WO2017048016A1 - Wired air vehicle energy supply system - Google Patents

Wired air vehicle energy supply system Download PDF

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Publication number
WO2017048016A1
WO2017048016A1 PCT/KR2016/010263 KR2016010263W WO2017048016A1 WO 2017048016 A1 WO2017048016 A1 WO 2017048016A1 KR 2016010263 W KR2016010263 W KR 2016010263W WO 2017048016 A1 WO2017048016 A1 WO 2017048016A1
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WO
WIPO (PCT)
Prior art keywords
cable
vehicle
supply system
fuel
energy supply
Prior art date
Application number
PCT/KR2016/010263
Other languages
French (fr)
Korean (ko)
Inventor
이승규
Original Assignee
이승규
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 이승규 filed Critical 이승규
Priority to KR1020187010221A priority Critical patent/KR102096039B1/en
Publication of WO2017048016A1 publication Critical patent/WO2017048016A1/en

Links

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
    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B11/00—Communication cables or conductors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H01M8/04201—Reactant storage and supply, e.g. means for feeding, pipes
    • 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
    • B64U2101/20—UAVs specially adapted for particular uses or applications for use as communications relays, e.g. high-altitude platforms
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2250/00—Fuel cells for particular applications; Specific features of fuel cell system
    • H01M2250/20—Fuel cells in motive systems, e.g. vehicle, ship, plane
    • 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
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

Definitions

  • the present invention relates to a wired airplane energy supply system, and more specifically, in supplying energy to a wired airplane, not to supply electric energy through a power line, but to supply fuel cell-based fuel energy to a wired airplane. It's about a wired airplane energy supply system.
  • An unmanned aerial vehicle includes fixed rotors with fixed wings and rotor blades that fly using propeller propulsion.
  • the rotor blades are divided into electric rotors driven by the motor and engine rotors driven by the engine.
  • An unmanned aerial vehicle may also be flying using the buoyancy of a device filled with hydrogen or helium, or may use both the propeller propulsion and the buoyancy of the device.
  • unmanned unmanned aerial vehicles It is powered by an engine / generator or battery mounted inside the aircraft.
  • These unmanned unmanned aerial vehicles have the disadvantage that flight time is limited by the capacity of the fuel or battery mounted inside the vehicle.If the onboard mission equipment requires additional high power consumption, the flight time will be shorter. .
  • Patent Document 1 International Application Publication WO 2013/162128 A1 (Publication date: October 31, 2013) ⁇ ,
  • Patent Document 2 ⁇ Korea Patent Publication KR 10-2015-0066223 A (Published: 2015.06.16.) ⁇
  • Patent Document 3 ⁇ Korea Patent Publication KR 10-1373852 B1 (Registration Date: 2014.03.06.) ⁇
  • Patent Document 4 ⁇ Korean Patent Registration KR 10-1373850 B1 (Registration Date: 2014.03.06.) ⁇
  • Patent Document 5 Korea Patent Publication KR 10-2015-0087491 A (Publication Date: 2015.07.30.) ⁇
  • a system (or device) for powering a vehicle by wire is disclosed.
  • Interference with obstacles occurs, i.e., the obstacles in the horizontal direction due to obstacles on the cable are hindered.
  • low-altitude horizontal flight is essential for real-time detection of disaster targets in real-time and for use in search.
  • Wired aircraft used for surveillance reconnaissance or communication relaying require very high flight altitude to secure a wide field of view.
  • the conventional wired vehicle energy supply method does not satisfy the above requirements.
  • Cables can be damaged by twisting. In order to prevent this problem, the cable is normally detected by twisting the cable.
  • the present invention has been devised to solve the above-mentioned problems.
  • the purpose of the present invention is to supply energy to a vehicle from ground level by wire, even if the flying altitude of the aircraft is increased.
  • the transmission loss is rarely incurred and allows the vehicle to minimize the load on the cable.
  • cable carriers can move horizontally (or even fly) horizontally on cable bases.
  • a wired vehicle energy supply system includes: a vehicle including a fuel cell and a vehicle electric machine; a fuel cell fuel supply device located outside the vehicle; the vehicle and the fuel cell fuel supply device. It includes a transmission cable for connecting, wherein the transmission cable includes a fuel transmission passage for transmitting a fuel cell fuel, the fuel cell receives the fuel cell fuel through the fuel transmission passage to produce electricity after the flight It is characterized by the supply of electrical equipment.
  • the fuel cell fuel may be hydrogen.
  • the transmission cable may be a transmission cable having a multiple transmission path in one tube. have.
  • the fiber optic communication line may pass through the fuel transmission path of the transmission cable.
  • the fiber optic communication line may enclose a fuel transmission tube.
  • the high strength center line may pass through the fuel transmission path of the transmission cable.
  • the flying vehicle may include a battery capable of storing electricity produced by the fuel cell.
  • the transmission cable includes a cable twist prevention device comprising a swivel portion connected to the fuel cell and a rotating portion that is fixed to the fuel cell and that provides a mechanical connection for the fuel cell and the vehicle to rotate independently. Therefore, when the rotation moment causing the twist of the cable is generated, the twist of the cable may be eliminated by the relative rotation of the fuel cell and the aircraft body.
  • the fuel cell fuel supply device may include a hydrogen generator that generates hydrogen.
  • the fuel cell fuel supply device adjusts the tension and length of the cable.
  • It can include a cable control.
  • the transmission cable connected to the vehicle may be connected via a rotary joint.
  • the fuel cell fuel supply device may further include a supply control unit capable of controlling the amount or pressure of hydrogen to be supplied.
  • the maximum output power control of the fuel cell may be performed by adjusting the hydrogen supply amount in the supply control unit.
  • a wired flight energy supply system includes: a flying vehicle for supplying power via a wired wire; a power supply system located outside of the flying vehicle; a power cable connecting the flying vehicle and the power supply system; The vehicle includes a slip ring, and the power cable is connected through the slip ring.
  • a wired vehicle energy supply system includes: a vehicle including an internal combustion engine and a vehicle electric machine; an internal combustion engine fuel supply device located outside of the vehicle; and the vehicle and the internal combustion engine fuel supply vehicle. And a transmission cable for connecting, wherein the cable includes a fuel transmission passage for transmitting the internal combustion engine fuel, wherein the internal combustion engine receives the internal combustion fuel through the fuel transmission passage to generate rotational power of the vehicle. It is characterized by producing electricity by the generated rotational power and supplying it to the flying electric equipment.
  • a mission fluid supply unit for supplying a mission fluid and a fluid transmission cable for transmitting the mission fluid are provided.
  • the wired vehicle energy supply system wherein the flying body includes a plurality of flying objects including a first flying body, and the cable is connected in series to the remaining flying vehicles via the first flying body, and the plurality of flying bodies. Is supplied with energy from the cable, and the cable connecting the plurality of vehicles may be fixed in length.
  • a tension sensor for detecting the tension of the cable may be installed in the flying vehicle.
  • the cable may include a communication line capable of transmitting a communication signal.
  • a cable control unit for adjusting the tension and length of the cable may be included.
  • the cable control unit includes: a drum for winding and unwinding the cable; a sorter rotating 360 degrees about a central axis of the drum; a motor driving unit driving the sorter; a moving guide providing a movement path of the cable; The sorter may be rotated to wind or unwind a cable to the drum.
  • the cable control unit includes a drum for winding and unwinding the cable; a motor driving unit for driving the drum; a moving guide for providing a movement path of the cable; and the drum rotates to connect a cable to the drum. It can be wound or unwound.
  • the cable control unit includes: a drum for winding and unwinding the cable; a motor driving unit for driving the drum; a movement guide for providing a movement path of the cable; It may include a aligner rotates 360 degrees to the axis of rotation of the drum; a position sensor for detecting the position of the drum process locator;
  • a drum is controlled by the motor driver so that the alignment position error between the alignment unit and the drum is zero. It may be possible.
  • the drum is stably stably stably stably
  • It may further include an auxiliary guide that provides a linear movement of the cable in the direction of the axis of rotation of the drum so that the unwinding and winding are carried out uniformly.
  • the cable control unit may be a hydrogen storage unit inside the drum rotation center.
  • the drum of the cable control unit may be formed in one body with the hydrogen storage unit to rotate the rotation axis of the drum.
  • the cable router and the cable router are connected to each other via a cable router located at a predetermined height. It may also include more via the cable installed.
  • the cable may further include a cable duct and a cable duct supporter for supporting the cable duct via a cable duct located at a predetermined height.
  • the cable router is located on the rotation axis of the drum or the alignment unit of the cable control unit.
  • the cable router is located on the axis of rotation of the drum
  • the cable carrier support may be configured to be at a predetermined height.
  • the cable carrier support part is provided in the drum rotation center of the rotary cable control unit.
  • the cable transit supporter is fixed to the outside of the cylinder formed when the sorter rotates; the through hole from the core end to the cable transiter installed at a predetermined height on the sorter rotation axis. It can be a pipe shape with:
  • the cable router provides a contact surface in the tangential direction of the cable movement path.
  • the rotating body may include a rotating part capable of rotating the direction of the vertical authentication force on the rotating shaft of the rotating body to the rotating shaft.
  • the cable router and the cable router support may be provided in the cable control unit.
  • It may be located at multiple points apart to provide a bypass and long horizontal distance of the obstacle.
  • the cable route installed at the point where it is spaced apart from the cable control part may be an open top of one side so as not to bind the cable.
  • the cable router installed at a point spaced apart from the cable control unit includes a lower rotating body and a left rotating body which provide a contact surface in the tangential direction of the moving path to minimize the moving friction of the cable.
  • the lower rotor Located at the left and right of the cable, the lower rotor is located at the bottom of the cable, the lower rotor and the left and right rotors may be rotated in a direction perpendicular to each other.
  • the cable router descends the cable of the vehicle so that the cable router
  • It may further include a cable guide for easy contact with the rotating body.
  • the airplane energy supply system according to the present invention is wired from the ground.
  • FIG. 1 is a configuration diagram of an embodiment of a flying body energy supply system according to the present invention.
  • FIG. 2 is a configuration diagram of a fuel cell.
  • FIG. 4 illustrates an embodiment of a rotating body displacement detection method and a tension sensor.
  • FIG. 5 is a perspective view of an embodiment of a fuel cell fuel supply device including a cable control unit and a hydrogen storage unit.
  • Embodiment 6 is a sectional view of Embodiment 1 of a transmission cable
  • FIG. 7 is a cross-sectional view and perspective view of a second embodiment of a transmission cable
  • Embodiment 8 is a sectional view of Embodiment 3 of a transmission cable
  • FIG. 9 is a perspective view of an embodiment of an end processing unit of a transmission cable
  • 10 is an example of a cable connection diagram including a plurality of fluid transmission cables
  • Figure 11 shows the interference between the ground obstacle and the cable
  • FIG. 12 is a conceptual diagram of an embodiment of a support cable via a system
  • FIG. 13 illustrates an embodiment of a rotary cable control unit including a cable passer.
  • FIG. 14 shows an embodiment of a fixed cable control unit including a cable passer
  • FIG. 15 is a perspective view of one embodiment of FIG. 14 (a)
  • 16 is a conceptual diagram of an embodiment of the intermediate support cable via a system
  • FIG. 17 illustrates an embodiment of a cable router of an intermediate support
  • FIG. 18 is a conceptual diagram of an embodiment of a cable routing method by a flying vehicle
  • 19 illustrates an embodiment of a cable router using a route vehicle route.
  • 20 is a block diagram of a daisy chain type cable connection
  • 21 is a spring tension sensor embodiment
  • Figure 22 is a daisy chain connection diagram for securing the diagonal field of view
  • FIG. 23 shows an embodiment of a slip ring unit.
  • Example 24 is a configuration diagram with Example 1 of the cable twist prevention
  • 26 is a configuration diagram of a cable twist prevention Example 3
  • the power supply system or power source mounted on the wired flying vehicle referred to in the present invention is based on fuel energy or electric energy supplied from the outside of the aircraft, and the energy supply system of the present invention provides both a power supply method and a fuel supply method. Include.
  • the term "cables" of wired aircraft referred to in the present invention is the energy supply.
  • a cable and a fluid transmission cable the energy supply cable is divided into a fuel transmission cable and a power supply cable.
  • the fuel supply energy supply system uses fuel cells to generate power for wired aircraft.
  • Fuel cells can be fueled by a variety of fuels, including natural gas, methanol and gasoline, which can be reformed into hydrogen using a fuel reformer or pure hydrogen.
  • Fuel cells electrochemically react fuel and oxidants to produce electrical energy.
  • This chemical reaction is generated by the catalyst in the catalyst bed and generally generates electricity as long as the fuel is continuously supplied.
  • oxygen can be used as an oxidizing agent.
  • hydrocarbons and alcohols can be used as fuel, and air, chlorine and chlorine dioxide can be used as oxidizing agents.
  • the main body of the fuel cell is introduced hydrogen, oxygen in the air, direct current electricity, water and
  • Fuel cells may include a fuel reformer, which is a fuel reformer.
  • the incoming fuel is fuel other than hydrogen (eg methanol, methane, LPG, LNG, gasoline)
  • hydrogen can be derived from the fuel.
  • the conventional wired power supply method increases the power lost in proportion to the flight distance due to the resistance of the cable supplying the power.
  • the fuel cell fuel supply method leaks from the transmission cable that transmits the fuel cell fuel. If not, no energy is lost.
  • the conventional wired power supply method uses a metal with a high density of cables.
  • Fuel-fueled cables can be made up of lightweight lubrication (hoses) that do not contain metal conductors and can carry fluid to reduce the weight of the fuel transmission cable .
  • hoses lightweight lubrication
  • the present invention also allows the use of internal combustion engines (hydrogen engines, gasoline engines, diesel engines, LNG engines, etc.) and generators without using fuel cells to supply power and power to the aircraft.
  • internal combustion engines hydrogen engines, gasoline engines, diesel engines, LNG engines, etc.
  • the representative hydrogen engine of the internal combustion engine refers to an engine that uses hydrogen as a fuel, and supplies hydrogen to the intake pipe according to the fuel supply method, and supplies hydrogen to the combustion chamber in a form compatible with air and hydrogen directly to the combustion chamber. Can be distinguished by the way.
  • the generator can use that power to produce electricity and then supply electricity to the aircraft.
  • FIG. 1 is a view of an embodiment of a wired vehicle energy supply system according to the present invention.
  • the wired airplane energy supply system according to the present invention may be referred to as a wired airplane energy supply device.
  • the flying vehicle energy supply system of FIG. 1 includes a flying vehicle 100 and fuel cell fuel supply.
  • Apparatus 200 transmission cable 300 for connecting the vehicle 100 and the fuel cell fuel supply device 200.
  • the fuel cell fuel supply device 200 may be located on the ground or underground, or may be located on a ground building, but the fuel cell fuel supply device 200 according to the present invention may be located outside the vehicle 100. Located.
  • the flying body 100 includes a fuel cell 110, a battery 120, and a flying electric device 130.
  • the fuel cell 110 is a transmission providing a transfer path of fuel energy.
  • a fuel cell fuel (eg, hydrogen) may be transmitted or received from the transmission cable 300 in connection with the cable 300.
  • the fuel cell fuel is hydrogen
  • the fuel cell 110 is delivered with hydrogen and atmospheric charge.
  • Oxygen can be used to produce electricity.
  • the aircraft electrical equipment 130 means a device that requires electricity for operation, and all devices that require electricity while in the aircraft are flying vehicles.
  • the electric device 130 An example of the flying electric device 130 is
  • flight control system There are flight control system, driving motor, communication equipment and mission equipment.
  • the electricity produced by the fuel cell 110 may be transmitted directly to the flying electric machine 130. However, it may also be transmitted to the flying electrical device 130 after being stored in the battery 120.
  • the battery 120 is an auxiliary power supply that provides a DC buffering function. When the battery 120 does not produce electricity, the battery 120 may also perform an emergency power supply function.
  • a power converter 140 may be further included between the fuel cell 110 and the battery 120 to control the output of the fuel cell 110 to the required output (or voltage).
  • the fuel cell fuel supply device 200 includes a hydrogen generation unit 210, a hydrogen storage unit 220, a supply control unit 230, and a cable control unit 240.
  • the hydrogen generating unit 210 and the cable control unit 240 may be omitted, the function of the supply control unit 230 may be included in the hydrogen storage unit 220.
  • the hydrogen generator 210 is a device for generating hydrogen.
  • Methods include electrolysis of water and generation of hydrogen using a fuel reformer from natural gas, methanol, and the like.
  • Hydrogen generated from the hydrogen generator 210 may be stored in the hydrogen storage 220 and used when needed.
  • the hydrogen generator 210 is included, but is produced elsewhere. Since hydrogen may be used in a storage container or the like, the hydrogen generator 210 may be excluded from the configuration of the present invention.
  • Hydrogen storage methods include liquid storage, gas storage, and
  • the supply control unit 230 controls the maximum amount of hydrogen supply so that the maximum output power ( The maximum amount of power output from the fuel cell can be counted.
  • the hydrogen gas supplied to the fuel cell stack 111 of the fuel cell 110 is controlled (adjusted) through a fuel cell controller 112 including a control valve in a flying vehicle. Supplied to the aircraft's electrical equipment 130
  • the output power of the fuel cell 110 can be controlled.
  • the cable control unit 240 is basically a device for adjusting the tension and length of the cable.
  • One end of the transmission cable 300 is connected to the cable control unit 240 and the other side
  • the tip is connected to the fuel cell 110 of the flying vehicle. When the flying vehicle rotates or rotates, twisting of the transmission cable occurs.
