WO2017131451A1 - Drone - Google Patents

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Publication number
WO2017131451A1
WO2017131451A1 PCT/KR2017/000917 KR2017000917W WO2017131451A1 WO 2017131451 A1 WO2017131451 A1 WO 2017131451A1 KR 2017000917 W KR2017000917 W KR 2017000917W WO 2017131451 A1 WO2017131451 A1 WO 2017131451A1
Authority
WO
WIPO (PCT)
Prior art keywords
unmanned flying
battery
flexible
flying device
power
Prior art date
Application number
PCT/KR2017/000917
Other languages
English (en)
Korean (ko)
Inventor
노승윤
정상동
Original Assignee
주식회사 아모그린텍
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 주식회사 아모그린텍 filed Critical 주식회사 아모그린텍
Publication of WO2017131451A1 publication Critical patent/WO2017131451A1/fr

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    • 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
    • H01M10/04—Construction or manufacture in general
    • 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
    • B60L50/64—Constructional details of batteries specially adapted for electric vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • 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
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
    • 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
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • 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
    • 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
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics
    • 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
    • B64U50/32—Supply or distribution of electrical power generated by fuel cells
    • 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
    • H01M10/04—Construction or manufacture in general
    • H01M10/045—Cells or batteries with folded plate-like electrodes
    • 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
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/60—UAVs characterised by the material
    • 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
    • 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
    • B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • 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

  • the present invention relates to an unmanned flying device, and relates to an unmanned flying device that can fly indoors or in the atmosphere.
  • an unmanned flying apparatus includes a control system for flight control and an unmanned aerial vehicle that performs a flight according to a flight control signal transmitted from a control system at a remote location, and acquires various local data and transmits it to a control system.
  • the unmanned aerial vehicle is equipped with electronic equipment including a camera unit, a sensor module, a communication module, and the like, and is remotely controlled or autonomous. That is, the unmanned aerial vehicle may be directly remotely controlled by the user, or when the operator preprograms points to be passed by the unmanned aerial vehicle, the unmanned aerial vehicle may fly by adjusting the flight trajectory to reach the point.
  • such an unmanned flying device is mounted with a rectangular solid battery to drive the above-described electronic equipment.
  • the weight of such a solid battery increases as the storage capacity increases. Therefore, when the battery having a high capacity is mounted, the weight of the portion on which the battery is mounted is relatively concentrated compared to other portions, so that the direction of the unmanned flying device may not be changed quickly.
  • the weight of the unmanned flying device is also increased by increasing the weight of the battery, the power consumption is increased, thereby reducing the overall running time.
  • the present invention has been made in view of the above, and an object thereof is to provide an unmanned flying device capable of reducing the weight of a battery and distributing the weight of the battery.
  • the present invention to solve the above problems the body portion; A plurality of power generators connected to the body and generating power for flight; A plurality of connection portions connecting the body portion and the power generation portion; And a power supply unit supplying power for driving the power generation unit, wherein the power supply unit is a plate-shaped flexible battery that is built in at least one side of the plurality of connection units.
  • the flexible battery may include a plurality of flexible batteries having the same weight and may be built in the plurality of connection units, respectively.
  • the body portion may include an accommodating portion which is open at one side and drawn inward.
  • it may further include a plurality of supports coupled to the body portion having a predetermined length.
  • the apparatus may further include a plurality of fastening units which are coupled to each of the free ends of the plurality of supports and detached from the object to be transferred.
  • the flexible battery an electrode assembly; And an exterior member encapsulating the electrode assembly together with an electrolyte solution, wherein the electrode assembly and the exterior member may be formed to coincide with each other so that a pattern for contraction and relaxation in the longitudinal direction may match each other.
  • the pattern may be formed on the entire length of the flexible battery, and may be locally formed on the length of a part of the entire length of the flexible battery.
  • the fuselage portion including the main blade fixedly coupled in the horizontal direction; And a power supply unit embedded in the fuselage to supply power for driving the controller, wherein the power supply comprises at least one flexible battery wound at least once around an axial direction of the fuselage. to provide.
  • the flexible battery may be provided in plural numbers arranged along the axial direction of the body portion, and the plurality of flexible batteries may be electrically connected to each other.
  • each of the flexible batteries arranged along the axial direction of the fuselage may be a battery connection body connected in parallel with each other after the plurality of flexible batteries are arranged in a straight line.
