliably supply power from the power supply device 10 for the operation of the device 100 and not to prevent free flight of the flying device 100.
  • FIG. 4 is an explanatory diagram illustrating a functional configuration example of the flying device 100 according to an embodiment of the present disclosure.
  • the functional configuration example of the flying device 100 according to the embodiment of the present disclosure will be described with reference to FIG.
  • the flying device 100 includes an imaging device 101, rotors 104a to 104d, motors 108a to 108d, a control unit 110, a communication unit 120, and a sensor unit. 130, a position information acquisition unit 132, a storage unit 140, and a battery 150.
  • the control unit 110 controls the operation of the flying device 100.
  • the control unit 110 may be configured to include a memory such as a CPU (Central Processing Unit), a ROM (Read Only Memory), a RAM (Random Access Memory), and the like.
  • a memory such as a CPU (Central Processing Unit), a ROM (Read Only Memory), a RAM (Random Access Memory), and the like.
  • the control unit 110 adjusts the rotational speeds of the rotors 104a to 104d by adjusting the rotational speeds of the motors 108a to 108d, performs imaging processing by the imaging device 101, and transmits / receives information to / from other devices via the communication unit 120.
  • the storage and reading of information with respect to the storage unit 140 can be controlled.
  • control unit 110 controls the flight by adjusting the rotation speeds of the motors 108a to 108d and the execution of the still image capturing process for the image capturing apparatus 101.
  • the image pickup apparatus 101 includes a lens, an image pickup device such as a CCD image sensor and a CMOS image sensor, a flash, and the like.
  • the imaging device 101 provided in the flying device 100 performs still image or moving image imaging under the control of the control unit 110.
  • An image captured by the imaging apparatus 101 is transmitted from the communication unit 120 to an external apparatus.
  • the imaging device 101 executes imaging processing based on information on the imaging position of a still image included in flight information transmitted from another device.
  • An image obtained by the imaging process of the imaging device 101 can be stored in the storage unit 140 or transmitted from the communication unit 120 to an external device.
  • the imaging apparatus 101 can change the imaging direction to an arbitrary direction by control from the control unit 110, for example. For example, when the horizontal direction of the hovering camera is set to 0 degrees, it is possible to capture an imaging direction represented by a range of ⁇ 90 degrees in the vertical direction. Since the imaging device 101 can change the imaging direction, the flying device 100 can capture an image in a predetermined direction.
  • the rotors 104a to 104d cause the flying device 100 to fly by generating lift by rotation.
  • the rotors 104a to 104d are rotated by the rotation of the motors 108a to 108d.
  • the motors 108a to 108d rotate the rotors 104a to 104d.
  • the rotation of the motors 108a to 108d can be controlled by the control unit 110.
  • the communication unit 120 performs information transmission / reception processing by wireless communication with other devices.
  • the communication unit 120 can be configured by, for example, a communication circuit that performs transmission / reception processing, an antenna that performs wireless communication, and the like.
  • the flying device 100 may transmit an image captured by the imaging device 101 from the communication unit 120 to another device. Further, the flying device 100 may receive an instruction relating to flight from another device by the communication unit 120.
  • FIG. 1 shows a form in which the power supply device 10 and the flying device 100 are connected by a conducting wire 20, the power supplying device 10 and the flying device 100 are connected by a cable including the conducting wire 20. May be.
  • the cable may include a wire for wire communication in addition to the wire 20 for supplying power.
  • the number of cables may be one or a plurality.
  • the communication unit 120 may perform wired communication with other devices. When wired communication is performed between the flying device 100 and another device, the communication unit 120 performs wired communication with the other device using a wire for wired communication included in the cable. By connecting the power supply device 10 and the flying device 100 with a cable composed of a plurality of conducting wires, the communication state of the image captured by the flying device 100 and the operation information for operating the flying device 100 can be determined. This is better than in the case of wireless communication.
  • the sensor unit 130 is a device group that acquires the state of the flying device 100, and may be configured by, for example, an acceleration sensor, a gyro sensor, an ultrasonic sensor, an atmospheric pressure sensor, a contact sensor, a tension sensor, an optical flow sensor, a laser range finder, and the like. .
  • the sensor unit 130 may convert the acquired state of the flying device 100 into a predetermined signal and provide it to the control unit 110 as necessary.
  • the position information acquisition unit 132 is, for example, a GPS (Global Positioning System), a GNSS (Global Information on the current position of the flying device 100 is acquired using a navigation satellite system), a vision sensor, or the like.
  • the position information acquisition unit 132 can provide the acquired information on the current position of the flying device 100 to the control unit 110 as necessary.
  • the control unit 110 uses the information on the current position of the flying device 100 acquired by the position information acquiring unit 132 to execute flight control of the flying device 100 based on flight information received from another device.