  • the flight energy supply system of FIG. 1 has a cable twist prevention function to prevent the cable twisting when the aircraft rotates and turns.
  • the cable control part is divided into a rotary type and a fixed type according to whether the drum (reel or spool) is wound around the cable.
  • the rotary type is a widely used method where the drum (reel) rotates.
  • the cable is wound or unwound and the fixed type is a cable wound or unwound on a fixed drum (reel).
  • 3 is an embodiment of a cable control unit.
  • the cable adjusting unit 240 includes a motor driving unit 241 and a drum 242.
  • the drum 242 has a structure that rotates by the motor driving unit 241, it is a commonly used rotary type, while the drum 242 is fixed, and the fixed drum 242 To provide the ability to wind or unwind cable 300
  • the cable 300 is connected to the cable 300 according to the direction of rotation of the aligner.
  • the fixed cable control unit 240 does not rotate the drum, so the connection with the energy supply cable 300 for supplying energy (fuel, electricity) has the advantage of being able to connect directly without using rotary joints or slip rings.
  • the guide 244 is composed of a rotating body (for example, a roller) that tangentially moves the path of the cable 300.
  • the moving guide 244 is composed of a plurality of rotating bodies (for example, rollers) in multiple stages, the direction and the moving path of the cable 300 can be changed as desired.
  • the auxiliary guide 255 is stably connected to the drum 242 in a stable manner.
  • the auxiliary guide 255 linearly moves in the direction of the rotation axis of the drum in association with the rotation angle of the drum.
  • the rotation axis direction of the wood drum is vertical when the cable control unit 240 is rotated.
  • the sorter 243 may be fixed, and the drum ( It is possible to rotate freely with the rotation axis of 242 as the center.
  • the drum 242 is rotated by the motor driving unit 241, the sorter 243 is
  • the sorter 243 and the drum 242 may have a structure that rotates independently of each other.
  • the rotation angle position control can be performed by shifting the motor drive part 241 load rum 242 so that the position error becomes "zero".
  • the drum 242 is placed in the alignment position of the sorter 243.
  • the cable control unit 240 may be implemented in other ways, and may be omitted from time to time. However, when the cable control unit 240 is omitted, a separate method of managing the cable is required.
  • the cable control unit 240 of the present invention can adjust the tension of the cable through the winding and unwinding of the cable, including the cable tension sensor in the cable movement path.
  • FIG. 4 is an embodiment of a tension sensor for detecting a tension due to a displacement of a rotating body.
  • the path of travel includes a rotor (AA) that can move freely according to the tension of the cable
  • the displacement of the rotor (AA) is proportional to the tension of the cable (300), and the movement displacement is measured to measure the cable (300).
  • the design power is sensed.
  • the tension sensor of the rotor displacement detection method of FIG. 4 which is generally used to control the tension of the cable in the cable control part of the present invention, is omitted in the remaining drawings of the present invention.
  • FIG. 5 is a perspective view of an embodiment of a fuel cell fuel supply device including a cable control unit and a hydrogen storage unit.
  • the drum 242 of the rotary cable control unit 240 rotates so that the connection between the transmission cable 300a wound on the drum and the hydrogen storage unit 220 or the hydrogen generator 210 is independently separated. Is generally between the rotor and the government
  • Connections can be made via rotary joints that provide the ability to transfer fluid (liquid, air, gas, etc.) media.
  • FIG. 5A is a perspective view of an embodiment in which the hydrogen storage unit 220 and the cable control unit 240 are integrally connected without using the rotary joint.
  • the hydrogen storage unit 220 and the drum 242 in Figure 5 (a) is a body (same frame)
  • the hydrogen storage unit 220 which includes the drum 242 and the supply control unit 230, is rotated by one body by the motor driving unit 241.
  • FIG. 5 (b) is a perspective view of another embodiment of a fuel cell fuel supply device.
  • FIG. 5 (a) the hydrogen storage unit 220 is located outside the drum 242, while FIG.
  • a cylindrical hydrogen storage unit 220 is placed inside the center of rotation of the drum 242 to increase space utilization.
  • sorter tracking control can be performed.
  • the hydrogen storage unit 220 and the drum 242 are fixed without rotation, and the winding and unwinding of the cable 300a is performed on the drum 242 by the rotation of the sorter 243 by the motor driving unit 241.
  • the fixed cable control unit provides an advantage of connecting the transmission cable 300a directly to the hydrogen storage unit (or the hydrogen generation unit) without using a rotary joint.
  • the fuel cell fuel supply device when the fuel cell fuel supply device is mounted in a vehicle, the fuel cell fuel supply device is preferably mounted in a hydrogen fuel cell vehicle equipped with a hydrogen storage unit.
  • the transmission cable 300a connects a fuel transmission path for transmitting fuel cell fuel.
  • Embodiment 6 is a sectional view of Embodiment 1 of a transmission cable.
  • a fuel transmission passage 310 is basically formed for the transfer of fuel of the fuel cell, and the fuel transmission passage 310 is surrounded by the endothelium 320.
  • 340 is preferably a material having excellent tensile strength and strength (eg, aramid fiber, high strength polyethylene fiber, etc.).
  • a protective material 330 having excellent flexibility and elasticity is laminated between the outer skin 340 and the inner skin 320.
  • the transmission cable 300a is light and excellent in durability.
  • the transmission cable 300a can be implemented as a single material rib (eg, a silicone tube) without the distinction between the inner shell 320, the outer shell 340, and the protective material 330.
  • a single material rib eg, a silicone tube
  • Embodiment 7 is a sectional view and perspective view of Embodiment 2 of a transmission cable.
  • the outer skin 340 of FIG. 6 does not provide an external tensile force, but provides an external tensile force other than the high-strength center line 370 installed therein.
  • the high-strength center line 370 is a line-shaped object that can withstand strong forces and is transmitted.
  • the fuel transfer tube 360 of FIG. 7 may use a general purpose fuel transfer tube in which tensile strength and strength are relatively weak.
  • a material having excellent tensile strength and strength eg, aramid fiber, high strength.
  • the transmission cable of Figure 7 can effectively maintain a high tensile strength and strength.
  • the tube 360 may include a communication line 350 for wired communication with the aircraft 100.
  • the communication line 350 may be a copper line capable of conducting electricity, but may also be an optical fiber communication line that is light in weight and has a large amount of data transmission.
  • Embodiment 8 is a sectional view of Embodiment 3 of a transmission cable.
  • the fluids including the fuel may be transferred independently.
  • the transmission cable 300a of FIG. 8 has a multiple transmission tube structure capable of transmitting a large number of fluids to a single valve 360, so that the weight of the transmission cable 300a is increased rather than transferring the fluid to individual tubes. It offers the advantage of greatly reducing.
  • the optical fiber 350a communication line when configured to penetrate the fuel transmission passage 310, the optical fiber 350a provides the following advantages.
  • the fuel transmission cable 300a and the optical fiber 350a communication line can be integrated into a single-stranded cable.
  • the protective sheath (or sheath) of the optical fiber or optical fiber communication line was transferred to the tube 360.
  • the fiber does not interact with the fuel of the fuel transmission cable because it operates with an optical signal rather than an electrical signal.
  • the fuel transmission is performed by the optical fiber 350a communication line in the space of the fuel transmission passage 310.
  • FIG. 9 shows a perspective view of an embodiment of the end processing unit of the transmission cable 300a.
  • the optical fiber 350a communication line is also branched into the fuel transmission path 310 and the optical fiber 350a communication line as shown in Fig. 9 at the start and end portions of the tube 360.
  • FIG. 10 is an example of a cable connection diagram including a plurality of fluid transmission cables.
  • the cable 300 of the flying vehicle 100 is connected to the energy supply unit 2000.
  • the mission fluid supply 2000a provides a variety of fluids (eg pesticides, fertilizer studs) for the mission required by the aircraft 100. It may further comprise a fluid transfer cable (3000a).
  • the energy supply cable 3000 and the fluid transmission cable 3000a are cables
  • the wired aircraft energy supply system of the present invention thus provides not only the supply of energy (fuel, electricity) to the aircraft, but also provides a fluid transmission cable to provide a variety of fluids (e.g. pesticides, fertilizers, etc.) for the required mission.
  • a fluid transmission cable to provide a variety of fluids (e.g. pesticides, fertilizers, etc.) for the required mission.
  • fluids e.g. pesticides, fertilizers, etc.
  • FIG. 11 shows how the obstacle 2 and the cable 300 of the ground 1 are interfered with.
  • the obstacles (2) can be hindered by the movement.
  • FIG. 12 is a conceptual diagram of an embodiment of a support cable route method.
  • FIG. 12 (b) is a conceptual diagram of a state in which the cable 300 is lifted by the support 5000 so that there is no interference of the ground object 2.
  • a cable installed at an upper portion of the support 5000 provides a predetermined height of the cable 300 of the cable control unit 240.
  • the cable 300 is displaced when the vehicle moves horizontally.
  • the maximum height of the ground object 2 that can avoid interference is determined.
  • the position and structure of the cable control unit 240 is different.
  • FIG. 13 is a view of a rotary cable control unit 240 including a cable passer
  • FIG. 13 (a) is a front view of one embodiment
  • FIG. 13 (b) is a perspective view of FIG. 13 (a).
  • FIG. 13 (c) shows a perspective view of an embodiment with a gasoline.
  • the cable 300 of the cable control unit 240 is a cable
  • the cable transit 500 is a cable according to the movement of the cable and the position of the flying vehicle.
  • the cable route 500 includes a rotor body 520 and a rotor body that provide a contact surface in the tangential direction of the cable 300 movement path so that movement friction is minimized for various movement directions of the cable.
  • a rotating part 530 (bearing) having a rotating shaft perpendicular to the rotating shaft of 520.
  • the rotating body 520 is supported by the rotating body support 510, and the rotating body support 510 is
  • the cable passer 500 is connected to the cable at the time of movement and change of direction. Minimize the friction at work.
  • the cable carrier support 5000 may, of course, be composed of a multi-stage connection structure of various shapes to adjust the height.
  • FIG. 14 is an embodiment of a fixed cable adjuster including a cable passer.
  • FIG. 14 (a) is a front view of one embodiment of a fixed cable control unit
  • FIG. 14 (b) is a perspective view of one embodiment of a cable transiter
  • FIG. 14 (c) is a perspective view of one embodiment of a support movement guide. .
  • Winding and unwinding operations are performed on the drum 242 of the cable 300.
  • a cone space having a height of the cable adjusting section 240 as a square section, and a conical space having a triangular cross section of the inclined cable 300 between the fixed cable adjusting section 240 and the support movement guide 544 are formed.
  • the support (5000) is characterized in that it is fixed in a location where the space occupied by the cone and the cone so as not to interfere with the fixed cable control unit 240 is generated.
  • the cable router 500 is positioned at an upper side of the cable router support 5000 on the rotation axis of the alignmentr 243, and is connected to the vehicle.
  • the cable 300 is connected to the cable adjusting unit 240 via the cable passer 500.
  • the cable is twisted by the rotation of the sorter 243 by a predetermined distance between the moving guides 544 of the support on the rotation axis of the cable adjusting unit 240. It is desirable that the cable be unwound and wound smoothly on the drum 242 without being generated.
  • the cable router 500 has the cable router as shown in FIG. 14 (b) such that the friction of the cable is minimized with respect to the direction of connection of the cable according to the movement of the cable 300 and the position of the vehicle.
  • 500 comprises a rotating body 520 which provides a contact surface in a tangential direction to the movement path of the cable 300 and a rotating part 530 having a rotating shaft perpendicular to the rotating shaft of the rotating body 520.
  • the rotating part 530 Is preferably a bearing.
  • the rotating body 520 is supported by the rotating body support 510, the rotating body support 510 is fixed to the outer ring of the rotating part 530, the inner ring of the rotating part 530 is a cable carrier support (5000).
  • the support 5000 has a hollow pipe shape through which the cable 300 is constrained.
  • the cable carrier support (5000) is configured to be detachable in a multi-stage connection structure
  • the cable (300) is connected to the support (5000) in order to facilitate detachment and detachment.
  • a structure that is not bound by the through holes is desirable.
  • the support for moving the support 544 on the aligner axis of rotation (5000) It is attached to the lower end of one side.
  • the support movement guide 544 includes the cable of FIG. 14 (b).
  • the support cable route method shown in FIG. 14 has an advantage that it can be applied to both fixed and rotary cable control.
  • the cable passer of the present invention is illustrated only when the rotating body is attached up and down, but the rotating body may be attached to the left and right according to the direction of the cable moving path and the size of the tension.
  • FIG. 15 is a perspective view of one embodiment of FIG. 14.
  • the diesel engine 500 and the support movement guide 544 are used for moving the cable and
  • the support cable route method of the present invention is composed of one support in the example of FIG. 12, and when the horizontal travel distance is increased, the cable sags and the load of the cable applied to the vehicle increases.
  • FIG. 16 is a conceptual diagram of one embodiment of the intermediate support cable route method.
  • 16 (a) shows a method of via a support cable including an intermediate support (5000a).
  • FIG. 16 (b) is a conceptual diagram which provides the right path of the cable 300 so that it may not interfere with the ground material 2 by the intermediate support 5000a.
  • an incremental support 5000a including a cable transiter 500 is provided.
  • the cable 300 is routed through the K-free tanker 500a of the incremental support 5000a, thereby reducing the cable sagging and increasing the maximum horizontal travel distance without interference with the ground obstacle 2.
  • the intermediate support (5000a) can be fixed on the ground, It can be installed on moving bodies (eg vehicles) and a multi-stage connection structure is preferred to allow height adjustment. '
  • the intermediate support 5000a is configured as one, but may be configured in plural according to the required operating conditions (eg obstacle position, horizontal child distance).
  • the cable route can be provided for horizontal movement to a position beyond the support (5000a).
  • the flying vehicle freely passes through the cable carrier 500a of the intermediate support for vertical and horizontal movement in an area not exceeding the intermediate support.
  • the structure of the cable route 500a is configured to be routed or routed through the cable depending on the position of the vehicle.
  • the cable router 500a of the middle magnetic field zone does not bind the cable and provides the cable route.
  • the vertical height support provides long horizontal travel distances and bypass paths at low altitudes without obstacles and interference.
  • intermediate supports 5000a may be provided with a separate structure, but the existing structures (for example, street lamps, power poles, high-rise buildings, etc.) may be used as intermediate supports. have.
  • FIG 17 shows an embodiment of a cable router of an intermediate support.
  • FIG. 17 (a) is a front view of the cable router embodiment of the intermediate support
  • FIG. 17 (b) is a front view of the cable router embodiment of the intermediate support
  • the cable supporter 500a of the intermediate support basically has a lower rotating body 520_1 and a left and right rotating body 52 that minimize the moving friction of the cable 300. 2) is configured to be vertical, and the cable route 500a is connected to the intermediate support 5000a through the support connecting portion 531.
  • the one side may be selectively configured to be controlled in an open structure and a closed structure.
  • the cable guide 51 1 allows the cable to easily contact the rotors 520_1 and 520_2 even if the vehicle drops the cable within a width (width) of the cable guide 511.
  • the vertical direction of the surface including the left and right rotating bodies 520_2 of the cable transiter 500a lowers the cables so that the contact with the rotating bodies is smooth, as shown in FIG. 16 (a).
  • the cable router 500 and the intermediate supporter cable router 500a are installed in the same straight direction.
  • 18 is a conceptual diagram of an embodiment of a cable via method by a flying body.
  • FIG. 18 (a) is a conceptual diagram of a support cable via a vehicle
  • FIG. 16 (b) shows a cable 300 lifted by a cable carrier 500 of an aircraft, thereby causing interference of the ground object 2. It is a conceptual diagram of a state without.
  • the cable passing path provides a cable routing path at a height provided by the cable passing support, while FIG. 18 provides a route of the cable 300 by the flying body 100b.
  • the cable transit vehicle 100b is provided with a cable transiter 500, so that the cable 300 is moved upward with the vertical flight altitude provided by the vehicle 100b.
  • the cable of the cable adjusting unit passes through flight 2 (100b).
  • the flight 2 (100b) Since it has a structure connected to the vehicle l (100a):
  • the flight 2 (100b) has the advantage of changing the vertical height of the cable 300 via the variable.
  • the flight via method is independent of the cable supply structure, so that flight 2 (100b) provides a cable routing through the cable l of the flight l (100a).
  • the cable transiter of the present invention schedules the cable load when the vehicle moves horizontally.
  • the cable router of the present invention provides the effect of increasing the horizontal travel distance by reducing the cable load on the plane as well as preventing the interference between the ground and the cable during the horizontal movement.
  • FIG. 19 shows an embodiment of a cable router using a vehicle route route.
  • the cable route installed in the rotary cable control unit of FIG. 13 is structurally identical to the cable route applied to the vehicle route route.
  • the cable duct shown in FIG. 19 can be applied to the cable duct shown in FIG. 19
  • the cable router 500 of FIG. 19 (a) includes a ring portion 501 and a connection portion 502 having a simple ring shape, and allows the cable 300 to pass through the ring portion 501.
  • 501 is coupled to the connecting portion 502 and the connecting portion 502 is installed on the lower body of the cable passing vehicle 400.
  • the configuration of the cable route This has the advantage of simplicity, but there is a problem that if the cable 300 is moved, the strong frictional force and tension between the ring part 501 and the cable 300 act to damage the transmission cable 300.
  • the frictional force of the cable 300 can be minimized by including the bearing portion 501 (only a part) to the ring portion 501 through which the cable 300 passes.