  • At least two flexible batteries of the plurality of flexible batteries constituting the battery connector may be disposed such that terminals thereof face each other.
  • the main wing includes a plurality of solar panels are arranged on the outer surface, the power supply may be charged through the power generated from the solar panel.
  • the unmanned aerial vehicle may further include at least one camera unit for capturing an external image.
  • a plurality of flexible batteries are distributed in each of the connecting portions or distributed in the longitudinal direction of the fuselage, so that the weight of the battery is not concentrated compared to the conventional unmanned flying device in which a solid solid battery is disposed in the body portion. Can be. Accordingly, the flight direction of the unmanned aerial vehicle can be changed more easily.
  • the unmanned flying apparatus includes a flexible battery which is lighter in weight than the storage capacity of the solid battery, so that the overall weight can be reduced, thereby reducing power consumption and increasing flight time.
  • the unmanned flying device according to the present invention can increase the space utilization of the body portion because it does not require a space for mounting a solid solid battery of the prior art.
  • a communication module or various electronic devices for compressing and transmitting an image captured by a camera unit in real time may be further mounted on the body.
  • the unmanned flying apparatus may prevent the flexible battery from being damaged or deteriorated through the pattern even when the connection part is repeatedly bent by an external force when the flexible battery is built in the connection part.
  • FIG. 1 is a view showing an unmanned flying device according to an embodiment of the present invention
  • FIG. 2 is a view showing an unmanned flying device according to another embodiment of the present invention.
  • FIG. 3 is a view showing an unmanned flying device according to another embodiment of the present invention.
  • FIG. 4 is a block diagram showing a connection relationship between a control unit and various electronic units in the unmanned flying apparatus according to the present invention
  • FIG. 5 is a schematic view showing a flexible battery that can be applied to the unmanned flying apparatus according to the present invention.
  • FIG. 6 is an exemplary view illustrating various patterns applied to an electrode assembly and an exterior member in a flexible battery applied to an unmanned flying device according to the present invention, illustrating various intervals between adjacent valleys or mountains,
  • FIG. 7 is an enlarged view showing the detailed configuration of a flexible battery applied to the unmanned flying device according to the present invention.
  • FIG. 8 is a view showing an unmanned flying device according to another embodiment of the present invention.
  • FIG. 9 is a view showing a connection relationship of the flexible battery that can be applied to FIG.
  • FIG. 10 is a view showing another connection relationship of the flexible battery that can be applied to FIG. 8,
  • FIG. 11 is a view illustrating one flexible battery of FIG. 9; FIG.
  • FIG. 12 is a view showing an extract of one battery connector in FIG. 10, and
  • FIG. 13 is a view illustrating a state in which a solar cell panel is applied to FIG. 7.
  • the unmanned flying apparatus 100, 200, 200 ′ includes a body 110, a power generator 120, a connection 130, and a power supply S as shown in FIGS. 1 to 3. Include.
  • the body 110 may include a circuit board (not shown) capable of overall control of the unmanned flying device 100.
  • the material of the body 110 may be plastic or metal, but is not limited thereto.
  • the power generator 120 may be connected to the body 110 to generate power for the flight of the body 110.
  • the power generator 120 may include a housing 121, a motor 122, and a propeller 123.
  • the housing 121 may be fixedly coupled to the body portion 110 via the connection portion 130.
  • a power generator 120 may be one, but may be provided in plurality so as to be free to change direction, the plurality of power generator 120 may be disposed at an equal angle to each other.
  • the unmanned flight apparatus 100, 200, 200 ′ when the unmanned flight apparatus 100, 200, 200 ′ according to an embodiment of the present invention includes four power generators 120, the four power generators 120 may be configured based on the body 110. It may be arranged to achieve an angle of °.
  • the unmanned aerial vehicle 100, 200, 200 ′ when the unmanned aerial vehicle 100, 200, 200 ′ includes three power generators 120, the three power generators 120 may have an angle of 120 ° based on the body 110. It can be arranged to achieve.
  • the material of the housing 121 may be the same material as the body part 110, but is not limited thereto.
  • the material of the housing 121 may be a material different from that of the body part 110.
  • the motor 122 is driven by using the power supplied from the power supply unit S, and may be disposed inside the housing 121, and the rotation shaft of the motor 122 is upward from the housing 121. Or downwards. However, the rotating shaft of the motor 122 may be advantageously exposed upward from the housing 121 to prevent interference with the ground during takeoff and landing.