  • the sensor unit 130 detects an obstacle that may hinder flight during flight.
  • the flying device 100 can provide information regarding the detected obstacle to other devices.
  • the sensor unit 130 detects the presence / absence of contact of the conductive wire 20, the contact position and the contact direction when there is a contact, and the like. Further, the sensor unit 130 detects the presence / absence of the pulling of the conductive wire 20 and the direction and number of times of pulling when there is a pulling.
  • the storage unit 140 stores various information.
  • the storage unit 140 can be configured by a rewritable memory such as a flash memory. Examples of the information stored in the storage unit 140 include flight information of the flying device 100 transmitted from another device, an image captured by the imaging device 101, and the like.
  • the battery 150 stores electric power for temporarily operating the flying device 100 when the power supply from the power supply device 10 is interrupted.
  • the battery 150 may be a primary battery that can only be discharged, or may be a secondary battery that can be charged. However, the power supply from the power supply device 10 may be performed by cutting the conductor 20 or the power supply device. In the case of interruption for some reason such as 10 problems, the power for temporarily operating the flying device 100 is stored, so that it is sufficient to have a capacity capable of flying for about several minutes.
  • the step-down device 160 steps down the DC power supplied from the power supply device 10 through the conductor 20 to the rated voltage in the flying device 100. For example, when the voltage of the DC power supplied from the power supply device 10 through the conductor 20 is 400V and the rated voltage in the flying device 100 is 12V, the step-down device 160 steps down the 400V voltage to 12V. The stepped down power is supplied to the motors 108 a to 108 d and other blocks of the flying device 100.
  • the flying device 100 can operate based on the power supplied from the power supply device 10 through the conductor 20 by having the configuration as shown in FIG.
  • the weight of the flying device 100 that rotates four rotors 104a to 104d as shown in FIG. 4 is 300 g
  • a battery with a voltage of 11.2 V, a capacity of 1300 mAh, and a weight of 110 g is used.
  • Experiments by the present disclosure have shown that it is possible to fly for approximately 8 minutes.
  • the battery capacity needs to be increased. For example, when the battery voltage is the same 11.2 V and the capacity is increased to 2200 mAh, the weight of the battery is about 262 g. Also, for example, if the battery voltage is the same 11.2 V and increased to 5000 mAh, the weight of the battery becomes approximately 397 g.
  • the weight of the 5000 mAh battery becomes heavier than the weight of the flying device 100, making it impossible to fly with the same aircraft, and a larger aircraft must be created. In addition, as the weight of the battery increases, more power must be consumed for buoyancy.
  • the step-down device 160 is realized with the same size as the above-mentioned battery capable of flying for 8 minutes, it can be realized in a light weight.
  • the step-down device 160 can be realized with a weight of about 50 g. Therefore, when the step-down device 160 is provided in place of the above-described battery, the step-down device 160 is 60 g lighter than the above-described battery, and the flying device 100 can obtain surplus buoyancy for 60 g lightened.
  • the flying device 100 which concerns on one Embodiment of this indication is equipped with the battery 150 which stores the electric power for operating the flying device 100 temporarily, and the electric power supply from the electric power supply apparatus 10 is for some reason Even if it is interrupted, flight can be continued.
  • the flying device 100 switches the battery 150 to a power source so as to fly to a predetermined position. You may control by the control part 110, and you may control by the control part 110 so that it may descend
  • FIG. 5 is an explanatory diagram illustrating an appearance example of the flying device 100 according to an embodiment of the present disclosure.
  • the flying device 100 is stabilized without being affected by the lead wire 20 by being connected to the lead wire 20 so that the lead wire 20 extends from the center of gravity at the center of the fuselage toward the bottom of the fuselage. You can fly. Further, since the conductor 20 is connected to the conductor 20 so that the conductor 20 extends from the center of gravity of the aircraft toward the lower part of the aircraft, the flying device 100 can fly so that the conductor 20 does not get entangled with the rotors 104a to 104d. I can do it. In FIG.
  • a state is shown in which the conductor 20 is connected to the conductor 20 so that the conductor 20 extends from the center of gravity at the center of the aircraft toward the lower side of the aircraft, but the present disclosure is not limited to such an example. Instead, the conductor 20 may be connected to the conductor 20 so that the conductor 20 extends from the center of gravity at the center of the aircraft toward the upper side of the aircraft.
  • the flying device 100 may be connected to the conductive wire 20 on its surface by a rotating connector that can conduct electricity.
  • the lead wire 20 can be prevented from being twisted by the flight of the flying device 100.
  • the flying device 100 is connected to the conducting wire 20 by a rotary connector that can conduct electricity by being boosted to a very high voltage in the power supply device 10, the electric power by the rotary connector that can conduct electricity. Little affected by loss.
  • a rotary connector or a slip ring can be used as the rotary connector that can conduct electricity.