  • the rotary part 503 may be further included to minimize the forces acting on each other.
  • the cable passer 500 of FIG. 19 (b) includes a rotor support 510 and two rotors 520.
  • the rotor support 510 is a transmission in which the cable carrier 500 is installed.
  • the vertical direction of the surface of the lower body 100b_l of the cable-flying body 100b is provided in the axial direction so as to be freely rotated.
  • the rotor support 510 is coupled to the two rotors 520, the two
  • Grooves are formed at the edges of the two rotating bodies so that the transmission cable 300 does not come off between the two rotating bodies.
  • FIG. 19 (b) has a rotating body and the rotating body providing a tangential contact surface to the cable movement path so that the frictional force is minimized when the cable 300 passes through the cable router 500. It is characterized by providing a rotation axis perpendicular to the rotation axis of the motor.
  • the cable router depends on the tension applied to the cable and the durability of the cable.
  • 20 shows a method of configuring an easy chain, in which cables are connected in series to a plurality of vehicles.
  • FIG. 20 shows a configuration of a "daisies chain" in which a plurality of flying bodies 100a to 100n are continuously connected in series by a cable 300.
  • FIG. 20 Accordingly, the daisy chain configuration has an advantage of maximizing vertical flight altitude by dividing the weight of the total cable length by a plurality of airplanes.
  • the cable 300 of the vehicle l (100a), which is located at the bottom, is located on the ground.
  • the length and tension are adjusted by the cable adjuster 240.
  • the cable 300 further includes a cable control unit 240 in the airplane l (100a),
  • the length and tension of the cable 300 connected to the aircraft 2 (100b) may be adjusted, but the cable length of the aircraft 2 may be fixed by omitting the cable control unit to minimize the increase in load of the aircraft l (100a).
  • the tension sensor can detect the tension of the cable is installed in the cable path of the cable control unit or in parallel to the cable.
  • the cable 300 connected to the flight body 1 can sense the tension in the cable control unit 240, but the flight body 2 preferably senses the tension by the tension sensor 999 connected in parallel with the cable. .
  • a plurality of flying vehicles comprising a first flying vehicle, the cable being connected in series with the remaining flying vehicles via the first flying vehicle, wherein the plurality of flying vehicles comprises:.
  • the cable is supplied with energy from the cable, and the cable connecting the plurality of airplanes is fixed to be long.
  • the commercial vehicle is provided with a tension sensor that senses the tension of the cable.
  • 21 is an embodiment of a spring tension sensor installed in parallel with a cable.
  • the spring-type tension sensor is a structure that senses the tension by measuring the displacement of the elastic body (999_1) according to the cable tension by connecting the elastic body (for example, a spring) in parallel to the cable (300).
  • the tension value is measured to detect the tension.
  • the length of the cable 300 connected in parallel to the tension sensor is longer than the maximum displacement of the elastic body 999_1 as in FIG. 21 to prevent cable breakage.
  • FIG. 22 is a connection diagram of a daisy chain for securing a field of view of a blind spot.
  • the vehicle l (100a) is positioned higher than the obstacle (2).
  • aircraft 2 (100b) is positioned lower than obstacle (2), vehicle l (00a) can secure a higher field of view, and aircraft 2 (100b) can secure a low field of view obscured by the obstacle (2). have.
  • the wired flight energy supply system which consists of the "Daisy chain" of the present invention, has the structure that maximizes the highest flight altitude, because the total cable weight connected to the flight is distributed to a large number of vehicles. To provide.
  • Cable twist protection which does not cause cross cable twisting, is required even when rotating independently.
  • the system is characterized by providing maximum flight altitude for high-floor flight and maximum horizontal movement without horizontal interference with horizontal obstacles.
  • the cable transit system using cable transiters and the wired chain energy supply system of the daisy chain method provide low altitude horizontal flight (movement) without interference with the cable ground.
  • Wired energy supply systems of the present invention may be applied to shooting, military mine detection, etc.).
  • the wired flight energy supply system of the present invention is further characterized by the provision of a fluid transmission cable for the performance of a variety of low-altitude horizontal flights (eg pesticide spraying, fertilizer supply, etc.).
  • a fluid transmission cable for the performance of a variety of low-altitude horizontal flights (eg pesticide spraying, fertilizer supply, etc.).
  • mission equipment eg, fluid sprayers, cameras, mine detectors, etc.
  • Cables fixed to the aircraft can be twisted, which can damage the cables.
  • the cable 300 may be configured to rotate independently of the vehicle.
  • the rotary connection portion of the fuel cell has a bearing for mechanically connecting the flying vehicle body and the fuel cell such that the fuel cell and the flying vehicle have a mutually independent rotating structure.
  • a slip ring that electrically connects the fuel cell output can prevent cable twisting.
  • the slip ring provides a function of transferring electricity without twisting an electrical cable connected between the rotating part and the fixing part.
  • FIG. 23 shows an embodiment of a slip ring unit.
  • the maximum allowable number of cable strands is determined by the number of slip rings 115_1, so the number of slip rings 115_1 may be configured as many as the required number of cable strands;
  • Embodiment 24 is a configuration diagram of Embodiment 1 for preventing cable twist by allowing the fuel cell and the flying vehicle to have mutually independent rotating structures.
  • the fuel cell 110 connected to the transmission cable 300a is connected to the inner ring 116_2 (inner rotating body) of the rotating unit 116, and the flying vehicle body 100_1 is connected to the rotating unit 1 16 of the rotating unit 116.
  • the outer ring (116_1, the outer rotating body) Connected to the outer ring (116_1, the outer rotating body) to make the structure of the flying vehicle body (10 1) and the fuel cell (10) independently freely, the fuel cell 110 using the slip ring unit 115 And maintain electrical connection of the battery 120.
  • the electrical connection with the battery 120 is maintained without cable twist.
  • the output terminal 111 of the fuel cell is connected to the fixing terminal of the slip ring unit to rotate in one body, and the rotary part of the slip ring unit is rotated.
  • the cable 112 is a structure that is connected to the power converter 140 of the flight electric device 130 is fixed to the flight body (100_1). :
  • the cable twist prevention device is such that the fuel cell 110 and the flying vehicle 100 have a mutually independent rotation structure, the rotary connection portion of the fuel cell mechanically connects the flying body 100 and the fuel cell 110. It consists of a rotating unit 116, and a slip ring unit 115 for electrically connecting the power converter 140 and the fuel cell output, to prevent the cable twist.
  • 25 is a configuration diagram of cable twist prevention Example 2;
  • the transmission cable 300a is connected via a rotary joint 118.
  • a commonly used rotary joint is used between the rotary part and the fixed part.
  • the fuel cell 110 can be configured in a non-rotating structure.
  • rotary joints which use hydrogen gas as a delivery medium, have the disadvantage of ensuring strict confidentiality against hydrogen gas leakage for safety purposes, while slip rings are used as a carrier medium for safety. This has the advantage of being guaranteed.
  • FIG. 26 is a configuration diagram of Embodiment 3 for preventing cable twist using a slip ring.
  • FIG. 1 In the case of supplying power to the wired aircraft 100 through the power cable 300b, FIG.
  • the power cable 300b is directly connected to the slip ring unit 115.

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Abstract

A wired air vehicle energy supply system according to the present invention comprises: an air vehicle comprising a fuel cell and an air vehicle electric device; a fuel cell fuel supply device positioned outside the air vehicle; and a transfer cable connecting the air vehicle and the fuel cell fuel supply device, wherein the transfer cable comprises a fuel transfer passage for transferring fuel cell fuel, and the fuel cell is supplied with fuel cell fuel through the fuel transfer passage, produces electricity, and then supplies the same to the air vehicle electric device.

Description

명세서  Specification
발명의명칭:유선비행체의 에너지공급시스템 기술분야  Title of invention: Technical field of energy supply system of wired aircraft
[1] 본발명은유선비행체에너지공급시스템에관한것으로서，더욱상세하게는 유선비행체에에너지를공급함에 있어서，전력선을통해전기에너지를 공급하는것이아니라연료전지기반의연료에너지를유선비행체에공급하는 유선비행체에너지공급시스템에관한것이다.  [1] The present invention relates to a wired airplane energy supply system, and more specifically, in supplying energy to a wired airplane, not to supply electric energy through a power line, but to supply fuel cell-based fuel energy to a wired airplane. It's about a wired airplane energy supply system.
배경기술  Background
[2] 현재다양한무인비행체가감시정찰또는통신중계,시설감시,수색등의  [2] surveillance and communication relays, facility surveillance, search, etc.
다양한목적으로이용되고있다.무인비행체는날개가고정되어 있는고정익과 프로펠러의추진력를이용하여비행하는회전익을포함하며，회전익은모터에 의해구동되는전동회전익과엔진에의해구동되는엔진회전익으로구분된다. 또한무인비행체는수소나헬륨을채운기구의부력을이용하여비행하는것일 수도있고,프로펠러의추진력과기구의부력모두를이용한것일수도있다.  It is used for a variety of purposes. An unmanned aerial vehicle includes fixed rotors with fixed wings and rotor blades that fly using propeller propulsion. The rotor blades are divided into electric rotors driven by the motor and engine rotors driven by the engine. An unmanned aerial vehicle may also be flying using the buoyancy of a device filled with hydrogen or helium, or may use both the propeller propulsion and the buoyancy of the device.
[3] 무인비행체는다양한임무를수행하기위해충분한전력이필요로하며,  [3] Unmanned aerial vehicles require sufficient power to perform a variety of missions,
비행체내부에탑재된엔진 /발전기또는배터리를이용하여전력을공급받는다. 이러한무선무인비행체의경우비행체내부에탑재된연료또는배터리의 용량에의해비행시간이제한되는단점을갖고있다.만일탑재된임무수행 장비가추가적으로높은전력소모를필요로하는경우비행시간은더욱 짧아지게된다.  It is powered by an engine / generator or battery mounted inside the aircraft. These unmanned unmanned aerial vehicles have the disadvantage that flight time is limited by the capacity of the fuel or battery mounted inside the vehicle.If the onboard mission equipment requires additional high power consumption, the flight time will be shorter. .
[4] 이와같은문제점을해결하기위해，지상에 있는전력공급장치가  [4] To solve these problems, ground power supplies
유선 (Tethered cable)으로비행체에전력을공급하는시스템 (또는장치)가종래에 이용되고있었다.  Systems (or devices) that power vehicles by wired cables have traditionally been used.
[5] 특허문헌 1 {국제출원공개 WO 2013/162128 A1 (공개일: 2013.10.31.)}，  [5] Patent Document 1 {International Application Publication WO 2013/162128 A1 (Publication date: October 31, 2013)} ，
특허문헌 2{한국공개특허 KR 10-2015-0066223 A (공개일: 2015.06.16.)}， 특허문헌 3{한국둥록특허 KR 10-1373852 B1 (등록일: 2014.03.06.)},특허문헌 4{한국등록특허 KR 10-1373850 B1 (등록일: 2014.03.06.)},특허문헌 5Γ한국 공개특허 KR 10-2015-0087491 A (공개일: 2015.07.30.)}에는지상에 있는전력 공급장치가유선으로비행체에전력을공급하는시스템 (또는장치)이개시되어 있다.  Patent Document 2 {Korea Patent Publication KR 10-2015-0066223 A (Published: 2015.06.16.)}, Patent Document 3 {Korea Patent Publication KR 10-1373852 B1 (Registration Date: 2014.03.06.)}, Patent Document 4 {Korean Patent Registration KR 10-1373850 B1 (Registration Date: 2014.03.06.)}, Patent Document 5ΓKorea Patent Publication KR 10-2015-0087491 A (Publication Date: 2015.07.30.)} A system (or device) for powering a vehicle by wire is disclosed.
[6] 하지만，지상으로부터유선으로비행체로전력을공급하는방식은,비행체의 비행고도가높아짐에따라 (또는비행거리가길어짐에따라)，케이블의길이가 길어지면서전력손실이커지고，케이블의무게가증가하면서비행체가 감당해야할하중이증가하게되고，그결과전력공급장치의용량과비행체의 양력및추력이증가해야하는문제점이 있다.  [6] However, the method of supplying power from the ground to the wires by wires increases as the flight height of the aircraft increases (or as the flight distance increases), the power loss increases as the length of the cable increases, and the weight of the cable increases. Increasingly, there is a problem that the vehicle must bear the load, and as a result, the capacity of the power supply and the lift and thrust of the vehicle must increase.
[7] 이러한문제점으로인해,유선전력공급방식의비행체의고도 (또는 비행거리)는실용적인운용조건에서현재수십미터를넘지못하고있다. [7] Due to these problems, the altitude (or The flight distance is currently not exceeding tens of meters under practical operating conditions.
[8] 또한유선비행체들은지상의케이블이공급되는지점으로부터수평으로  [8] Wired aircraft also moved horizontally from the point where ground cables were fed.
이동할경우，케이블의경사각과케이블의처짐현상으로인해지상의  When moving, ground due to the inclination of the cable and the deflection of the cable
장애물과의간섭이일어난다.즉케이블이지상의장애물에걸려서수평방향 이동이방해받는문제점이있다.  Interference with obstacles occurs, i.e., the obstacles in the horizontal direction due to obstacles on the cable are hindered.
[9] 특히，재난현장사각지대상황을실시간으로파악하고，수색용으로사용시에는 저고도수평비행이필수적이고,감시정찰또는통신중계용으로활용되는유선 비행체는넓은시야확보를위해매우높은비행고도가요구되지만종래의유선 비행체에너지공급방식으로는상기요구조건을층족하지못하는문제점이 있다. [9] In particular, low-altitude horizontal flight is essential for real-time detection of disaster targets in real-time and for use in search. Wired aircraft used for surveillance reconnaissance or communication relaying require very high flight altitude to secure a wide field of view. However, the conventional wired vehicle energy supply method does not satisfy the above requirements.
[10] 또한비행체가회전및선회비행으로자세가변경되면비행체에고정되어  [10] Also, when the aircraft changes its position due to rotation and turning, it is fixed to the aircraft.
있는케이블은꼬임현상에의해케이블이손상을받올수있다ᅳ이러한 문제점을방지하기위해，종래에는케이블꼬임을감지하여꼬임의  Cables can be damaged by twisting. In order to prevent this problem, the cable is normally detected by twisting the cable.
반대방향으로비행체를회전시키는방식으로해결했으나，이러한방식은 구조적으로비행체가자유롭게회전및선회비행의자세변경이요구되는 임무수행을할수없는문제점이 있다.  The solution was to rotate the vehicle in the opposite direction, but this approach is structurally incapable of performing missions that require changing the attitude of the turning and turning flight.
발명의상세한설명  Detailed description of the invention
기술적과제  Technical task
[11] 본발명은상기한문제점을해결하기위해안출된것^로서，본발명의목적은， 지상으로부터유선으로비행체에에너지를공급함에 있어서，비행체의 비행고도가높아지더라도，비행체에공급되는에너지전송손실은거의 발생되지않고，비행체가감당해야할케이블의하중을최소화하도록하는 것이다.  [11] The present invention has been devised to solve the above-mentioned problems. The purpose of the present invention is to supply energy to a vehicle from ground level by wire, even if the flying altitude of the aircraft is increased. The transmission loss is rarely incurred and allows the vehicle to minimize the load on the cable.
[12] 또한유선비행체가수평으로이동 (또는비행)하더라도케이블이지상의  [12] In addition, cable carriers can move horizontally (or even fly) horizontally on cable bases.
장애물에방해받지않는것을목적으로하다.  It is aimed at not being disturbed by obstacles.
[13] 또한유선비행체가회전과선회비행으로자세변경이발생하더라도，케이블의 꼬암을해소하는것을목적으로한다ᅳ ' 과제해결수단 [13] In addition, even if the vehicle is wired attitude change occurs in the rotational and turning flight, and an object thereof is to solve the kkoam cable eu 'problem solving means
[14] 본발명의일실시예에따른유선비행체에너지공급시스템은，연료전지와 비행체전기기기를포함하는비행체;비행체의외부에위치하는연료전지연료 공급장치；상기비행체와상기연료전지연료공급장치를연결하는전송 케이블；을포함하고,상기전송케이블은연료전지연료를전송하는연료전송 통로를포함하고，상기연료전지는상기연료전송통로를통해연료전지연료를 공급받아전기를생산한후상기비행체전기기기에공급하는것을특징으로 한다.  A wired vehicle energy supply system according to an embodiment of the present invention includes: a vehicle including a fuel cell and a vehicle electric machine; a fuel cell fuel supply device located outside the vehicle; the vehicle and the fuel cell fuel supply device. It includes a transmission cable for connecting, wherein the transmission cable includes a fuel transmission passage for transmitting a fuel cell fuel, the fuel cell receives the fuel cell fuel through the fuel transmission passage to produce electricity after the flight It is characterized by the supply of electrical equipment.
[15] 상기연료전지연료는수소일수있다.  The fuel cell fuel may be hydrogen.
[16] 상기전송케이블은 1가닥의튜브에다증전송통로를갖는전송케이블일수 있다. [16] The transmission cable may be a transmission cable having a multiple transmission path in one tube. have.
[17] 상기전송케이블의연료전송통로내부에광섬유통신선이관통하는것일 수도있다.  The fiber optic communication line may pass through the fuel transmission path of the transmission cable.
[18] 상기광섬유통신선은연료전송튜브를외피로할수도있다.  The fiber optic communication line may enclose a fuel transmission tube.
[19] 상기전송케이블의연료전송통로내부를고강도중심선이관통하는것일 수도있다. [19] The high strength center line may pass through the fuel transmission path of the transmission cable.