  • the propeller 123 may be fixedly coupled to the rotating shaft of the motor 122. Accordingly, when the motor 122 is driven, lift force or propulsion force is generated while the propeller 123 is rotated, so that the unmanned flying device 100, 200, 200 ′ may fly. In addition, when the unmanned flying device 100 includes a plurality of power generators 120, the flight direction may be varied according to the output difference of the propellers 123 included in each of the power generators 120. .
  • connection portion 130 connects the body part 110 and the power generation part 120.
  • the material of the connection portion 130 may be the same as the material of the body portion 110, for example.
  • the shape of the connection unit 130 may be, for example, a pipe shape, but is not limited thereto.
  • the cable that can be electrically connected to the inside of the connection portion 130 may be disposed.
  • One end of the cable may be connected to a circuit board of the body portion 110, and the other end thereof may be connected to the power generator 120.
  • the cable is not necessarily disposed inside the connecting portion 130, the circuit board and the power generating unit 120 is mutually through an electrode pattern (not shown) formed on the inner surface of the connecting portion 130. It may be electrically connected.
  • the power supply unit S is for supplying power for driving the motor 122.
  • the power supply S may be a plate-shaped flexible battery 140, and may be embedded in at least one of the plurality of connection units 130.
  • the flexible battery 140 may be provided in plural so as to constitute a high capacity power supply S and implement overall weight balancing, and may be embedded in the plurality of connection units 130.
  • all of the flexible batteries 140 embedded in the plurality of connection units 130 may have the same weight and may have the same storage capacity.
  • each of the flexible batteries 140 built in the plurality of connection units 130 has the same weight, and thus, the inside of the body part 110. Compared to a conventional unmanned flying device in which a solid solid battery is built in, the weight of the battery can be distributed without being concentrated in a local position.
  • a light weight can be realized by configuring the power supply unit S through the flexible battery 140 which is relatively light in weight.
  • the weight of a solid battery having a storage capacity of 4000mAh is about 1kg, while the weight of the flexible battery 140 having a storage capacity of 1000mAh is about 30g.
  • the unmanned aerial vehicle 100, 200, 200 ′ according to an embodiment of the present invention has the same storage capacity of 4000 mAh as that of a conventional solid battery when four flexible batteries 140 having a storage capacity of 1000 mAh are connected in parallel.
  • the total weight of the battery can be reduced to around 120g.
  • the unmanned aerial vehicle 100, 200, 200 ′ according to an embodiment of the present invention comprises a power supply S through a plurality of flexible batteries 140 that are relatively lighter in weight than the solid battery so that the solid battery is mounted.
  • the weight can be significantly reduced as compared to the conventional unmanned flying device. Through this, it is possible to reduce the total weight of the unmanned flying device (100, 200, 200 ') to reduce the power consumption by weight reduction, so that the overall flight time even if the total storage capacity of the power supply (S) is the same as the conventional unmanned flying device Can be increased.
  • the flexible battery 140 is embedded in the side of the connection unit 130 adjacent to the power generation unit 120, the flexible battery 140 is electrically compared with the unmanned flying device 100 in which the battery is located inside the body unit 110.
  • the voltage drop can be reduced by minimizing the paths through which power consumption can be reduced.
  • the unmanned flight apparatus 100, 200, 200 ′ when the unmanned flight apparatus 100, 200, 200 ′ according to an embodiment of the present invention needs to replace any one of the plurality of flexible batteries 140, the unmanned flight device 100, 200, 200 ′ may be replaced without replacing all of the plurality of flexible batteries 140. Maintenance costs can be reduced by only replacing the batteries that are needed.
  • the above-mentioned body portion 110 side may include a controller 190 for the overall control of the unmanned flying device (100, 200, 200 ').
  • a controller may be in the form of a chipset mounted on a circuit board (not shown).
  • the controller 190 may be a microprocessor, and may control the overall operation of the other electronic unit as well as the driving of the power generator 120.
  • the controller 190 may individually control the rotational force of the motor 122 included in the plurality of power generation units 120 according to the flight trajectory of the unmanned flight apparatus 100, 200, 200 ′.
  • the plurality of power generators 120 may be changed in various directions of flight of the unmanned flying apparatuses 100, 200, and 200 ′ according to the difference in the rotational force generated by the motor 122.