  • the flying device 100 may perform posture determination using the position of the connected conductor 20.
  • FIG. 6 is an explanatory diagram showing the posture determination using the position of the conducting wire 20 by the flying device 100.
  • FIG. 6 shows a state in which the contact sensors 131a and 131b constituting the sensor unit 130 of FIG.
  • Contact sensors 131a and 131b are sensors for detecting the contact of the conductive wire 20. If the conducting wire 20 does not touch the contact sensors 131a and 131b, the flying device 100 can determine that it is in a horizontal state. On the other hand, if the conducting wire 20 touches one of the contact sensors 131a and 131b, the flying device 100 can determine that it is tilted.
  • the number, position, and size of the contact sensors for detecting the contact of the conductive wire 20 are not limited to those shown in FIG.
  • the power supply system 1 may extend the conductive wire 20 from the apex of a pole extended from the power supply device 10 or installed in the vicinity of the power supply device 10.
  • FIG. 7 is an explanatory diagram illustrating a configuration example of the power supply system 1 according to an embodiment of the present disclosure.
  • FIG. 7 shows a state in which a pole 30 having a predetermined length extends from the power supply device 10, and the conductor 20 extends from the vicinity of the apex of the pole 30.
  • the flying device 100 is connected to the power supply device 10 by the conducting wire 20, so that the flight range is restricted by the conducting wire 20.
  • the limitation of the flight range of the flying device 100 is eliminated by moving the power supply device 10. For example, by placing the power supply device 10 on a vehicle body such as a passenger car or a truck and repeating the movement of the power supply device 10 and the flight of the flying device 100, the restriction on the flight range of the flying device 100 can be eliminated.
  • the movement of the power supply device 10 and the flying device 100 are performed.
  • the flight may be performed in parallel.
  • the flying device 100 may detect that the conducting wire 20 has been pulled based on the sensing data from the sensor unit 130 by the control unit 110 and perform a flight based on the detection.
  • the flying device 100 may be detected by the sensor unit 130 in the direction in which the conductor 20 is pulled by the user, and may be controlled by the control unit 110 so as to fly in the direction pulled by the user.
  • the flying device 100 may detect the number of times that the conducting wire 20 has been pulled by the user based on the sensing data from the sensor unit 130 by the control unit 110 and perform a flight based on the detection.
  • the flying device 100 controls the controlling unit 110 to fly in the direction in which the conducting wire 20 is pulled.
  • the control unit 110 may control to fly to a predetermined position according to the pull.
  • the above-described relationship between the number of pulls and flight control is merely an example, and it goes without saying that the relationship between the number of pulls and flight control can be set as appropriate.
  • the conducting wire 20 may have a function of communicating information in addition to a function of supplying power. That is, the power supply system 1 according to the present embodiment causes the power supply device 10 to superimpose predetermined information on the DC power and transmit the power with the information to the flying device 100 through the conductor 20. Good.
  • the conductor 20 may be cut off.
  • the flying device 100 may use the sensor unit 130 to detect that a sudden change has occurred in the posture.
  • the flying device 100 may notify other devices, for example, the power supply device 10, that the posture has suddenly changed.
  • the flying device 100 may notify other devices, for example, the power supply device 10, that the posture has suddenly changed.
  • the flying device 100 may notify other devices, for example, the power supply device 10, that the posture has suddenly changed.
  • whether or not a sudden change has occurred in the posture may be determined by whether or not the data sensed by the sensor unit 130 has changed by a predetermined threshold or more per unit time.
  • the power supply device 10 When the power supply device 10 receives a notification from the flying device 100 that a sudden change has occurred in the attitude of the flying device 100, for example, the power supply device 10 automatically winds up the conductor 20 to stabilize the attitude of the flying device 100. Such an operation may be executed.
  • the conducting wire 20 is thin and light so as not to prevent free flight of the flying device 100, winding by the power supply device 10 is facilitated.
  • the winding of the conducting wire 20 may be performed by a human.
  • the power supply system 1 that supplies power from the power supply device 10 to the flying device 100 through the conductor 20 is provided.
  • the power supply system 1 according to the embodiment of the present invention supplies the power supply device 10 to the flight device 100 from the power supply device 10 through the lead wire 20 with the power supply device 10 having a voltage that is significantly higher than the rated voltage of the flight device 100. .
  • the power supply system 1 can permanently supply power to the flying device 100 as long as power is not interrupted in the power supply device 10 or the conductor 20 is not disconnected. become.
  • the power supply system 1 By supplying power to the flying device 100 permanently, the power supply system 1 according to an embodiment of the present disclosure dramatically increases the flight duration of the flying device 100 compared to a case where only the battery is provided. Can be improved.