[20] 상기비행체는상기연료전지에서생산한전기를저장할수있는배터리를 포함할수있다.  The flying vehicle may include a battery capable of storing electricity produced by the fuel cell.
[21] 상기전송케이블은상기연료전지에연결되어고정되고,상기연료전지와 상기비행체가독립적으로회전할수있도록기계적연결을제공하는회전부와 연료전지에연결된슬립링으로구성되는케이블꼬임방지장치를포함하여， 상가케이블의꼬임을유발시키는회전모멘트가발생되면상기연료전지와 비행체몸체간의상대회전운동으로상기케이블의꼬임이해소되는것일수도 있다.  [21] The transmission cable includes a cable twist prevention device comprising a swivel portion connected to the fuel cell and a rotating portion that is fixed to the fuel cell and that provides a mechanical connection for the fuel cell and the vehicle to rotate independently. Therefore, when the rotation moment causing the twist of the cable is generated, the twist of the cable may be eliminated by the relative rotation of the fuel cell and the aircraft body.
[22] 상기연료전지연료공급장치는수소를발생시키는수소발생부를포함할수 있다.  The fuel cell fuel supply device may include a hydrogen generator that generates hydrogen.
[23] 상기연료전지연료공급장치는상기케이블의장력및길이를조절하는  The fuel cell fuel supply device adjusts the tension and length of the cable.
케이블조절부를포함할수있다.  It can include a cable control.
[24] 상기비행체에연결되는전송케이블은로터리조인트를통하여연결되는것일 수있다. The transmission cable connected to the vehicle may be connected via a rotary joint.
[25] 상기연료전지연료공급장치는공급하는수소의양또는압력을제어할수 있는공급제어부를더포함할수있다.  The fuel cell fuel supply device may further include a supply control unit capable of controlling the amount or pressure of hydrogen to be supplied.
[26] 상기연료전지의최대출력전력제어는상기공급제어부에서수소공급량을 조절함으로써수행되는것일수있다.  The maximum output power control of the fuel cell may be performed by adjusting the hydrogen supply amount in the supply control unit.
[27] 본발명의다른실시예에따른유선비행체에너지공급시스템은,유선으로 전력을공급하는비행체;비행체의외부에위치하는전력공급시스템;상기 비행체와상기전력공급시스템를연결하는전력케이블;을포함하고,상기 비행체는슬립링을포함하고，상기전력케이블은상기슬립링을통하여 연결되는것을특징으로한다.  According to another embodiment of the present invention, a wired flight energy supply system includes: a flying vehicle for supplying power via a wired wire; a power supply system located outside of the flying vehicle; a power cable connecting the flying vehicle and the power supply system; The vehicle includes a slip ring, and the power cable is connected through the slip ring.
[28] 본발명의다른실시예에따른유선비행체에너지공급시스템은，내연기관와 비행체전기기기를포함하는비행체；비행체의외부에위치하는내연기관연료 공급장치;상기비행체와상기내연기관연료공급장차를연결하는전송 케이블；을포함하고,상기케이블은내연기관연료를전송하는연료전송통로를 포함하고，상기내연기관은상기연료전송통로를통해내연기관연료를 공급받아비행체의회전동력을발생시키고，상기발생된회전동력에의해 전기를생산한후상기비행체전기기기에공급하는것을특징으로한다.  According to another embodiment of the present invention, a wired vehicle energy supply system includes: a vehicle including an internal combustion engine and a vehicle electric machine; an internal combustion engine fuel supply device located outside of the vehicle; and the vehicle and the internal combustion engine fuel supply vehicle. And a transmission cable for connecting, wherein the cable includes a fuel transmission passage for transmitting the internal combustion engine fuel, wherein the internal combustion engine receives the internal combustion fuel through the fuel transmission passage to generate rotational power of the vehicle. It is characterized by producing electricity by the generated rotational power and supplying it to the flying electric equipment.
[29] 상기유선비행체에너지공급시스템에 있어서，임무용유체를공급하기위한 임무용유체공급부와상기임무용유체를전송하기위한유체전송케이블을 추가적으로더포함할수있다. In the wired vehicle energy supply system, a mission fluid supply unit for supplying a mission fluid and a fluid transmission cable for transmitting the mission fluid are provided. In addition, you can include more.
[30] 상기유선비행체에너지공급시스템에 있어서，상기비행체는제 1비행체를 포함하는복수의비행체를포함하고,상기케이블은제 1비행체를경유하여 나머지비행체들에직렬로연결되고，상기복수의비행체는상기케이블로부터 에너지를공급받으며 ,상기복수의비행체를연결하는케이블은길이가고정된 것일수있다.  [30] The wired vehicle energy supply system, wherein the flying body includes a plurality of flying objects including a first flying body, and the cable is connected in series to the remaining flying vehicles via the first flying body, and the plurality of flying bodies. Is supplied with energy from the cable, and the cable connecting the plurality of vehicles may be fixed in length.
[31] 상기비행체에는상기케이블의：장력을감지하는장력감지기가설치될수 있다.  A tension sensor for detecting the tension of the cable may be installed in the flying vehicle.
[32] 상기유선비행체에너지공급시스템에 있어서，상기케이블은통신신호를 전송할수있는통신선을포함할수있다.  In the wired vehicle energy supply system, the cable may include a communication line capable of transmitting a communication signal.
[33] 상기유선비행체에너지공급시스템에 있어서,상기케이블의장력및길이를 조절하는케이블조절부를포함할수있다. In the wired flight energy supply system, a cable control unit for adjusting the tension and length of the cable may be included.
[34] 상기케이블조절부는，케이블의감김과풀림을수행하는드럼；상기드럼의 중심축으로 360도회전하는정렬기;상기정렬기를구동하는모터구동부；상기 케이불의이동경로를제공해주는이동가이드;를포함하여상기정렬기가 회전하여상기드럼에케이블을감거나푸는것일수있다. The cable control unit includes: a drum for winding and unwinding the cable; a sorter rotating 360 degrees about a central axis of the drum; a motor driving unit driving the sorter; a moving guide providing a movement path of the cable; The sorter may be rotated to wind or unwind a cable to the drum.
[35] 상기케이블조절부는,케이블의감김과풀림을수행하는드럼；상기드럼을 구동하는모터구동부；상기케이블의이동경로를제공해주는이동가이드;를 포함하여상기드럼이회전하여상기드럼에케이블을감거나푸는것일수 있다.  The cable control unit includes a drum for winding and unwinding the cable; a motor driving unit for driving the drum; a moving guide for providing a movement path of the cable; and the drum rotates to connect a cable to the drum. It can be wound or unwound.
[36] 상기케이블조절부는，케이블의감김과풀림을수행하는드럼；상기드럼을 구동하는모터구동부；상기케이블의이동경로를제공해주는이동가이드; 상기드럼의회전축으로 360도회전하는정렬기;상기드럼과정렬기의위치를 감지하는위치센서；를포함하는것일수있다.  The cable control unit includes: a drum for winding and unwinding the cable; a motor driving unit for driving the drum; a movement guide for providing a movement path of the cable; It may include a aligner rotates 360 degrees to the axis of rotation of the drum; a position sensor for detecting the position of the drum process locator;
[37] 상기유선비행체에너지공급시스템 23에 있어서，상기케이블의길이를 일정하기유지하기위해상기정렬기의정렬위치에드럼이상기모터구동부에 의해추종제어가되어정렬기와드럼간의정렬위치오차가 0이되도록하는 것일수있다.  In the wired airplane energy supply system 23, in order to keep the length of the cable constant, a drum is controlled by the motor driver so that the alignment position error between the alignment unit and the drum is zero. It may be possible.
[38] 상기유선비행체에너지공급시스템에 있어서，상기드럼은안정적으로  In the wired aircraft energy supply system, the drum is stably
균일하게풀림과감김이수행되도록드럼의회전축방향으로케이블의 직선운동을제공하는보조가이드를더포함하는것일수있다.  It may further include an auxiliary guide that provides a linear movement of the cable in the direction of the axis of rotation of the drum so that the unwinding and winding are carried out uniformly.
[39] 상기유선비행체에너지공급시스템에 있어서，상기케이블조절부는드럼 회전중심내부에수소저장부를위치하는것일수있다.  In the wired vehicle energy supply system, the cable control unit may be a hydrogen storage unit inside the drum rotation center.
[40] 상기유선비행체에너지공급시스템에 있어서，상기케이블조절부의드럼은 수소저장부와한몸체로형성되어드럼의회전축을중심으로회전하는것일수 있다.  In the wired vehicle energy supply system, the drum of the cable control unit may be formed in one body with the hydrogen storage unit to rotate the rotation axis of the drum.
[41] 상기유선비행체에너지공급시스템에 있어서，상기케이블은소정와높이에 위치하는케이블경유기를경유하도록케이블경유기와상기케이블경유기가 설치되는케이블경유비행체를더포함하는것일수있다. [41] In the wired aircraft energy supply system, the cable router and the cable router are connected to each other via a cable router located at a predetermined height. It may also include more via the cable installed.
[42] 상기유선비행체에너지공급시스템에 있어서，상기케이블은소정의높이에 위치하는케이블경유기를경유하도록케이블경유기와상기케이블경유기를 지지하는케이블경유기지지대를더포함하는것일수있다.  In the wired vehicle energy supply system, the cable may further include a cable duct and a cable duct supporter for supporting the cable duct via a cable duct located at a predetermined height.
[43] 상기케이블경유기는케이블조절부의드럼또는정렬기의회전축선상에  [43] The cable router is located on the rotation axis of the drum or the alignment unit of the cable control unit.
위치하는것일수있다.  May be located.
[44] 상기케이블경유기는케이블조절부의드럼또는정렬기의회전축선상에  [44] The cable router is located on the axis of rotation of the drum
소정의높이에위치하도록상기케이블경유기지지대가구성되는것일수있다.  The cable carrier support may be configured to be at a predetermined height.
[45] 상기케이블경유기지지대는회전식케이블조절부의드럼회전중심부에  [45] The cable carrier support part is provided in the drum rotation center of the rotary cable control unit.
설치되는것일수있다.  It may be installed.
[46] 상기케이블경유기지지대는，상기정렬기의회전시형성되는원통의외부에 고정되고;상기원통상단의증심에서시작하여상기정렬기회전축선상의 소정의높이에설치된상기케이블경유기까지관통구멍을갖는파이프형상일 수있다, ：  The cable transit supporter is fixed to the outside of the cylinder formed when the sorter rotates; the through hole from the core end to the cable transiter installed at a predetermined height on the sorter rotation axis. It can be a pipe shape with:
[47] 상기케이블경유기는，케이블이동경로의접선방향에접촉면을제공하는  [47] The cable router provides a contact surface in the tangential direction of the cable movement path.
회전체，상기회전체의회전축에수직방향인증력방향을회전축으로회전할수 있는회전부를포함하는것일수있다.  The rotating body may include a rotating part capable of rotating the direction of the vertical authentication force on the rotating shaft of the rotating body to the rotating shaft.
[48] 상기케이블경유기와케이블경유기지지대는상기케이블조절부에서 [48] The cable router and the cable router support may be provided in the cable control unit.
이격되어장애물의우회경로와긴수평거리를제공하도록다수의지점에 설치되는것일수있다.  It may be located at multiple points apart to provide a bypass and long horizontal distance of the obstacle.
[49] 상기케이블조절부에서이격되는지점에설치되는케이블경유기는일측면의 상단이개방되어케이블을구속하지않는것일수있다. The cable route installed at the point where it is spaced apart from the cable control part may be an open top of one side so as not to bind the cable.
[50] 상기케이블조절부에서이격되는지점에설치되는케이블경유기는케이블의 이동마찰을최소화하기위해이동경로의접선방향에접촉면을제공하는하부 회전체와좌우회전체를포함하고,좌우회전체는케이블의좌우에위치하고, 하부회전체는케이블의하부에위치하여 ,하부회전체와좌우회전체는서로 수직되는방향으로회전하는것일수있다. [50] The cable router installed at a point spaced apart from the cable control unit includes a lower rotating body and a left rotating body which provide a contact surface in the tangential direction of the moving path to minimize the moving friction of the cable. Located at the left and right of the cable, the lower rotor is located at the bottom of the cable, the lower rotor and the left and right rotors may be rotated in a direction perpendicular to each other.
[51] 상기케이블경유기는비행체의케이블이하강하여상기 케이블경유기의 [51] The cable router descends the cable of the vehicle so that the cable router
회전체에쉽게접촉되도록케이블가이드를더포함하는것일수있다.  It may further include a cable guide for easy contact with the rotating body.
발명의효과  Effects of the Invention
[52] 본발명에의한비행체에너지공급시스템은，지상으로부터유선으로  [52] The airplane energy supply system according to the present invention is wired from the ground.
비행체에에너지를공급함에 있어서，유선비행체의비행거리가길어지더라도， 에너지의전송손실은거의발생되지않고，유선비행체가감당해야케이블의 하중은대폭적으로감소시킬수있다.  In supplying energy to the aircraft, even if the flying distance of the wired aircraft is longer, the transmission loss of energy is hardly generated, and the cable weight can be greatly reduced when the wired vehicle is to be handled.
[53] 또한유선비행체가수평으로이동하더라도케이블이지상의장애물에  [53] In addition, obstacles on the ground of the cable can be avoided even if the wired vehicle moves horizontally.
방해받지않는다.  Undisturbed
[54] 또한유선비행체가회전과선회비행으로자세변경이발생하더라도，케이블의 꼬임을해소할수있다. [54] In addition, even if the wired vehicle changes its position due to rotation and turning flight, The kink can be eliminated.
도면의간단한설명  Brief description of the drawings
[55] 도 1은본발명에의한비행체에너지공급시스템의일실시예의구성도 [56] 도 2는연료전지의구성도  1 is a configuration diagram of an embodiment of a flying body energy supply system according to the present invention. FIG. 2 is a configuration diagram of a fuel cell.
[57] 도 3은케이블조절부의 예 3 is an example of a cable control unit
[58] 도 4는회전체이동변위검출방식와장력감지기의실시예  4 illustrates an embodiment of a rotating body displacement detection method and a tension sensor.
[59] 도 5는케이블조절부와수소저장부로구성되는연료전지연료공급장치의 실시예의사시도 FIG. 5 is a perspective view of an embodiment of a fuel cell fuel supply device including a cable control unit and a hydrogen storage unit. FIG.
[60] 도 6은전송케이블의실시예 1의단면도  6 is a sectional view of Embodiment 1 of a transmission cable
[61] 도 7은전송케이블의실시예 2의단면도및사시도  7 is a cross-sectional view and perspective view of a second embodiment of a transmission cable
[62] 도 8은전송케이블의실시예 3의단면도  8 is a sectional view of Embodiment 3 of a transmission cable;
[63] 도 9는전송케이불의끝단처리부실시예의사시도  9 is a perspective view of an embodiment of an end processing unit of a transmission cable;
[64] 도 10은다수의유체전송케이블을포함하는케이블연결구성도의예  10 is an example of a cable connection diagram including a plurality of fluid transmission cables
[65] 도 11은지상의장애물과케이블이간섭되는모습  [65] Figure 11 shows the interference between the ground obstacle and the cable
[66] 도 12는지지대케이블경유방식의일실시예의개념도  12 is a conceptual diagram of an embodiment of a support cable via a system;
[67] 도 13은케이블경유기를포함하는회전식케이블조절부의 일실시예  FIG. 13 illustrates an embodiment of a rotary cable control unit including a cable passer. FIG.
[68] 도 14는케이블경유기를포함하는고정식케이블조절부의일실시예  14 shows an embodiment of a fixed cable control unit including a cable passer
[69] 도 15는도 14(a)의 일실시예의사시도  FIG. 15 is a perspective view of one embodiment of FIG. 14 (a)
[70] 도 16은중간지지대케이블경유방식의일실시예의개념도  16 is a conceptual diagram of an embodiment of the intermediate support cable via a system;
[71] 도 17은중간지지대의케이블경유기일실시예  17 illustrates an embodiment of a cable router of an intermediate support;
[72] 도 18은비행체에의한케이블경유방식의실시예의개념도  FIG. 18 is a conceptual diagram of an embodiment of a cable routing method by a flying vehicle
[73] 도 19는비행체경유방식의케이블경유기실시예  19 illustrates an embodiment of a cable router using a route vehicle route.
[74] 도 20은데이지체인방식케이블연결구성도  20 is a block diagram of a daisy chain type cable connection
[75] 도 21은스프링식장력감지기실시예  21 is a spring tension sensor embodiment
[76] 도 22는사각지대시야확보를위한데이지체인연결도  [76] Figure 22 is a daisy chain connection diagram for securing the diagonal field of view
[77] 도 23은슬립링유닛의실시예  23 shows an embodiment of a slip ring unit.
[78] 도 24는케이블꼬임방지실시예 1와구성도  24 is a configuration diagram with Example 1 of the cable twist prevention
[79] 도 25는케이블꼬임방지실시예 2의구성도  25 is a configuration diagram of cable twist prevention Example 2
[80] 도 26은케이블꼬임방지실시예 3의구성도  26 is a configuration diagram of a cable twist prevention Example 3
발명의실시를위한최선의형태  Best Mode for Carrying Out the Invention
[81] 본발명은다양한변경을가할수있고여러가지실시예를가질수있는바， 특정실시예들을도면에 예시하고상세한설명에상세하게설명하고자한다. 그러나이는본발명을특정한실시형태에대해한정하려는것이아니며，본 발명의사상및기술범위에포함되는모든변환,균둥물내지대체물을 포함하는것으로이해되어야한다.본발명을설명함에 있어서관련된공지 기술에대한구체적인설명이본발명의요지를흐릴수있다고판단되는경우 그상세한설명을생략한다. [82] 본출원에서사용한용어는단지특정한실시예를설명하기위해사용된 것으로，본발명을한정하려는의도가아니다.단수의표현은문맥상명백하게 다르게뜻하지않는한,복수의표현을포함한다. The present invention may be modified in various ways and may have various embodiments, and specific embodiments will be illustrated in the drawings and described in detail in the detailed description. However, this is not intended to limit the invention to a particular embodiment, it should be understood to include all transformations, lumps and substitutes included in the spirit and scope of the present invention. If it is determined that the specific description of the subject matter may obscure the subject matter of the present invention, the detailed explanation thereof will be omitted. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. The singular expression includes plural expressions unless the context clearly indicates otherwise.