  • the unmanned flying apparatus 100, 200, 200 ′ may move forward or rotate according to the rotation speed of each motor 122.
  • the unmanned aerial vehicle 100, 200, 200 ′ may vertically rise or descend.
  • the flying method of the unmanned flying device 100, 200, 200 ′ is not limited thereto, and it is understood that various types of flying such as forward, backward, and rotation are possible by adjusting the outputs of the plurality of motors 122.
  • the unmanned flying apparatus 100, 200, 200 ′ may include a plurality of support units 160 as illustrated in FIGS. 1 to 3.
  • the plurality of support parts 160 may be formed in a stick shape so that one end may be coupled to one side of the body part 110 and the free end may be disposed downward.
  • the receiving part 111 having one side open to the body part 110 and formed inwardly is formed.
  • the accommodation part 111 may be in the form of a receiving groove having an upper portion, and a transfer object to be transported may be mounted on the receiving part 111 side.
  • the transfer object may be directly inserted into the receiving portion 111, or may be in the form of the storage member 150 is inserted into the receiving portion 111 in a state stored in a separate storage member 150.
  • the storage member 150 may be configured to have a size substantially the same as that of the accommodation portion 111, thereby preventing the storage member 150 from being separated from the accommodation portion 111 during transportation. It is possible to prevent the transfer object from being damaged.
  • the unmanned flying apparatus 200 ′ may further include a plurality of fastening units 170 as shown in FIG. 3.
  • the plurality of fastening units 170 may be coupled to the free ends of the plurality of support parts 160, and the case 10 in which a transfer object is accommodated may be detachably coupled to the fastening unit 170. That is, when the transfer object is a relatively larger size than the accommodating part 111, the case 10 in which the transfer object is stored through the fastening unit 170 is fastened so that the transfer object is stored in the case 10. It may be transferred in a state.
  • the case 10 has a coupling groove 11 may be formed on the upper side to facilitate the coupling with the fastening unit 170.
  • the coupling groove 11 may be formed to be introduced into a size that the fastening unit 170 can be accommodated.
  • the case 10 and the fastening unit 170 may be fixed through the fixing pin 12, but is not limited thereto.
  • the storage member 150 and the case 10 side may be provided with a cover (not shown) that can be opened and closed to insert or take out the transfer object.
  • the unmanned flying device 300, 400 may be a fixed wing type unmanned flying device including a fuselage 310, wings and power supply (S).
  • At least one wing 321 and 322 for generating lift force is fixedly coupled to the fuselage 310 as illustrated in FIGS. 8 and 13. Can be.
  • the wing portion may include a main wing 321 coupled to the body portion 310 in a horizontal direction and at least one tail wing 322 formed on the end side of the body portion 310,
  • the main wings 321 may be provided in pairs and coupled to both sides of the fuselage 310, or may be composed of one member and coupled to an upper side of the fuselage 310.
  • the configuration of the wing is not limited thereto, and the tail wing 322 may be omitted, or a separate auxiliary wing (not shown) may be formed on the main wing 321 side.
  • the fuselage 310 may be equipped with a power transmission unit such as a propeller driven by a motor so as to obtain a propulsion force for the flight, it may be found that the glider method without using a propeller. Since the structure of the flying device implemented in a fixed wing system as described above is well known, a detailed description thereof will be omitted.
  • the fuselage 310 may include a controller 190 for controlling the overall operation of the unmanned aerial vehicle 300, 400, and the controller 190 may receive the driving power through the power supply S. Can be.
  • the controller 190 may be a chipset type mounted on the circuit board 192 as described above.
  • the controller 190 may be a microprocessor and control the overall operation of various electronic units mounted on the fuselage 310.
  • the unmanned flying apparatus 300 or 400 may have a form in which a power supply S for providing driving power to the controller 190 is embedded in the fuselage 310, and the power supply unit ( S) may be configured of at least one flexible battery 140.
  • the power supply unit S may be embedded in the fuselage 310 as shown in FIGS. 8 and 13, and a plurality of flexible batteries 140 arranged along the longitudinal direction of the fuselage 310. ) May be electrically connected to each other.
  • the flexible battery 140 may be arranged to be electrically connected to each other along an axial direction parallel to the longitudinal direction of the fuselage 310, and each of the flexible batteries 140 may include the fuselage ( It may be disposed in the form of winding one or more times around the axial direction of 310.