  • the power supply system 1 can save the trouble of charging and replacing the battery of the flying device 100 by supplying the flying device 100 from the power supply device 10 to the flying device 100 through the conductor 20.
  • the mobile body which receives supply of electric power from the power supply apparatus 10 is not limited to the flying apparatus 100, for example, It may be a device such as a robot that operates by receiving power.
  • a moving object A booster that boosts the voltage to a voltage greater than the rating of the mobile body;
  • a conducting wire that transmits electric power generated by the voltage boosted by the boosting unit to the moving body;
  • the moving body is A power supply system including a step-down unit for stepping down a voltage of electric power transmitted through the conducting wire to a rating in the moving body.
  • the power supply system according to (1), wherein the power transmitted through the conducting wire is DC power.
  • the moving body includes a control unit that detects pulling of the conducting wire.
  • the said control part is an electric power supply system as described in said (3) which controls the said mobile body to fly in the direction of the pull of the detected said conducting wire.
  • the said control part is an electric power supply system as described in said (3) or (4) which controls the flight of the said mobile body according to the frequency
  • the said mobile body is a power supply system as described in said (1) provided with the battery for continuing the flight of the said mobile body when the electric power supply from the said conducting wire stops.
  • the moving body is A power detection unit for detecting that power supply from the conducting wire has been interrupted; When the power detection unit detects that the power supply from the conducting wire has been interrupted, a flight control unit that controls the flight of the mobile body to perform a predetermined flight with the power of the battery;
  • the power supply system according to (6) comprising: (8)
  • the said flight control part is an electric power supply system as described in said (7) which controls flight of the said mobile body so that it may fly to a predetermined position.
  • the boosting unit boosts the voltage to a voltage of 30 times or more of a rating of the moving body.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Power Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

L'invention a pour objet la fourniture d'un système d'alimentation en énergie électrique capable de fournir à un corps mobile de l'énergie électrique grâce à laquelle le corps mobile est apte à fonctionner, sans imposer aucune limitation au mouvement du corps mobile. Pour ce faire, l'invention concerne un système d'alimentation en énergie électrique comprenant un corps mobile, une unité d'élévation destinée à élever la tension à un niveau plus élevé que la tension nominale du corps mobile, et un fil conducteur destiné à transmettre de l'énergie électrique à la tension élevée par l'unité d'élévation au corps mobile, le corps mobile comprenant une unité d'abaissement destinée à abaisser la tension de l'énergie électrique transmise par le fil conducteur à la tension nominale du corps mobile.
PCT/JP2015/076989 2014-10-17 2015-09-24 Système d'alimentation en énergie électrique WO2016059953A1 (fr)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018002775A1 (fr) * 2016-07-01 2018-01-04 Elistair Dispositif d'alimentation pour drone filaire
CN108725768A (zh) * 2018-05-30 2018-11-02 同济大学 一种系留无人机装置
WO2019090865A1 (fr) * 2017-11-08 2019-05-16 珠海市双捷科技有限公司 Station terrestre captive et système de drone captif
JP2019182228A (ja) * 2018-04-11 2019-10-24 株式会社荏原製作所 有線ドローンシステム

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Publication number Priority date Publication date Assignee Title
US20070200027A1 (en) * 2006-02-24 2007-08-30 Johnson Samuel A Aerial robot
WO2014027097A2 (fr) * 2012-08-17 2014-02-20 Markus Waibel Caméra volante avec ensemble de ficelle à des fins de localisation et d'interaction
JP2014031118A (ja) * 2012-08-03 2014-02-20 Tsubakimoto Chain Co 飛行体及び飛行体システム

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070200027A1 (en) * 2006-02-24 2007-08-30 Johnson Samuel A Aerial robot
JP2014031118A (ja) * 2012-08-03 2014-02-20 Tsubakimoto Chain Co 飛行体及び飛行体システム
WO2014027097A2 (fr) * 2012-08-17 2014-02-20 Markus Waibel Caméra volante avec ensemble de ficelle à des fins de localisation et d'interaction

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018002775A1 (fr) * 2016-07-01 2018-01-04 Elistair Dispositif d'alimentation pour drone filaire
FR3053259A1 (fr) * 2016-07-01 2018-01-05 Elistair Dispositif d'alimentation pour drone filaire
US11059580B2 (en) 2016-07-01 2021-07-13 Elistair Device for supplying power to a wired drone
WO2019090865A1 (fr) * 2017-11-08 2019-05-16 珠海市双捷科技有限公司 Station terrestre captive et système de drone captif
JP2019182228A (ja) * 2018-04-11 2019-10-24 株式会社荏原製作所 有線ドローンシステム
JP7085880B2 (ja) 2018-04-11 2022-06-17 株式会社荏原製作所 有線ドローンシステム
CN108725768A (zh) * 2018-05-30 2018-11-02 同济大学 一种系留无人机装置

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