[83] 본발명에서언급하는유선비행체에탑재되는전력공급시스템또는동력원은 비행체외부로부터공급되는연료에너지또는전기에너지를기반으로하여，본 발명의에너지공급시스템은전력공급방식과연료공급방식을모두포함한다. [83] The power supply system or power source mounted on the wired flying vehicle referred to in the present invention is based on fuel energy or electric energy supplied from the outside of the aircraft, and the energy supply system of the present invention provides both a power supply method and a fuel supply method. Include.
[84] 또한본발명에서언급하는유선비행체의 "케이블?용어는에너지공급 [84] Also, the term "cables" of wired aircraft referred to in the present invention is the energy supply.
케이블과유체전송케이블을포함하고，상기에너지공급케이블은연료전송 케이블과전력공급케이블로구분된다.  A cable and a fluid transmission cable, the energy supply cable is divided into a fuel transmission cable and a power supply cable.
[85] 본발명에서연료공급방식의에너지공급시스템은유선비행체의전력발생을 위해연료전지를사용한다. In the present invention, the fuel supply energy supply system uses fuel cells to generate power for wired aircraft.
[86] 연료전지에는천연가스,메탄올，가솔린등의다양한연료가사용되어질수 있는데，연료개질기 (fuel reformer)를이용해수소로개질하거나순수수소를 사용한다. [000] Fuel cells can be fueled by a variety of fuels, including natural gas, methanol and gasoline, which can be reformed into hydrogen using a fuel reformer or pure hydrogen.
[87] 연료전지는연료와산화제를전기화학적으로반웅시켜전기에너지를  [87] Fuel cells electrochemically react fuel and oxidants to produce electrical energy.
발생시키는장치이다.이화학반웅은촉매층내에서촉매에의해이루어지면， 일반적으로연료가계속적으로공급되는한지속적으로전기를발생시킨다.  This chemical reaction is generated by the catalyst in the catalyst bed and generally generates electricity as long as the fuel is continuously supplied.
[88] 연료와산화제로는여러가지를이용할수있다.수소연료전지는수소를  [88] Several fuels and oxidants are available. Hydrogen fuel cells use hydrogen.
연료로，산소를산화제로이용하며，그외에탄화수소，알코올등을연료로，공기， 염소，이산화염소등을산화제로이용할수있다.  As a fuel, oxygen can be used as an oxidizing agent. In addition, hydrocarbons and alcohols can be used as fuel, and air, chlorine and chlorine dioxide can be used as oxidizing agents.
[89] 연료전지의본체는유입되는수소로공기중의산소로직류전기와물및  [89] The main body of the fuel cell is introduced hydrogen, oxygen in the air, direct current electricity, water and
부산물을발생시킨다.  Generates byproducts.
[90] 연료전지는연료개질기 (fuel reformer)를포함할수있는데,연료개질기는  [90] Fuel cells may include a fuel reformer, which is a fuel reformer.
유입되는연료가수소외에연료 (예를들면,메탄올,메탄, LPG, LNG，가솔린 둥)일경우그연료로부터수소를얻을수있다.  If the incoming fuel is fuel other than hydrogen (eg methanol, methane, LPG, LNG, gasoline), hydrogen can be derived from the fuel.
[91] 지상또는지상건물둥에위치하는연료전지연료공급장치에서비행체로  [91] From a fuel cell fuel supply located on the ground or above ground, to a flying vehicle
연료전지연료를공급하고,비행체내의연료전지에서전기를생산하여비행체 내에공급한다면,종래의유선전력공급방식보다여러가지이점이있다.  There are a number of advantages over conventional wired power delivery methods when supplying fuel cell fuel and producing electricity from the fuel cells in the vehicle and supplying it into the vehicle.
[92] 첫째，종래의유선전력공급방식은전력을공급하는케이블의저항으로인해 비행거리에비례하여유실되는전력이커지지만,연료전지연료공급방식은 연료전지연료를전송하는전송케이블에서누설이없다면,유실되는에너지는 거와없다.  [92] First, the conventional wired power supply method increases the power lost in proportion to the flight distance due to the resistance of the cable supplying the power. However, the fuel cell fuel supply method leaks from the transmission cable that transmits the fuel cell fuel. If not, no energy is lost.
[93] 둘째，종래의유선전력공급방식은케이블이밀도가높은금속의  [93] Second, the conventional wired power supply method uses a metal with a high density of cables.
전도체 (예:구리)가포함하여매우무거우나，연료전지연료공급방식의 케이블은금속의전도체가포함되지않고유체를전송할수있는가벼운 류브 (호스)로구성할수있어연료전송케이블의무게를경량화할수있다.  Very heavy, including conductors (e.g. copper), fuel-fueled cables can be made up of lightweight lubrication (hoses) that do not contain metal conductors and can carry fluid to reduce the weight of the fuel transmission cable .
[94] 특히연료전지연료가수소인경우，수소는매우가볍고확산속도가빨라서  [94] Especially when the fuel cell fuel is hydrogen, hydrogen is very light and has a fast diffusion rate.
높은곳에 있는비행체에전송할때유리하다.또한수소를전송하면，전송 케이블은부력을받아서그무게가더욱가벼워지고비행체의부하는더욱 즐어드는장점이있다. This is advantageous when transferring to a high plane. Also, if you transfer hydrogen, Cables are buoyant, making their weight lighter and the load on the aircraft more enjoyable.
[95] 또한，본발명에서는비행체의동력원과전력공급을위해연료전지를이용하지 않고，내연기관 (수소엔진,가솔린엔진,디젤엔진, LNG엔진등)과발전기를 이용할수도있다.  [95] The present invention also allows the use of internal combustion engines (hydrogen engines, gasoline engines, diesel engines, LNG engines, etc.) and generators without using fuel cells to supply power and power to the aircraft.
[96] 즉，지상에서비행체의내연기관에연료전송케이블을통해내연기관의  [96] In other words, through the fuel transmission cable to the internal combustion engine of the aircraft on the ground
연료 (수소,가솔린,디젤, LNG등)를지상에서공급하는구조이다.  It is a structure that supplies fuel (hydrogen, gasoline, diesel, LNG, etc.) from the ground.
[97] 상기내연기관의대표적인수소엔진은수소를연료로하는엔진을말하며， 연료공급방식에따라수소를흡기관에공급하여공기와흔합된형태로 연소실로공급하는방식과수소를직접연소실로공급하는방식으로대별할수 있다.  The representative hydrogen engine of the internal combustion engine refers to an engine that uses hydrogen as a fuel, and supplies hydrogen to the intake pipe according to the fuel supply method, and supplies hydrogen to the combustion chamber in a form compatible with air and hydrogen directly to the combustion chamber. Can be distinguished by the way.
[98] 수소엔진이동력 (회전력등의움직이는힘)을발생시키면，발전기는그동력을 이용하여전기를생산한후비행체내부에전기를공급할수있다.  [98] When the hydrogen engine generates a moving force (moving force such as rotational power), the generator can use that power to produce electricity and then supply electricity to the aircraft.
[99] 따라서내연기관과발전기를이용하는경우에도,종래의유선전력공급  [99] Therefore, even when using an internal combustion engine and a generator, conventional wired power supply
방식보다，유실되는에너지가적고연료전송케이블의무게가감소하여 비행체의부하가줄어드는장점이 있다.  Compared to the method, there is less energy lost and the weight of the fuel transmission cable is reduced to reduce the load on the aircraft.
[100] 도 1은본발명에의한유선비행체에너지공급시스템의일실시예의  1 is a view of an embodiment of a wired vehicle energy supply system according to the present invention.
구성도이다.  It is a block diagram.
[101] 본발명에의한유선비행체에너지공급시스템은유선비행체에너지공급 장치라고부를수도있다.  The wired airplane energy supply system according to the present invention may be referred to as a wired airplane energy supply device.
[102] 도 1의비행체에너지공급시스템은비행체 (100)，연료전지연료공급  [102] The flying vehicle energy supply system of FIG. 1 includes a flying vehicle 100 and fuel cell fuel supply.
장치 (200)，상기비행체 (100)와상기연료전지연료공급장치 (200)를연결하는 전송케이블 (300)을포함한다.  Apparatus 200, transmission cable 300 for connecting the vehicle 100 and the fuel cell fuel supply device 200.
[103] 상기연료전지연료공급장치 (200)는지상또는지하에 있을수도있고,지상의 건축물에위치할수도있지만，본발명의연료전지연료공급장치 (200)는상기 비행체 (100)의외부에위치한다. The fuel cell fuel supply device 200 may be located on the ground or underground, or may be located on a ground building, but the fuel cell fuel supply device 200 according to the present invention may be located outside the vehicle 100. Located.
[104] 상기비행체 (100)는연료전지 (110)，배터리 (120),비행체전기기기 (130)를 The flying body 100 includes a fuel cell 110, a battery 120, and a flying electric device 130.
포함한다.  Include.
[105] 상기연료전지 (110)는연료에너지의전달경로를제공해주는전송  The fuel cell 110 is a transmission providing a transfer path of fuel energy.
케이블 (300)과연결되어전송케이블 (300)로부터연료전지연료 (예를들면, 수소)를전송또는전달받을수있다.연료전지연료가수소인경우,상기 연료전지 (110)는전달받은수소와대기증의산소를이용하여전기를생산할수 있다.  A fuel cell fuel (eg, hydrogen) may be transmitted or received from the transmission cable 300 in connection with the cable 300. When the fuel cell fuel is hydrogen, the fuel cell 110 is delivered with hydrogen and atmospheric charge. Oxygen can be used to produce electricity.
[106] 비행체전기기기 (130)는작동을위해전기를필요로하는장치를의미하며, 비행체내에존재하면서전기를필요로하는모든장치는비행체  [106] The aircraft electrical equipment 130 means a device that requires electricity for operation, and all devices that require electricity while in the aircraft are flying vehicles.
전기기기 (130)에해당한다.비행체전기기기 (130)의 예로는  The electric device 130. An example of the flying electric device 130 is
비행제어장치，구동모터，통신장비,임무장비등이 있다.  There are flight control system, driving motor, communication equipment and mission equipment.
[107] 연료전지 (110)에서생산된전기는비행체전기기기 (130)에바로전송될수도 있지만，배터리 (120)에저장된후에비행체전기기기 (130)에전송될수도있다. 상기배터리 (120)은직류버퍼링기능을제공하는보조전원으로서,연료전지가 전기를생산하지못할경우비상전원기능도수행할수있다. The electricity produced by the fuel cell 110 may be transmitted directly to the flying electric machine 130. However, it may also be transmitted to the flying electrical device 130 after being stored in the battery 120. The battery 120 is an auxiliary power supply that provides a DC buffering function. When the battery 120 does not produce electricity, the battery 120 may also perform an emergency power supply function.
[108] 또한，상기연료전지 (110)의출력을요구되는출력 (또는전압)으로제어하기 위하여전력변환기 (140)를연료전지 (110)와배터리 (120)사이에더포함할수도 있다. In addition, a power converter 140 may be further included between the fuel cell 110 and the battery 120 to control the output of the fuel cell 110 to the required output (or voltage).
[109] 상기연료전지연료공급장치 (200)은수소발생부 (210)，수소저장부 (220)，공급 제어부 (230),케이블조절부 (240)을포함한다.  The fuel cell fuel supply device 200 includes a hydrogen generation unit 210, a hydrogen storage unit 220, a supply control unit 230, and a cable control unit 240.
[110] 설계상의필요에따라서는수소발생부 (210)과케이블조절부 (240)는생략될 수있고，공급제어부 (230)의기능은수소저장부 (220)에포함될수있다. Depending on the design needs, the hydrogen generating unit 210 and the cable control unit 240 may be omitted, the function of the supply control unit 230 may be included in the hydrogen storage unit 220.
[111] 수소발생부 (210)는수소를발생시키는장치이다.수소를발생시키는 [111] The hydrogen generator 210 is a device for generating hydrogen.
방법으로는물을전기분해하는것，천연가스，메탄올등으로부터연료개질기를 이용하여수소를발생시키는방법등이 있다.  Methods include electrolysis of water and generation of hydrogen using a fuel reformer from natural gas, methanol, and the like.
[112] 수소발생부 (210)에서발생된수소는수소저장부 (220)에저장된후,필요시에 사용될수있다.실시예 1에서는수소발생부 (210)를포함하고있으나다른 곳에서생산한수소를저장용기등에담아와서사용할수도있으므로수소 발생부 (210)는본발명의구성에서제외될수도있다. Hydrogen generated from the hydrogen generator 210 may be stored in the hydrogen storage 220 and used when needed. In Example 1, the hydrogen generator 210 is included, but is produced elsewhere. Since hydrogen may be used in a storage container or the like, the hydrogen generator 210 may be excluded from the configuration of the present invention.
[113] 수소를저장하는방법으로는,액체로저장하는법，기체로저장하는법, [113] Hydrogen storage methods include liquid storage, gas storage,
금속수소화물형태의고체로저장하는법둥이 있다.  There is a method of storing as a solid in the form of metal hydride.
[114] 그리고작은부피로많은양의수소가스를저장하기위해서는,가볍고  [114] And to store a lot of hydrogen gas in small volumes,
내구성이우수한탄소섬유기반의수소가스저장용기를사용하는것이 바람직하다.  It is desirable to use a carbon fiber based hydrogen gas storage container with excellent durability.
[115] 상기공급제어부 (230)는수소발생부 (210)또는수소저장부 (220)로부터  The supply control unit 230 from the hydrogen generating unit 210 or the hydrogen storage unit 220
전달되는수소를전송케이블 (300)로전달함에 있어,수소가스의압력과최대 공급양을제어하고，수소가스누출이감지되거나비상시에는수소공급을 차단하는안전기능을포함한다.전송케이블 (300)로전달되는수소가스의 압력과양을제어하면，연료전지 (110)으로전달되는수소가스의압력과양도 제어된다.따라서공급제어부 (230)는최대수소공급량을조절함으로써 연료전지의최대출력전력 (연료전지에서출력되는최대전력의양)을쎄어할수 있다.  In delivering the delivered hydrogen to the transmission cable 300, it controls the pressure and the maximum supply amount of hydrogen gas, and includes a safety function to detect the leakage of hydrogen gas or to cut off the hydrogen supply in case of emergency. By controlling the pressure and amount of hydrogen gas delivered to the furnace, the pressure and amount of hydrogen gas delivered to the fuel cell 110 are also controlled. Thus, the supply control unit 230 controls the maximum amount of hydrogen supply so that the maximum output power ( The maximum amount of power output from the fuel cell can be counted.
[116] 본발명에서상기공급제어부 (230)는기능적으로수소저장부 (220)에포함될 ' 수있다ᅳ [116] included in the feed control unit 230 functionally hydrogen stored in unit 220 in the present invention, can eu
[117] 또한도 2에서보는바와같이비행체에서상기연료전지 (110)의연료전지 스택 (111)에공급되는수소가스를제어밸브를포함하는연료전지제어기 (112)를 통하여제어 (조절)하므로써,비행체의전기기기 (130)에공급되는  In addition, as shown in FIG. 2, the hydrogen gas supplied to the fuel cell stack 111 of the fuel cell 110 is controlled (adjusted) through a fuel cell controller 112 including a control valve in a flying vehicle. Supplied to the aircraft's electrical equipment 130
연료전지 (110)의출력전력을제어할수있다.  The output power of the fuel cell 110 can be controlled.
[118] 상기케이블조절부 (240)는기본적으로케이블의장력및길이를조절하는 장치이다.전송케이블 (300)의한쪽끝은케이블조절부 (240)에연결되고반대쪽 끝은비행체의연료전지 (110)에연결되는데，비행체가회전또는선회비행을 하게되면전송케이블의꼬임이발생한다. The cable control unit 240 is basically a device for adjusting the tension and length of the cable. One end of the transmission cable 300 is connected to the cable control unit 240 and the other side The tip is connected to the fuel cell 110 of the flying vehicle. When the flying vehicle rotates or rotates, twisting of the transmission cable occurs.
[119] 따라서도 1의비행체에너지공급시스템은비행체가회전및선회시에케이블 꼬임이발생되지않도록케이블꼬임방지기능을구비하는것이바람직하다.  Therefore, it is preferable that the flight energy supply system of FIG. 1 has a cable twist prevention function to prevent the cable twisting when the aircraft rotates and turns.
[120] 또한본발명에서케이블조절부는케이블이감기는드럼 (릴또는스풀)의 회전유무에따라회전식과고정식으로구분한다. In addition, according to the present invention, the cable control part is divided into a rotary type and a fixed type according to whether the drum (reel or spool) is wound around the cable.
[121] 즉회전식은일반적으로널리사용하는방식으로드럼 (릴)이회전하여 [121] In other words, the rotary type is a widely used method where the drum (reel) rotates.