  • the plurality of flexible batteries 140 constituting the power supply unit S are arranged along the longitudinal direction of the fuselage 310 to distribute the total weight of the battery. Can be.
  • the weight of the battery may be distributed over the entire length of the fuselage 310 without being concentrated in a local position, compared to a conventional unmanned flying device in which a solid solid battery is built in the fuselage.
  • the overall weight of the battery constituting the power supply (S) is distributed along the longitudinal direction of the fuselage 310, the overall control such as attitude control or direction control of the unmanned flying device (300,400) through the controller 190
  • the control operation can be made quickly and accurately.
  • the weight reduction may be realized by configuring the power supply unit S through the flexible battery 140 that is relatively lighter than the conventional unmanned flying device that uses a solid solid battery.
  • the plurality of flexible batteries 140 embedded in the fuselage 310 may all have the same weight, and may have the same storage capacity.
  • the flexible battery 140 is not limited thereto, and may have different weights or different power storage capacities according to positions of the fuselage 310 to be installed.
  • the power supply S includes a plurality of flexible batteries 140 arranged along the axial direction of the fuselage 310 in parallel with each other via two cables 191a and 191b.
  • a high capacitance storage capacity can be realized. That is, the pair of positive electrode terminals 145b and the negative electrode terminal 145a formed in each of the flexible batteries 140 may connect the positive electrode terminals 145b to the positive electrode terminals 145b, respectively, via the cables 191a and 191b.
  • the terminal 145a may have a form in which the cathode terminals 145b are connected to each other.
  • the plurality of flexible batteries 140 arranged along the longitudinal direction of the fuselage 310 may be connected in parallel to each other to realize high capacity storage capacity as well as overall weight distribution.
  • the two cables 191a and 191b may be electrically connected to one end of a circuit board 192 constituting the controller 190 or a separate circuit board electrically connected to the controller 190.
  • the power supply unit S may have a form in which a plurality of battery connectors B arranged along the axial direction of the fuselage 310 are electrically connected to each other.
  • the battery connector B may have a form in which a plurality of flexible batteries 140 are arranged in the longitudinal direction and connected in parallel to each other via cables 191c and 191d.
  • at least two flexible batteries 140 of the plurality of flexible batteries 140 constituting the battery connector B may be disposed such that a pair of electrode terminals 145a and 145b face each other, thereby providing a plurality of flexible batteries ( The overall length of the cables 191c and 191d for electrically connecting the 140 may be reduced.
  • the arrangement relationship of the plurality of flexible batteries 140 constituting the battery connector B is not limited thereto, and may be appropriately changed according to the formation position and structure of the pair of electrode terminals 145a and 145b. Let's find out.
  • each of the flexible batteries constituting the battery connection (B) may have a relatively short length compared to the total length L1 of the flexible battery of FIG. 9 (see FIGS. 11 and 12).
  • the flexible battery is recharged by an externally supplied power source. If the battery connection (B) consisting of a flexible battery having a relatively short length (L2) can be charged faster than the flexible battery having a relatively long length (L1).
  • the battery connection (B) may be in the form of each other through a separate housing (not shown), a separate reinforcing member (not shown) in a position corresponding to the pair of electrode terminals (145a, 145b) If a plurality of flexible batteries constituting the battery connector B may be arranged in series, the plurality of flexible batteries may be arranged in series.
  • connection method of the flexible battery constituting the power supply unit S is not limited thereto, and a plurality of flexible batteries arranged along the axial direction of the fuselage 310 when a product to be applied requires high power. 140 may be connected in series with each other.
  • the power supply unit (S) it is noted that one flexible battery may be implemented in the form of a spiral wound a plurality of times along the longitudinal direction of the body portion (310).
  • the unmanned flying device 400 when the unmanned flying device according to the present invention is implemented as a fixed wing type unmanned flying device, the unmanned flying device 400 includes a charging means for recharging the power supply (S) as shown in FIG. can do.
  • the charging means may be a solar panel 330 for producing power using solar light, the solar panel 330 may be disposed on one surface of the main wing 321.
  • the installation position of the solar cell panel 330 is not limited thereto, and it may be found that the solar cell panel 330 may also be disposed on the fuselage 310.
  • the unmanned flying device 400 generates power through the solar panel 330 and recharges the consumed power of the flexible battery 140 constituting the power supply unit S, thereby reducing power consumption. It can be reused without replacing the battery.
  • the driving time of the unmanned flying device 400 may be further increased by charging the flexible battery 140 by using the power produced by the solar panel 330 during operation.
  • the unmanned aerial vehicle 100, 200, 200 ′, 300, 400 may include at least one camera unit 180 for capturing an image of the ground or the surroundings.
  • various sensors 194 may be included to collect or detect various information about the state of the unmanned aerial vehicle 100, 200, 200 ′, 300 and 400 and the surrounding environment.
  • the sensors 194 may include a gyro sensor, a geomagnetic sensor, a gravity sensor, an altitude sensor, a tilt sensor, a humidity sensor, a wind sensor, an air flow sensor, a temperature sensor, an acoustic sensor, an illumination sensor, and the like.
  • Various sensors can be installed as appropriate.
  • the camera unit 180 and the sensors 194 may be controlled through the controller 190 as shown in FIG. 4.
  • the controller 190 transmits an image captured by the camera unit 180 or communicates for transmitting and receiving data such as flight information of the unmanned aerial vehicle 100, 200, 200 ′, 300, 400 or a control command transmitted from the outside.
  • Module 196 may be included.
  • the unmanned flying device 100, 200, 200 ′, 300, 400 according to the present invention may further include various electronic devices applied to a known unmanned flying device.
  • the flexible battery 140 for configuring the power supply unit (S) described above in the unmanned flying device (100,200,200 ', 300,400) according to the present invention may include an electrode assembly 141 and the exterior material (147, 148)
  • the electrode assembly 141 may be encapsulated in the exterior materials 147 and 148 together with the electrolyte.
  • the flexible battery 140 applied to the present invention may be in the form of a plate having flexibility, but patterns 146 and 149 for contraction and relaxation in the longitudinal direction may be formed.
  • the electrode assembly 141 and the exterior members 147 and 148 may be provided with patterns 146 and 149 for contraction and relaxation in the longitudinal direction, respectively, and are formed on the exterior members 147 and 148.
  • the pattern 149 and the second pattern 146 formed on the electrode assembly 141 may be formed to have the same directivity.
  • the deformation amount of the substrate itself constituting the electrode assembly 141 and the exterior materials 147 and 148 is prevented or minimized, the deformation amount of the substrate itself that may occur in the bent portion may be minimized even when banding is generated or embedded in the bent state. It is possible to prevent the electrode assembly 141 and the exterior members 147 and 148 from being damaged or deteriorated in performance.
  • first pattern 149 and the second pattern 146 may be disposed such that the first pattern 149 and the second pattern 146 coincide with each other as well as the same directionality. This is to allow the same behavior to always occur between the first pattern 149 and the second pattern 146.
  • the flexible battery 140 according to the present invention is disposed such that the first pattern 149 and the second pattern 146 formed on the electrode assembly 141 and the exterior members 147 and 148 respectively correspond to each other. Even if bending or bending in the longitudinal direction occurs, the electrode assembly 141 and the exterior members 147 and 148 may always maintain a uniform interval or contact state with respect to the entire length. As a result, since the electrolyte encapsulated together with the electrode assembly 141 is uniformly distributed over the entire length, performance of the battery may be prevented from being lowered.
  • each of the peaks and valleys of the first pattern 149 and the second pattern 146 may be formed in a direction parallel to the width direction of the exterior members 147 and 148 and the electrode assembly 141.
  • Each of the peaks and valleys may be alternately disposed along the length direction of the exterior members 147 and 148 and the electrode assembly 141.
  • the ridges and valleys constituting the first pattern 149 and the second pattern 146 are located at the same positions as the peaks and valleys between the peaks and the valleys, so that the first pattern 149 and the second pattern ( 146 may coincide with each other.
  • the peaks and valleys of the first pattern 149 and the second pattern 146 in a direction parallel to a straight line parallel to the width direction of the exterior members 147 and 148 and the electrode assembly 141. It may be formed, and the peaks and valleys may be repeatedly arranged along the longitudinal direction.
  • the patterns 146 and 149 may be continuously formed in a direction parallel to the width direction of the electrode assembly 141 and the exterior members 147 and 148 and may be formed discontinuously, and the electrode assembly 141. ) And the exterior materials 147 and 148, or may be partially formed in some of the entire length.