케아블을감거나푸는방식이고,고정식은고정된드럼 (릴)에케이블을감거나 푸는방식이다.  The cable is wound or unwound and the fixed type is a cable wound or unwound on a fixed drum (reel).
[122] 도 3은케이블조절부의실시예이다. 3 is an embodiment of a cable control unit.
[123] 도 3에서케이블조절부 (240)는모터구동부 (241)과드럼 (242)，이동  In FIG. 3, the cable adjusting unit 240 includes a motor driving unit 241 and a drum 242.
가이드 (244),정렬기 (243),보조가이드 (255)를포함한다.  Guide 244, aligner 243, and auxiliary guide 255.
[124] 여기서，상기드럼 (242)이모터구동부 (241)에의해회전하는구조를가지면 일반적으로널리사용하는회전식이되고,반면에상기드럼 (242)은고정되고， 상기고정된드럼 (242)에케이블 (300)을감거나푸는기능을제공하는  Here, when the drum 242 has a structure that rotates by the motor driving unit 241, it is a commonly used rotary type, while the drum 242 is fixed, and the fixed drum 242 To provide the ability to wind or unwind cable 300
정렬기 (243)가모터구동부 (241)에의해드럼주위를회전하면고정식이된다.  When the aligner 243 rotates around the drum by the motor driver 241, it becomes fixed.
[125] 상기고정식에서케이블 (300)은정렬기의회전방향에따라케이블 (300)이  In the fixed type, the cable 300 is connected to the cable 300 according to the direction of rotation of the aligner.
드럼 (242)에풀림과감김동작이수행된다.  Unwinding and winding operations are performed on the drum 242.
[126] 또한고정식의케이블조절부 (240)는드럼이회전하지않으므로에너지 (연료， 전기)를공급하는에너지공급케이블 (300)와의연결은로터리조인트또는 슬립링을사용하지않고직접연결할수있는장점을가진다.  In addition, the fixed cable control unit 240 does not rotate the drum, so the connection with the energy supply cable 300 for supplying energy (fuel, electricity) has the advantage of being able to connect directly without using rotary joints or slip rings. Have
[127] 케이블아꼬임없이원활하게드럼에풀리거나감기도록하는이동  [127] movements that allow the cable to be unwound or wound smoothly without twisting the cable
가이드 (244)는케이블 (300)의이동경로를접선방향으로하는회전체 (예， 롤러)로구성된다.  The guide 244 is composed of a rotating body (for example, a roller) that tangentially moves the path of the cable 300.
[128] 또한상기이동가이드 (244)는다수의회전체 (예，롤러)를다단으로구성하면， 케이블 (300)의방향과이동경로를원하는대로변경할수있다.  In addition, if the moving guide 244 is composed of a plurality of rotating bodies (for example, rollers) in multiple stages, the direction and the moving path of the cable 300 can be changed as desired.
[129] 도 3에서보조가이드 (255)는드럼 (242)에균등하게안정적으로케이블이  In FIG. 3, the auxiliary guide 255 is stably connected to the drum 242 in a stable manner.
감기거나풀릴수있도록있도록하기위한것이다.이를위하여  It is intended to be able to be wound or unwound.
보조가이드 (255)는드럼의회전각과연동하여드럼의회전축방향으로 직선운동한다.  The auxiliary guide 255 linearly moves in the direction of the rotation axis of the drum in association with the rotation angle of the drum.
[130] 또한비행체 (100)가 360도선회하더라도케이블 (300)의꼬임이발생하지  In addition, even if the flying vehicle 100 turns 360 degrees, the twisting of the cable 300 does not occur.
않도록하는정렬기 (243)를더포함하는것을특징으로한다.  It further comprises a sorter (243) to avoid.
[131] 도 3에서보는바와같이케이블조절부 (240)가회전식인경우드럼의회전축 방향은수직이다.드럼의회전축방향이수직인경우，상기정렬기 (243)는고정될 수도있고,드럼 (242)의회전축을중심으로하여자유롭게회전할수있다.  As shown in Fig. 3, the rotation axis direction of the wood drum is vertical when the cable control unit 240 is rotated. When the rotation axis direction of the drum is vertical, the sorter 243 may be fixed, and the drum ( It is possible to rotate freely with the rotation axis of 242 as the center.
[132] 즉，상기드럼 (242)은모터구동부 (241)에의해회전하고，정렬기 (243)는  That is, the drum 242 is rotated by the motor driving unit 241, the sorter 243 is
비행체 (100)의위치에의해결정되는케이블 (300)의장력에의해자유롭게 회전하거나정렬기 (243)의구동에의해회전할수있다. [133] 따라서，정렬기 (243)와드럼 (242)은서로독립적으로회전하는구조를가질수 있다. It can rotate freely by the tension of the cable 300, which is determined by the position of the vehicle 100, or by the drive of the sorter 243. Thus, the sorter 243 and the drum 242 may have a structure that rotates independently of each other.
[134] 또한회전식에서유선비행체의케이블을감거나푸는경우가아닌경우에는 비행체와연결된케이블의길이를일정하게유지할필요가있다.  [134] It is also necessary to maintain a constant length of the cable connected to the aircraft, unless the cable of the wired vehicle is wound or unwound in a rotary system.
[135] 이를위하여，정렬기 (243)가회전하여정렬기의정렬위치가변하면  For this purpose, if the sorter 243 rotates to change the sorting position of the sorter,
위치센서 (245)에의해제공되는정렬기 (243)와드럼 (242)간의정렬  Alignment between the sorter 243 and the drum 242 provided by the position sensor 245
위치오차가"영"이되도록모터구동부 (241)로드럼 (242)을희전시켜회전각 위치제어를수행할수있다.  The rotation angle position control can be performed by shifting the motor drive part 241 load rum 242 so that the position error becomes "zero".
[136] 즉비행체가선회시에는정렬기 (243)의정렬위치에드럼 (242)의  In other words, when the vehicle is turning, the drum 242 is placed in the alignment position of the sorter 243.
위치 (회전각)을추종하는정렬기추종제어를수행하는것을특징으로한다.  It is characterized by performing a sorter following control that follows the position (rotation angle).
[137] 케이블조절부 (240)는다른방식으로도구현할수있고，때에따라서는생략될 수도있다.다만케이블조절부 (240)를생략할때는케이블을관리할별도의 방법이필요하다. The cable control unit 240 may be implemented in other ways, and may be omitted from time to time. However, when the cable control unit 240 is omitted, a separate method of managing the cable is required.
[138] 본발명의케이블조절부 (240)는케이블이동경로에케이블장력감지기를 포함하여케이블의감김과풀림을통하여케이블의장력을조절할수있다.  The cable control unit 240 of the present invention can adjust the tension of the cable through the winding and unwinding of the cable, including the cable tension sensor in the cable movement path.
[139] 도 4는회전체의이동변위로장력을검출하는장력감지기의실시예이다. FIG. 4 is an embodiment of a tension sensor for detecting a tension due to a displacement of a rotating body.
[140] 도 4에서보는바와같이, 2개의회전체 (BB)는고정되고케이블 (300)의 As shown in Figure 4, the two rotors (BB) are fixed and the cable 300
이동경로에케이블의장력에따라자유롭게움직일수있는회전체 (AA)가 포함되면회전체 (AA)의이동변위는케이블 (300)의장력에비례하게되고，그 이동변위를측정하여케이블 (300)의장력이감지된다.  If the path of travel includes a rotor (AA) that can move freely according to the tension of the cable, the displacement of the rotor (AA) is proportional to the tension of the cable (300), and the movement displacement is measured to measure the cable (300). The design power is sensed.
[141] 본발명의케이블조절부에서케이블의장력을조절하기위해일반적으로널리 사용되는도 4의회전체변위검출방식의장력감지기는본발명의나머지 도면에서는생략하도록한다. The tension sensor of the rotor displacement detection method of FIG. 4, which is generally used to control the tension of the cable in the cable control part of the present invention, is omitted in the remaining drawings of the present invention.
[142] 따라서도 3에서회전체변위검출방식의장력감지기표시는생략되어있다. Therefore, in FIG. 3, the tension sensor display of the rotor displacement detection method is omitted.
[143] 도 5는케이블조절부와수소저장부로구성되는연료전지연료공급장치의 실시예의사시도이다. 5 is a perspective view of an embodiment of a fuel cell fuel supply device including a cable control unit and a hydrogen storage unit.
[144] 회전식케이블조절부 (240)의드럼 (242)은회전운동을하므로드럼에감겨져 있는전송케이블 (300a)과독립적으로분리되어 있는수소저장부 (220)또는 수소발생부 (210)간의연결은일반적으로회전부와고정부간에  The drum 242 of the rotary cable control unit 240 rotates so that the connection between the transmission cable 300a wound on the drum and the hydrogen storage unit 220 or the hydrogen generator 210 is independently separated. Is generally between the rotor and the government
유체 (액체,공기,가스등)매질을전달하는기능을제공하는로터리조인트를 통하여연결할수있다.  Connections can be made via rotary joints that provide the ability to transfer fluid (liquid, air, gas, etc.) media.
[145] 도 5(a)에서는상기로터리조인트를사용하지않고수소저장부 (220)와케이블 조절부 (240)를일체형으로연결한실시예의사시도이다.  FIG. 5A is a perspective view of an embodiment in which the hydrogen storage unit 220 and the cable control unit 240 are integrally connected without using the rotary joint.
[146] 즉,도 5(a)에서수소저장부 (220)와드럼 (242)은한몸체 (동일프레임)로  That is, the hydrogen storage unit 220 and the drum 242 in Figure 5 (a) is a body (same frame)
구성되어모터구동부 (241)에의해드럼 (242)과공급제어부 (230)을포함하는 수소저장부 (220)는한몸체로회전한다.  The hydrogen storage unit 220, which includes the drum 242 and the supply control unit 230, is rotated by one body by the motor driving unit 241.
[147] 따라서상기수소저장부 (220)와드럼 (242)간에상호움직임이발생되지않아 로터리조인트를이용할필요가없는장점이 있다. [148] 도 5(b)는연료전지연료공급장치의다른실시예의사시도이다. Accordingly, there is an advantage that there is no need to use a rotary joint because no mutual movement occurs between the hydrogen storage unit 220 and the drum 242. 5 (b) is a perspective view of another embodiment of a fuel cell fuel supply device.
[149] 도 5(a)에서수소저장부 (220)는드럼 (242)의외부에위치하는반면에，도  In FIG. 5 (a), the hydrogen storage unit 220 is located outside the drum 242, while FIG.
5(b)에서는공간활용성을높이기위해원통형의수소저장부 (220)를상기 드럼 (242)의회전중심내부에위치하는구조이다.:  In 5 (b), a cylindrical hydrogen storage unit 220 is placed inside the center of rotation of the drum 242 to increase space utilization.
[150] 도 5의회전식케이블조절부 (240)는모터구동부 (241)로드럼 (242)과수소 5, the rotary cable control unit 240 of the motor driving unit 241, the rod rum 242 and hydrogen
저장부 (220)를동시에회전시켜드럼에 전송케이블 (300a)을감거나풀며 ,또한 전송케이블 (300a)의길이를일정하게유지할경우에는정렬기추종제어를할수 있다.  When the storage unit 220 is rotated at the same time, the transfer cable 300a is wound or unwound on the drum, and when the length of the transfer cable 300a is kept constant, sorter tracking control can be performed.
[151] 한편，도 5에서케이블조절부 (240)가고정식인경우에는，상기  On the other hand, in the case where the cable control unit 240 is fixed in Figure 5,
수소저장부 (220)와드럼 (242)은회전하지않고고정되며，모터구동부 (241)에 의한정렬기 (243)의회전으로드럼 (242)에케이블 (300a)의감김과풀림이 수행된다.  The hydrogen storage unit 220 and the drum 242 are fixed without rotation, and the winding and unwinding of the cable 300a is performed on the drum 242 by the rotation of the sorter 243 by the motor driving unit 241.
[152] 상기고정식케이블조절부는로터리조인트를사용하지않고수소저장부 ( 또는수소발생부)에직접전송케이블 (300a)을연결할수있는장점을제공한다.  The fixed cable control unit provides an advantage of connecting the transmission cable 300a directly to the hydrogen storage unit (or the hydrogen generation unit) without using a rotary joint.
[153] 그리고상기연료전지연료공급장치는차량에탑재되는경우수소저장부를 탑재하고있는수소연료전지자동차에탑재하는것이바람직하다.  In addition, when the fuel cell fuel supply device is mounted in a vehicle, the fuel cell fuel supply device is preferably mounted in a hydrogen fuel cell vehicle equipped with a hydrogen storage unit.
[154] 상기전송케이블 (300a)은연료전지연료를전송하는연료전송통로를  The transmission cable 300a connects a fuel transmission path for transmitting fuel cell fuel.
포함한다.  Include.
[155] 도 6은전송케이블의실시예 1의단면도이다.  6 is a sectional view of Embodiment 1 of a transmission cable.
[156] 전송케이블 (300a)의중심에는기본적으로연료전지의연료의전송을위한 연료전송통로 (310)가형성되어 있고，연료전송통로 (310)는내피 (320)에의해 둘러싸여있다.외피는 (340)는인장력과강도가우수한재질 (예，아라미드섬유， 고강도폴리에틸렌섬유등)인것이바람직하다.외피 (340)와내피 (320)사이에는 유연성과탄력성이우수한보호재 (330)가층전된다.  At the center of the transmission cable 300a, a fuel transmission passage 310 is basically formed for the transfer of fuel of the fuel cell, and the fuel transmission passage 310 is surrounded by the endothelium 320. 340 is preferably a material having excellent tensile strength and strength (eg, aramid fiber, high strength polyethylene fiber, etc.). A protective material 330 having excellent flexibility and elasticity is laminated between the outer skin 340 and the inner skin 320.
[157] 그결과，전송케이블 (300a)은가벼우면서도내구성이우수하다.  As a result, the transmission cable 300a is light and excellent in durability.
[158] 또한요구되는운용조건에따라전송케이블 (300a)은내피 (320)，외피 (340), 보호재 (330)의구분없이단일소재의류브 (예:실리콘튜브)로구현될수있다.  In addition, depending on the required operating conditions, the transmission cable 300a can be implemented as a single material rib (eg, a silicone tube) without the distinction between the inner shell 320, the outer shell 340, and the protective material 330.
[159] 도 7은전송케이블의실시예 2의단면도와사시도이다.  7 is a sectional view and perspective view of Embodiment 2 of a transmission cable.
[160] 도 7에서는，도 6의외피 (340)가외부의 인장력에버티는힘을제공하는것이 아니라내부에설치되는고강도중심선 (370)이외부의인장력에버티는힘을 제공한다.  In FIG. 7, the outer skin 340 of FIG. 6 does not provide an external tensile force, but provides an external tensile force other than the high-strength center line 370 installed therein.
[161] 고강도중심선 (370)은강한힘을견딜수있는선모양의물체로서，전송  [161] The high-strength center line 370 is a line-shaped object that can withstand strong forces and is transmitted.
케이블의중심부에위치하여중심선 (central line)이라부른다.  It is located at the center of the cable and is called the central line.
[162] 도 7의연료전송튜브 (360)는인장력과강도가상대적으로취약한일반용도의 연료전송튜브를사용할수있다. The fuel transfer tube 360 of FIG. 7 may use a general purpose fuel transfer tube in which tensile strength and strength are relatively weak.
[163] 도 7에서는,인장력과강도가우수한재질 (예,아라미드섬유,고강도 [163] In Fig. 7, a material having excellent tensile strength and strength (eg, aramid fiber, high strength).
폴리에틸렌섬유둥)로구성되는고강도중심선 (370)을연료전송통로 (310) 내부를관통하는구조로되어 있다. [164] 따라서상기고강도중심선 (370)에의해，도 7의전송케이블은높은인장력과 강도를효과적으로유지할수있다. A high-strength center line 370 composed of a polyethylene fiber column penetrates the fuel transmission passage 310 inside. Thus, by the high strength center line 370, the transmission cable of Figure 7 can effectively maintain a high tensile strength and strength.
[165] 또한상기튜브 (360)은비행체 (100)와유선통신을하기위한통신선 (350)을 포함할수있다. In addition, the tube 360 may include a communication line 350 for wired communication with the aircraft 100.
[166] 도 7에서통신선 (350)은전기를전도할수있는구리선일수도있지만，무게가 가볍고데이터전송량이많은광섬유통신선일수도있다.  In FIG. 7, the communication line 350 may be a copper line capable of conducting electricity, but may also be an optical fiber communication line that is light in weight and has a large amount of data transmission.
[167] 도 8은전송케이블의실시예 3의단면도이다. 8 is a sectional view of Embodiment 3 of a transmission cable.
[168] 도 8에서와같이 1가닥의튜브 (360)내부에연료전송통로 (310)와유체전송 통로 (310a)의다중전송통로가구성되면,연료를포함한다종의유체를 독립적으로전송할수있다.  As shown in FIG. 8, when the fuel transmission passage 310 and the fluid transmission passage 310a are configured in the multiple transmission passages 310 in one strand of the tube 360, the fluids including the fuel may be transferred independently. .
[169] 또한도 8의전송케이블 (300a)은 1개의류브 (360)로다수의유체를전송할수 있는다중전송튜브구조로인하여，유체를개별적인튜브로전송하는것보다 전송케이블 (300a)의무게를대폭적으로줄일수있는장점을제공한다.  In addition, the transmission cable 300a of FIG. 8 has a multiple transmission tube structure capable of transmitting a large number of fluids to a single valve 360, so that the weight of the transmission cable 300a is increased rather than transferring the fluid to individual tubes. It offers the advantage of greatly reducing.
[170] 도 8에서광섬유 (350a)통신선은연료전송통로 (310)내부를관통하는구조로 구성되면，다음과같은장점을제공한다.  In FIG. 8, when the optical fiber 350a communication line is configured to penetrate the fuel transmission passage 310, the optical fiber 350a provides the following advantages.
[171] 첫째，연료전송케이블 (300a)과광섬유 (350a)통신선을 1가닥케이블로통합할 수있다.  [171] First, the fuel transmission cable 300a and the optical fiber 350a communication line can be integrated into a single-stranded cable.
[172] 둘째，광섬유또는광섬유통신선의보호외피 (또는피복)를튜브 (360)로  [172] Second, the protective sheath (or sheath) of the optical fiber or optical fiber communication line was transferred to the tube 360.
대산할수있어광섬유통신선은별도의보호외피가필요없어지므로광섬유 통신선의부피와무게를대폭감소시킬수있다.  This makes it possible to reduce the volume and weight of the fiber optic cable by eliminating the need for a separate protective jacket.
[173] 세째,광섬유는전기신호가아닌광신호로동작하기때문에연료전송케이블의 연료와상호아무런영향을주지않는다.  [173] Third, the fiber does not interact with the fuel of the fuel transmission cable because it operates with an optical signal rather than an electrical signal.
[174] 여기서연료전송은연료전송통로 (310)공간에서광섬유 (350a)통신선이  In this case, the fuel transmission is performed by the optical fiber 350a communication line in the space of the fuel transmission passage 310.
차자하는점유공간을제외한나머지공간을통해이루어진다.  This is accomplished through the remaining space, excluding the occupied space.
[175] 도 9는전송케이블 (300a)의끝단처리부실시예의사시도를보여준다.  9 shows a perspective view of an embodiment of the end processing unit of the transmission cable 300a.
[176] 광섬유 (350a)통신선은튜브 (360)의시작단과끝단부위에도 9에서보는바와 같이연료전송통로 (310)와광섬유 (350a)통신선으로분기된다.  The optical fiber 350a communication line is also branched into the fuel transmission path 310 and the optical fiber 350a communication line as shown in Fig. 9 at the start and end portions of the tube 360.
[177] 도 10은다수의유체전송케이블을포함하는케이블연결구성도의 예이다.  10 is an example of a cable connection diagram including a plurality of fluid transmission cables.
[178] 도 10에서비행체 (100)의케이블 (300)은에너지공급부 (2000)에서  In FIG. 10, the cable 300 of the flying vehicle 100 is connected to the energy supply unit 2000.
에너지 (연료，전기)를공급하기위한에너지공급케이블 (3000)이외에추가로 임무용유체공급부 (2000a)에서비행체 (100)에요구되는임무에대웅되는 다양한유체 (예：농약，비료둥)를제공할수있도록유체전송케이블 (3000a)를더 포함할수있다.  In addition to the energy supply cable 3000 for supplying energy (fuel, electricity), the mission fluid supply 2000a provides a variety of fluids (eg pesticides, fertilizer studs) for the mission required by the aircraft 100. It may further comprise a fluid transfer cable (3000a).
[179] 상기에너지공급케이블 (3000)과유체전송케이블 (3000a)은케이블  The energy supply cable 3000 and the fluid transmission cable 3000a are cables
조절부 (240)를경유하여비행체 (100)에연결된다.  It is connected to the vehicle 100 via the adjusting unit 240.
[180] 따라서본발명의유선비행체에너지공급시스템은비행체에에너지 (연료, 전기)공급뿐만아니라,요구되는임무에대웅되는다양한유체 (예:농약,비료 등)를제공하기위하여유체전송케이블을더구비할수있다. [181] 한편，도 1에서비행체에유선으로에너지를공급하는경우，비행체가 수직방향으로만비행하지않고수평방향으로비행을하게되면，케이블 (300)의 경사각과케이블처짐으로지상의장애물과간섭이발생하게되고，이로인하여 비행쎄방해를받을수있다. [180] The wired aircraft energy supply system of the present invention thus provides not only the supply of energy (fuel, electricity) to the aircraft, but also provides a fluid transmission cable to provide a variety of fluids (e.g. pesticides, fertilizers, etc.) for the required mission. Can be equipped On the other hand, in the case of supplying energy to the flying vehicle in FIG. 1 by wire, when the flying vehicle is flying in the horizontal direction instead of flying only in the vertical direction, the obstacle and interference on the ground are caused by the inclination angle of the cable 300 and the cable deflection. This can cause flight interruption.
[182] 도 11은지상 (1)의장애물 (2)과케이블 (300)이간섭되는모습이다. FIG. 11 shows how the obstacle 2 and the cable 300 of the ground 1 are interfered with.
[183] 비행체 (100)가수평방향으로움직일때,케이블 (300)이지상 (1)위의 [183] Above the ground (1), when the aircraft (100) moves horizontally, the cable (300)
장애물 (2)에걸려서움직임에방해를받을수있다.  The obstacles (2) can be hindered by the movement.
[184] 도 12는지지대케이블경유방식의일실시예의개념도이다. 12 is a conceptual diagram of an embodiment of a support cable route method.
[185] 도 12(a)는본발명에서수평비행시케이블의경사각과처짐으로인하여 12 (a) is due to the inclination angle and deflection of the cable during horizontal flight in the present invention.
발생되는지상장애물과케이블간의간섭을방지하기위한지지대에의한 케이블경유방식의개념도이다.  This is a conceptual diagram of the cable route by the support to prevent interference between the obstacle and the cable if it occurs.
[186] 도 12(b)는지지대 (5000)에의해케이블 (300)이들려서지상물 (2)의간섭이없는 상태의개념도이다. 12 (b) is a conceptual diagram of a state in which the cable 300 is lifted by the support 5000 so that there is no interference of the ground object 2.
[187] 도 12에서보듯이지지대경유방식은케이블조절부 (240)의케이블 (300)이 소정의높이를제공하는지지대 (5000)상단에설치되어 있는케이블  As shown in FIG. 12, in the support via method, a cable installed at an upper portion of the support 5000 provides a predetermined height of the cable 300 of the cable control unit 240.
경유기 (500)를경유하므로써 ,비행체가수평이동시에케이블 (300)이  By way of the transiter 500, the cable 300 is displaced when the vehicle moves horizontally.
지상물 (2)과간섭이되지않도록수직높이 (verticalheight)를제공한다.  Provide vertical height so as not to interfere with ground (2).
[188] 또한상기케이블경유기지지대 (5000)의높이에따라간섭을희피할수있는 지상물 (2)의최대높이가정해진다.  In addition, according to the height of the cable carrier support 5000, the maximum height of the ground object 2 that can avoid interference is determined.
[189] 그리고상기케이블경유기지지대 (5000)는상기케이블조절부 (240)의  And the cable carrier support (5000) of the cable control unit 240
방식 (회전식,고정식)에따라케이블조절부 (240)에부착되는위치와구조가 다르다.  Depending on the method (rotary, fixed), the position and structure of the cable control unit 240 is different.
[190] 도 13은케이블경유기를포함하는회전식케이블조절부 (240)의  13 is a view of a rotary cable control unit 240 including a cable passer
일실시예이다.  In one embodiment.
[191] 도 13(a)는일실시예의정면도아고,도 13(b)는도 13(a)의사시도이다.  FIG. 13 (a) is a front view of one embodiment, and FIG. 13 (b) is a perspective view of FIG. 13 (a).
[192] 도 13(c)는경유기와일실시예의사시도를보여준다. ：  FIG. 13 (c) shows a perspective view of an embodiment with a gasoline. ：
[193] 도 13(a)과도 13(b)에서케이블조절부 (240)의케이블 (300)은케이블  13 (a) and 13 (b), the cable 300 of the cable control unit 240 is a cable
경유기 (500)를경유하여비행체 (100)에연결되고，드럼 (242)의회전에의해 케이블 (300)의풀림과감김이수행되는회전식구조이다.  It is connected to the flying vehicle 100 via the diesel engine 500, and the rotation structure of the cable 300 is performed by the rotation of the drum 242 is a rotary structure.
[194] 또한,상기케이블경유기 (500)는케아블이동과비행체의위치에따른  In addition, the cable transit 500 is a cable according to the movement of the cable and the position of the flying vehicle.
케이블의다양한이동방향에대해이동마찰이최소화되도록，도 13(c)에서 보듯이상기케이블경유기 (500)는케이블 (300)이동경로의접선방향으로 접촉면을제공하는회전체 (520)와상기회전체 (520)의회전축에수직한 회전축을갖는회전부 (530) (베어링)로구성된다.또한상기회전체 (520)는 회전체지지대 (510)에의해지지되고，상기회전체지지대 (510)는  As shown in FIG. 13 (c), the cable route 500 includes a rotor body 520 and a rotor body that provide a contact surface in the tangential direction of the cable 300 movement path so that movement friction is minimized for various movement directions of the cable. And a rotating part 530 (bearing) having a rotating shaft perpendicular to the rotating shaft of 520. The rotating body 520 is supported by the rotating body support 510, and the rotating body support 510 is
회전부 (530) (베어링)와외륜에고정되고，상기회전부 (530) (베어링)의내륜은 케이블경유기지지대 (5000)에연결되는구조이다.  It is fixed to the rotating part 530 (bearing) and the outer ring, and the inner ring of the rotating part 530 (bearing) is connected to the cable carrier support 5000.
[195] 따라서，케이블경유기 (500)는케이블의이동과방향전환시에케이블에 작용하는마찰을최소화시킨다. [195] Accordingly, the cable passer 500 is connected to the cable at the time of movement and change of direction. Minimize the friction at work.
[196] 또한，케이블경유기지지대 (5000)는높은높이를조절할수있도록다양한 형상의다단식연결구조로구성될수있음은물론이다.  In addition, the cable carrier support 5000 may, of course, be composed of a multi-stage connection structure of various shapes to adjust the height.
[197] 도 14는케이블경유기를포함하는고정식케이블조절부의일실시예이다. FIG. 14 is an embodiment of a fixed cable adjuster including a cable passer. FIG.
[198] 도 14(a)는고정식케이블조절부의 일실시예의정면도이고,도 14(b)는케이블 경유기의일실시예의사시도이고，도 14(c)는지지대이동가이드의 일실시예의 사시도이다. 14 (a) is a front view of one embodiment of a fixed cable control unit, FIG. 14 (b) is a perspective view of one embodiment of a cable transiter, and FIG. 14 (c) is a perspective view of one embodiment of a support movement guide. .
[199] 도 14(a)에서고정삭케이블조절부 (240)는정렬기 (243)의회전에의해  In FIG. 14 (a), the fixed cable adjustment unit 240 is rotated by the alignment unit 243.
케이블 (300)이드럼 (242)에감김과풀림동작이수행된다.  Winding and unwinding operations are performed on the drum 242 of the cable 300.
[200] 도 14(a)에서상기정렬기 (243)회전에의해정렬기의회전반경과고정식 In Figure 14 (a) by the rotation of the sorter 243 rotation radius and fixed formula of the sorter
케이블조절부 (240)의높이를사각형단면으로하는원기등과，고정식케이블 조절부 (240)와지지대이동가이드 (544)간의경사진케이블 (300)경로를삼각형 단면으로하는원뿔공간이형성된다.  A cone space having a height of the cable adjusting section 240 as a square section, and a conical space having a triangular cross section of the inclined cable 300 between the fixed cable adjusting section 240 and the support movement guide 544 are formed.
[201] 따라서，상기고정식 케이블조절부 (240)에설치되는케이블경유기 Therefore, the cable passer that is installed in the fixed cable control unit 240
지지대 (5000)는상기고정식케이블조절부 (240)와간섭이발생되지않도록， 상기원기등과원뿔이점유하는공간을배제한곳에고정되는것을특징으로 한다ᅳ  The support (5000) is characterized in that it is fixed in a location where the space occupied by the cone and the cone so as not to interfere with the fixed cable control unit 240 is generated.
[202] 또한도 14(a)에서보듯이 케이블경유기 (500)는정렬기 (243)의회전축선상의 케이블경유기지지대 (5000)일측상단에위치하고,비행체와연결된  In addition, as shown in FIG. 14 (a), the cable router 500 is positioned at an upper side of the cable router support 5000 on the rotation axis of the alignmentr 243, and is connected to the vehicle.
케이블 (300)은케이블경유기 (500)를경유하여케이블조절부 (240)에연결된다.  The cable 300 is connected to the cable adjusting unit 240 via the cable passer 500.
[203] 또한도 14(a)에서보듯이케이블조절부 (240)의상단과정렬기회전축선상의 지지대의이동가이드 (544)간에소정의 이격거리를두어정렬기 (243)회전에 의해케이블꼬임이발생되지않고，드럼 (242)에케이블이풀림과감김이 원활하게되도록하는것이바람직하다.  In addition, as shown in FIG. 14 (a), the cable is twisted by the rotation of the sorter 243 by a predetermined distance between the moving guides 544 of the support on the rotation axis of the cable adjusting unit 240. It is desirable that the cable be unwound and wound smoothly on the drum 242 without being generated.
[204] 도 14(a)에서케이블경유기 (500)는케이블 (300)이동과비행체의위치에따른 케이블의연결방향에대하여케이블의마찰이최소화되도록도 14(b)에서 보듯이상기케이블경유기 (500)는케이블 (300)이동경로에접선방향으로 접촉면을제공하는회전체 (520)와상기회전체 (520)의회전축에수직한 ： 회전축을갖는회전부 (530)로구성된다.여기서상기회전부 (530)는베어링으로 구성하는것이바람직하다.  As shown in FIG. 14 (a), the cable router 500 has the cable router as shown in FIG. 14 (b) such that the friction of the cable is minimized with respect to the direction of connection of the cable according to the movement of the cable 300 and the position of the vehicle. 500 comprises a rotating body 520 which provides a contact surface in a tangential direction to the movement path of the cable 300 and a rotating part 530 having a rotating shaft perpendicular to the rotating shaft of the rotating body 520. Here, the rotating part 530 ) Is preferably a bearing.
[205] 여기서상기회전체 (520)는회전체지지대 (510)에의해지지되고，상기회전체 지지대 (510)는회전부 (530)의외륜에고정되고,상기회전부 (530)의내륜은 케이블경유기지지대 (5000)에연결된다.  Here, the rotating body 520 is supported by the rotating body support 510, the rotating body support 510 is fixed to the outer ring of the rotating part 530, the inner ring of the rotating part 530 is a cable carrier support (5000).
[206] 도 14(a)에서보듯아상기정렬기 (243)회전축선상의케이블경유기  As shown in FIG. 14 (a), a cable router on the axis of rotation of the above sorter 243 is shown.
지지대 (5000)는케이블 (300)을관통시켜구속시키는중공형태의파이프형상을 가진다.  The support 5000 has a hollow pipe shape through which the cable 300 is constrained.
[207] 그러나상기케이블경유기지지대 (5000)는다단식연결구조의착탈식으로 구성하는경우에는착탈을용이하기위해상기케이블 (300)은지지대 (5000)의 관통구멍에의해구속되지않는구조가바람직하다. However, when the cable carrier support (5000) is configured to be detachable in a multi-stage connection structure, the cable (300) is connected to the support (5000) in order to facilitate detachment and detachment. A structure that is not bound by the through holes is desirable.
[208] 도 14(a)에서보듯이정렬기 (243)의희전과케이블 (300)의이동시에케이블에 가해지는마찰력을최소화하기위하여,지지대이동가이드 (544)가정렬기 회전축선상의케이블경유기지지대 (5000)의 일측하단에부착되어 있다.  As shown in Fig. 14 (a), in order to minimize the friction of the sorter 243 and the frictional force applied to the cable during the movement of the cable 300, the support for moving the support 544 on the aligner axis of rotation (5000) It is attached to the lower end of one side.
[209] 또한도 14(c)에서보듯이지지대이동가이드 (544)는도 14(b)의케이블  [209] In addition, as shown in FIG. 14 (c), the support movement guide 544 includes the cable of FIG. 14 (b).
경유기 (500)와기능적으로같은구조를가지며，요구되는케이블의이동방향에 따라대웅되는회전체 (520)의부착위치 (각도)를다르게할수있다.  It has the same structure as the diesel engine 500, and the attachment position (angle) of the rotating body 520 to which it is based according to the movement direction of the cable requested | required can be different.
[210] 그리고도 14의고정식케이블조절부 (240)는,정렬기 (243)가고정되고  And fixed cable control unit 240 of Figure 14, the sorter 243 is fixed
드럼 (242)이회전하는구조의회전식케이블조절부로변경되어도,구조적으로 도 14의케이블경유기지지대 (5000)와케이블경유기 (500)는동일하게 적용된다.  Even if the drum 242 is changed to a rotary cable control unit having a structure in which the drum 242 rotates, the cable carrier support 5000 and the cable carrier 500 of FIG. 14 are applied in the same manner.
[211] 따라서도 14의지지대케이블경유방식은구조적으로고정식과회전식의 케이블조절부에모두적용할수있는장점을가진다.  Thus, the support cable route method shown in FIG. 14 has an advantage that it can be applied to both fixed and rotary cable control.
[212] 본발명의케이블경유기는회전체가상하로부착되는경우만예시하였으나 케이블의이동경로방향과장력의크기에따라회전체가좌우로더포함되어 부착될수있음은물론이다. The cable passer of the present invention is illustrated only when the rotating body is attached up and down, but the rotating body may be attached to the left and right according to the direction of the cable moving path and the size of the tension.