  • the ridges and valleys may be provided to have a cross section including at least one selected from an arc cross section including a semicircle, a polygonal cross section including a triangle or a square, and an arc cross section and a polygonal cross section.
  • the hills and valleys of may be provided to have the same pitch and width, but may be provided to have different pitches and widths.
  • the flexible battery 140 when the flexible battery 140 is embedded in the connection unit 130 as shown in FIGS. 1 to 3, stress is applied by the wind or the speed change during the operation of the unmanned aerial vehicle 100, 200, 200 ′ and thus the connection unit 130. ) May cause vibration or minute bending. Accordingly, the flexible battery 140 embedded in the connection unit 130 may also be bent or curved, but the amount of change in length is canceled through the patterns 146 and 149 to prevent the flexible battery 140 from being damaged or deteriorated. Can be.
  • the amount of length change that may occur in the bent portion through the patterns 146 and 149 is offset. By doing so, it is possible to prevent the performance of the flexible battery 140 from being lowered.
  • first pattern 149 and the second pattern 146 may be formed to have the same spacing or spacing between the ridges adjacent to each other, or may have different intervals, the same interval and different The spacing may be provided in a combined form.
  • first pattern 149 formed on the exterior members 147 and 148 may be formed on the entire surface of the exterior members 147 and 148, but may be partially formed.
  • the electrode assembly 141 is encapsulated with an electrolyte in the exterior materials 147 and 148, and includes an anode 142, a cathode 144, and a separator 143 as shown in FIG. 7.
  • the positive electrode 142 may include a positive electrode current collector 142a and a positive electrode active material 142b
  • the negative electrode 144 may include a negative electrode current collector 144a and a negative electrode active material 144b.
  • the current collector 142a and the negative electrode current collector 144a may be implemented in the form of a sheet of a plate having a predetermined area.
  • the positive electrode 142 and the negative electrode 144 may be pressed or deposited or coated on one surface or both surfaces of each of the current collector (142a, 144a).
  • the active materials 142b and 144b may be provided with respect to the entire areas of the current collectors 142a and 144a or partially provided with respect to a partial area.
  • the positive electrode current collector 142a and the negative electrode current collector 144a may be provided with a negative electrode terminal 145a and a positive electrode terminal 145b, respectively, for electrical connection from each body to an external device.
  • the positive electrode terminal 145b and the negative electrode terminal 145a may extend from the positive electrode current collector 142a and the negative electrode current collector 144a to protrude to one side of the exterior materials 147 and 148, and the exterior materials 147, 148 may be exposed on the surface.
  • the positive electrode active material 142b and the negative electrode active material 144b may contain a PTFE (Polytetrafluoroethylene) component. This is to prevent the positive electrode active material 142b and the negative electrode active material 144b from being peeled or cracks from the current collectors 142a and 144a during bending.
  • PTFE Polytetrafluoroethylene
  • the separator 143 disposed between the anode 142 and the cathode 144 may include a nanofiber web layer 143b on one or both surfaces of the nonwoven fabric layer 143a.
  • the nanofiber web layer 143b may be a nanofiber containing at least one selected from polyacrylonitrile nanofibers and polyvinylidene fluoride nanofibers.
  • the nanofiber web layer 143b may be composed of only polyacrylonitrile nanofibers to secure radioactive and uniform pore formation.
  • the exterior members 147 and 148 are formed of a plate-shaped member having a predetermined area, and are intended to protect the electrode assembly 141 from external force by accommodating the electrode assembly 141 and the electrolyte therein.
  • the exterior member (147, 148) is provided with a pair of the first exterior member 147 and the second exterior member 148, the electrolyte and the electrode assembly 141 accommodated therein by being sealed through an adhesive along the rim. To prevent exposure to the outside and leakage to the outside.
  • the exterior members 147 and 148 may be sealed by an adhesive after the first exterior member 147 and the second exterior member 148 are formed of two members, and the edges constituting the sealing part may be all sealed by an adhesive member. The remaining portion that is made and folded in half along the width direction or the longitudinal direction may be sealed through the adhesive.
  • the unmanned flying device (100,200,200 ', 300,400) according to the present invention described above can be used for purposes such as military, commercial, research, etc., it can also be used for leisure that the operation is controlled through the user's remote controller operation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Transportation (AREA)
  • Power Engineering (AREA)
  • Remote Sensing (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)
  • Toys (AREA)

Abstract

La présente invention se rapporte à un drone. Le drone selon un mode de réalisation de la présente invention comprend : une partie corps ; une pluralité d'unités de production d'énergie raccordées à la partie corps de manière à produire de l'énergie permettant le vol de la partie corps ; une pluralité de parties de raccordement pour raccorder la partie corps et les unités de production d'énergie ; et une pluralité de batteries souples, qui sont respectivement intégrée dans la pluralité de parties de raccordement et fournissent de l'énergie aux unités de production d'énergie.
PCT/KR2017/000917 2016-01-26 2017-01-25 Drone WO2017131451A1 (fr)

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KR20160009626 2016-01-26

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US11171324B2 (en) 2016-03-15 2021-11-09 Honda Motor Co., Ltd. System and method of producing a composite product
US11201318B2 (en) 2017-09-15 2021-12-14 Honda Motor Co., Ltd. Method for battery tab attachment to a self-standing electrode
US11325833B2 (en) 2019-03-04 2022-05-10 Honda Motor Co., Ltd. Composite yarn and method of making a carbon nanotube composite yarn
US11352258B2 (en) 2019-03-04 2022-06-07 Honda Motor Co., Ltd. Multifunctional conductive wire and method of making
US11374214B2 (en) 2017-07-31 2022-06-28 Honda Motor Co., Ltd. Self standing electrodes and methods for making thereof
US11383213B2 (en) 2016-03-15 2022-07-12 Honda Motor Co., Ltd. System and method of producing a composite product
US11539042B2 (en) 2019-07-19 2022-12-27 Honda Motor Co., Ltd. Flexible packaging with embedded electrode and method of making
US11535517B2 (en) 2019-01-24 2022-12-27 Honda Motor Co., Ltd. Method of making self-standing electrodes supported by carbon nanostructured filaments
US11569490B2 (en) 2017-07-31 2023-01-31 Honda Motor Co., Ltd. Continuous production of binder and collector-less self-standing electrodes for Li-ion batteries by using carbon nanotubes as an additive
US20230303274A1 (en) * 2021-07-13 2023-09-28 Sonin Hybrid, LLC Systems and Methods for Controlling Engine Speed and/or Pitch of Propulsion Members for Aerial Vehicles

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US11735705B2 (en) 2017-05-24 2023-08-22 Honda Motor Co., Ltd. Production of carbon nanotube modified battery electrode powders via single step dispersion
US11374214B2 (en) 2017-07-31 2022-06-28 Honda Motor Co., Ltd. Self standing electrodes and methods for making thereof
US11569490B2 (en) 2017-07-31 2023-01-31 Honda Motor Co., Ltd. Continuous production of binder and collector-less self-standing electrodes for Li-ion batteries by using carbon nanotubes as an additive
US11201318B2 (en) 2017-09-15 2021-12-14 Honda Motor Co., Ltd. Method for battery tab attachment to a self-standing electrode
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US11616221B2 (en) 2017-09-15 2023-03-28 Honda Motor Co., Ltd. Method for battery tab attachment to a self-standing electrode
US11121358B2 (en) 2017-09-15 2021-09-14 Honda Motor Co., Ltd. Method for embedding a battery tab attachment in a self-standing electrode without current collector or binder
WO2020051688A1 (fr) * 2018-09-11 2020-03-19 Hanna Mark Holbrook Véhicule aérien de transport sans pilote doté de batteries distribuées et son procédé d'alimentation
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US11535517B2 (en) 2019-01-24 2022-12-27 Honda Motor Co., Ltd. Method of making self-standing electrodes supported by carbon nanostructured filaments
US11352258B2 (en) 2019-03-04 2022-06-07 Honda Motor Co., Ltd. Multifunctional conductive wire and method of making
US11325833B2 (en) 2019-03-04 2022-05-10 Honda Motor Co., Ltd. Composite yarn and method of making a carbon nanotube composite yarn
US11834335B2 (en) 2019-03-04 2023-12-05 Honda Motor Co., Ltd. Article having multifunctional conductive wire
US11539042B2 (en) 2019-07-19 2022-12-27 Honda Motor Co., Ltd. Flexible packaging with embedded electrode and method of making
US20230303274A1 (en) * 2021-07-13 2023-09-28 Sonin Hybrid, LLC Systems and Methods for Controlling Engine Speed and/or Pitch of Propulsion Members for Aerial Vehicles

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