[213] 도 15는도 14의일실시예의사시도이다. 15 is a perspective view of one embodiment of FIG. 14.
[214] 상기지지대에의한케이블경유방식에서，도 14와도 15의케이블  [214] The cable of FIGS. 14 and 15 in the cable routing method by the support.
경유기 (500)와지지대이동가이드 (544)는케이블의이동과비행체의  The diesel engine 500 and the support movement guide 544 are used for moving the cable and
방향전환 (또는선회)시쎄케이블에작용하는마찰과꼬임을최소화시키는 기능을제공한다.  Provides the ability to minimize friction and twist on the cable when turning (or turning).
[215] 본발명의지지대케이블경유방식은상기도 12의예시에서 1개의지지대로 구성되어있어，수평이동거리가길어지는경우에는케이블의처짐이심해지고， 비행체에가해지는케이블의하중이증가한다.  The support cable route method of the present invention is composed of one support in the example of FIG. 12, and when the horizontal travel distance is increased, the cable sags and the load of the cable applied to the vehicle increases.
[216] 이를해소하기위해，도 12의지지대케이블경유방식에서증간지지대를 [216] In order to solve this problem, the incremental support can be removed by using the support cable of FIG.
추가적으로더포함시킬수있다.  In addition, you can include more.
[217] 도 16은중간지지대케이블경유방식의일실시예의개념도이다. FIG. 16 is a conceptual diagram of one embodiment of the intermediate support cable route method. FIG.
[218] 도 16(a)은중간지지대 (5000a)를포함하는지지대케이블경유방식의 16 (a) shows a method of via a support cable including an intermediate support (5000a).
개념도이고，도 16(b)는중간지지대 (5000a)에의해지상물 (2)과간섭이없도록 케이블 (300)의우희경로를제공하는개념도이다.  It is a conceptual diagram, and FIG. 16 (b) is a conceptual diagram which provides the right path of the cable 300 so that it may not interfere with the ground material 2 by the intermediate support 5000a.
[219] 도 16(a)에서보듯이케이블경유기 (500)를포함하는증간지지대 (5000a)는 As shown in FIG. 16 (a), an incremental support 5000a including a cable transiter 500 is provided.
케이블조절부에서최대수평이동거리까지의중간지점에설치되어  Installed at the intermediate point from the cable control section to the maximum horizontal travel distance
케이블 (300)이상기증간지지대 (5000a)의케이불경유기 (500a)를경유하게되고 이로인하여케이블처짐이줄어들어지상장애물 (2)과간섭없이최대수평이동 거리를증가시킬수있다. ：  The cable 300 is routed through the K-free tanker 500a of the incremental support 5000a, thereby reducing the cable sagging and increasing the maximum horizontal travel distance without interference with the ground obstacle 2. ：
[220] 또한케이블경유기 (500,500a)에의해비행체에가해지는케이블의하중도 [220] In addition, the load on the cable exerted on the vehicle by the cable transiter (500,500a)
감소된다.  Is reduced.
[221] 상기중간지지대 (5000a)는지상에고정하여설치할수도있고, 이동체 (예:차량)에설치할수있다.또한높이조절이가능하도록다단연결 구조가바람직하다. ' [221] The intermediate support (5000a) can be fixed on the ground, It can be installed on moving bodies (eg vehicles) and a multi-stage connection structure is preferred to allow height adjustment. '
[222] 도 16(a)의 예시에서상기중간지지대 (5000a)는한개로구성되어 있으나, 요구되는운용조건 (예:장애물위치，수평아동거리)에따라복수로구성될수 있다.  In the example of FIG. 16 (a), the intermediate support 5000a is configured as one, but may be configured in plural according to the required operating conditions (eg obstacle position, horizontal child distance).
[223] 여기서상기중간지지대의케이블경유기： (500a)는비행체가중간  [223] where the cable supporter of the intermediate support is 500a
지지대 (5000a)를넘어서는위치로수평이동을하는경우에케이블의경유 경로를제공할수있다.  The cable route can be provided for horizontal movement to a position beyond the support (5000a).
[224] 또한상기중간지지대를넘어서지않는영역에서비행체가자유롭게수직및 수평이동을위하여상기중간지지대의케이블경유기 (500a)를경유하지않는 것이바람직하다. In addition, it is preferable that the flying vehicle freely passes through the cable carrier 500a of the intermediate support for vertical and horizontal movement in an area not exceeding the intermediate support.
[225] 상기와같은기능을제공하기위해상기중간지지대 (5000a)에설치되는  It is installed on the intermediate support (5000a) to provide the function as described above.
케이블경유기 (500a)의구조는비행체의위치에따라케이블을경유시키거나 또는비경유가되도록구성한다.  The structure of the cable route 500a is configured to be routed or routed through the cable depending on the position of the vehicle.
[226] 따라서도 16(a)에서보는바와같이상기중간자지대의 케이블경유기 (500a)는 케이블을구속하지않고,케이블의경유경로를제공하도록케이블 Therefore, as shown in FIG. 16 (a), the cable router 500a of the middle magnetic field zone does not bind the cable and provides the cable route.
경유기 (500a)의일측면이개방되는구조를가지는것이바람직하다.  It is preferable to have a structure in which one side of the diesel engine 500a is opened.
[227] 도 16(b)에서보듯이다수의증간지지대 (5000a)와케이블경유기 (500a)는 As shown in FIG. 16 (b), a number of incremental supports 5000a and cable passers 500a are
다수의장애물 (2)을우회하는경로를제공하여비행체 (100)가장애물 (2)사이로 수평이동을할수있도록한다.  It provides a path to bypass a number of obstacles (2) so that the vehicle (100) can move horizontally between the obstacles (2).
[228] 이와같이,중간지지대를더포함하는지자대케이블경유방식은제한된 [228] In this way, it is restricted to include the intermediate support via the magnetic pole cable.
수직높이의지지대로저고도에서장애물과간섭없이긴수평이동거리와 장애물의우회 경로를제공한다.  The vertical height support provides long horizontal travel distances and bypass paths at low altitudes without obstacles and interference.
[229] 다수의중간지지대 (5000a)는별도의구조물을설치할수도있지만,기존에 설치되어있는구조물 (예를들면,가로등，전봇대，고층빌딩등)을이용하여，그 구조물을중간지지대로이용할수도있다. [229] Many of the intermediate supports 5000a may be provided with a separate structure, but the existing structures (for example, street lamps, power poles, high-rise buildings, etc.) may be used as intermediate supports. have.
[230] 도 17은중간지지대의케이블경유기일실시예이다. 17 shows an embodiment of a cable router of an intermediate support.
[231] 도 17(a)는중간지지대의케이블경유기실시예의정면도이고，도 17(b)는 FIG. 17 (a) is a front view of the cable router embodiment of the intermediate support, and FIG. 17 (b) is
사시도이다.  Perspective view.
[232] 도 17(a)에서중간지지대의 케이블경유기 (500a)는기본적으로케이블 (300)의 이동마찰을최소화시켜주는회전체 (를러)는하부회전체 (520_1)와좌우 회전체 (52으 2)가수직되게구성되고,상기케이블경유기 (500a)는지지대 연결부 (531)를통하여중간지지대 (5000a)에연결된다.  In FIG. 17 (a), the cable supporter 500a of the intermediate support basically has a lower rotating body 520_1 and a left and right rotating body 52 that minimize the moving friction of the cable 300. 2) is configured to be vertical, and the cable route 500a is connected to the intermediate support 5000a through the support connecting portion 531.
[233] 그리고도 17(a)에서보듯이중간지지대의케이블경유기 (500a)fe케이블  [233] And as shown in Figure 17 (a), the cable passer (500a) fe cable of the intermediate support
경유기의일측면상단이개방되어 있어케이블을구속하지않는구조로 구성되는것을특징으로한다.  It is characterized by the structure that does not bind the cable because the upper part of one side of the diesel engine is open.
[234] 따라서상기케이블경유기의 일측면상단이개방되어 있는구조로인하여 상기일측면상단방향으로비행체가케이블을하강시키면 (또는떨어뜨리면) 케이블은회전체 (520_1 ,520_2))에접촉하게되고,반대로비행체가케이블을 수직으로상승시키면 (또는들어올리면)상기케이블은회전체접촉에서 이격되어케이블경유기 (500a)를벗어날수있다. Therefore, when the plane descends (or drops) the cable toward the upper side in one direction due to the structure in which the upper end of one side of the cable passage is opened. The cable is brought into contact with the rotors 520_1, 520_2, and on the contrary, if the vehicle raises (or lifts) the cable vertically, the cable is spaced apart from the rotor contact and can exit the cable passer 500a.
[235] 또한요구되는운용환경에따라상기케이블을케이블경유기 (500a)에구속이 요구되는경우상기일측면을선택적으로개방구조와닫힌구조로구성하여 제어할수있다. In addition, when the cable is required to be connected to the cable passer 500a according to the required operating environment, the one side may be selectively configured to be controlled in an open structure and a closed structure.
[236] 또한케이블가이드 (51 1)는케아블가이드 (511)의폭 (너비)이내의위치에서 비행체가케이블을떨어뜨려도케이블이상기회전체 (520_1 ,520_2)에쉽게 접촉할수있도록해준다.  The cable guide 51 1 allows the cable to easily contact the rotors 520_1 and 520_2 even if the vehicle drops the cable within a width (width) of the cable guide 511.
[237] 또한，케이블경유기 (500a)의좌우회전체 (520_2)를포함하는면의수직방향은, 케이블을하강시켜회전체에접촉이원활하도록,도 16(a)에서보듯이케이블 조절부의케이블경유기 (500)와중간지지대의케이블경유기 (500a)를잇는직선 방향과동일하도록설치하는것이바람직하다. In addition, the vertical direction of the surface including the left and right rotating bodies 520_2 of the cable transiter 500a lowers the cables so that the contact with the rotating bodies is smooth, as shown in FIG. 16 (a). Preferably, the cable router 500 and the intermediate supporter cable router 500a are installed in the same straight direction.
[238] 도 18은비행체에의한케이블경유방식의실시예의개념도이다. 18 is a conceptual diagram of an embodiment of a cable via method by a flying body.
[239] 도 18(a)은비행체에의한지지대케이블경유방식의개념도이고，도 16(b)는 비행체의케이블경유기 (500)에의해케이블 (300)이들려서지상물 (2)의간섭이 없는상태의개념도이다. FIG. 18 (a) is a conceptual diagram of a support cable via a vehicle, and FIG. 16 (b) shows a cable 300 lifted by a cable carrier 500 of an aircraft, thereby causing interference of the ground object 2. It is a conceptual diagram of a state without.
[240] 도 12의지지대에의한케이블경유방식은케이블경유지지대가제공하는 높이로케이블의경유경로를제공하는반면에，도 18은비행체 (100b)가 케이블 (300)의경유경로를제공한다. In the cable passing method of the support of FIG. 12, the cable passing path provides a cable routing path at a height provided by the cable passing support, while FIG. 18 provides a route of the cable 300 by the flying body 100b.
[241] 케이블경유비행체 (100b)에는케이블경유기 (500)가설치되어 있어서，상기 비행체 (100b)가제공하는수직비행고도로케이블 (300)을위로 The cable transit vehicle 100b is provided with a cable transiter 500, so that the cable 300 is moved upward with the vertical flight altitude provided by the vehicle 100b.
들어주는 (받쳐주는)역할을하므로,케이블 (300)이지상의장애물 (2)에간섭되지 않는다.즉지상의장애물에걸리지않는다.  It does not interfere with the obstacles (2) on the cable (300), because it acts as a support (holding).
[242] 도 18(a)에서보듯이케이블조절부의케이블이비행체 2(100b)를경유하여  As shown in FIG. 18 (a), the cable of the cable adjusting unit passes through flight 2 (100b).
비행체 l(100a)에연결되는구조를가지므로,：비행체 2(100b)는케이블 (300)의 경유수직높이를가변적으로변경시킬수있는장점을갖는다.  Since it has a structure connected to the vehicle l (100a): The flight 2 (100b) has the advantage of changing the vertical height of the cable 300 via the variable.
[243] 반면에,비행체경유방식은독립적인케이블공급구조로인하여케이블의 경유경로를제공하는비행체 2(100b)는비행체 l(100a)의케이블하증를  [243] On the other hand, the flight via method is independent of the cable supply structure, so that flight 2 (100b) provides a cable routing through the cable l of the flight l (100a).
추가적으로부담해야하는단점을가진다.  It has additional disadvantages.
[244] 본발명의상기케이블경유기는비행체가수평이동시케이블하중의일정  [244] The cable transiter of the present invention schedules the cable load when the vehicle moves horizontally.
부분을떠받쳐주는역할을하므로,비행체에가해지는케이블하증을  As it supports the part, the cable lowering
감소시키는것을특징으로한다.  To reduce.
[245] 이것을다시설명하면，케이블경유기가제공하는수직높이로비행체가  [245] When this facility is re-named, the vehicle will be driven to the vertical height provided by the cable router.
수평이동을하면，총케이블중량이케이블경유기와비행체에균등하게 분배되어비행체에가해지는케이블하중이반으로감소하게되고，이로인하여 감소된하중에대웅되는케이블길이를더길게할수있어수평이동거리；를 증가시킬수있다. [246] 따라서，본발명의상기케이블경유기는수평이동시에지상물과케이블간의 간섭방지는물론이고，비행체에가해지는케이블하중을감소시켜수평이동 거리를증가시켜주는효과를제공한다. With horizontal movement, the total cable weight is distributed evenly between the cable passers and the vehicle, reducing the cable load on the vehicle by half, thereby increasing the length of the cable, which reduces the load to the horizontal. Can be increased. Therefore, the cable router of the present invention provides the effect of increasing the horizontal travel distance by reducing the cable load on the plane as well as preventing the interference between the ground and the cable during the horizontal movement.
[247] 도 19은비행체경유방식의케이블경유기실시예이다.  FIG. 19 shows an embodiment of a cable router using a vehicle route route.
[248] 도 13의회전식케이블조절부에설치되는케이블경유기는비행체경유방식에 적용되는케이블경유기와구조적으로동일하다.  The cable route installed in the rotary cable control unit of FIG. 13 is structurally identical to the cable route applied to the vehicle route route.
[249] 그러므로도 19에예시된케이블경유기는도 13의케이블경유기로적용될수 있다. Therefore, the cable duct shown in FIG. 19 can be applied to the cable duct shown in FIG.
[250] 도 19(a)의케이블경유기 (500)는단순한링형태의 링부 (501)와연결부 (502)를 포함하고，케이블 (300)이상기링부 (501)를통과하도록할수있다.상기 링부 (501)는연결부 (502)에결합되고연결부 (502)는케이블경유비행체 (400)의 하부몸체에설치된다.그러나링부 (501)와연결부 (502)만으로케이블경유기를 만들면,케이블경유기의구성이단순하다는장점이 있으나케이블 (300)이 이동할경우링부 (501)과케이블 (300)사이에강한마찰력과장력이작용하여 전송케이블 (300)이손상될수있는문제점아있다ᅳ  The cable router 500 of FIG. 19 (a) includes a ring portion 501 and a connection portion 502 having a simple ring shape, and allows the cable 300 to pass through the ring portion 501. 501 is coupled to the connecting portion 502 and the connecting portion 502 is installed on the lower body of the cable passing vehicle 400. However, if only the ring portion 501 and the connecting portion 502 make the cable route, the configuration of the cable route This has the advantage of simplicity, but there is a problem that if the cable 300 is moved, the strong frictional force and tension between the ring part 501 and the cable 300 act to damage the transmission cable 300.
[251] 따라서，상기케이블 (300)이통과하는링부 (501)에를러또는베어링 (504) (일부분만표시)포함하여케이블 (300)의이동마찰력을최소화할수있다.  Therefore, the frictional force of the cable 300 can be minimized by including the bearing portion 501 (only a part) to the ring portion 501 through which the cable 300 passes.
[252] 또한，케이블의상하위치에따른케이블 (300)과케이블경유기 (500)의  [252] In addition, the cable 300 and the cable passer 500
상호간에작용하는웅력을최소화하기위해회전부 (503)을더포함할수있다.  The rotary part 503 may be further included to minimize the forces acting on each other.
[253] 도 19(b)의케이블경유기 (500)는회전체지지대 (510)， 2개의회전체 (520)를 포함한다.회전체지지대 (510)는상기케이블경유기 (500)가설치된전송케이블 경유비행체 (100b)의하부몸체 (100b_l)의표면의수직방향을축방향으로하여 자유롭게회전을할수있도록설치된다.  The cable passer 500 of FIG. 19 (b) includes a rotor support 510 and two rotors 520. The rotor support 510 is a transmission in which the cable carrier 500 is installed. The vertical direction of the surface of the lower body 100b_l of the cable-flying body 100b is provided in the axial direction so as to be freely rotated.
[254] 또회전체지지대 (510)는 2개의회전체 (520)와결합하는데，상기 2개의  In addition, the rotor support 510 is coupled to the two rotors 520, the two
회전체의회전을허용하는구조로결합된다.  Combined in a structure that allows rotation of the rotor.
[255] 또한전송케이블 (300)은상기 2개의회전체사이를통과하도록하고,상기In addition, the transmission cable 300 to pass between the two rotating bodies, and
2개의회전체의테두리에는홈이형성되어 있어서，상기전송케이블 (300)이 상기 2개의회전체사이를벗어나지않도록한다. Grooves are formed at the edges of the two rotating bodies so that the transmission cable 300 does not come off between the two rotating bodies.
[256] 또한도 19(b)의구조는상기케이블 (300)이상기케이블경유기 (500)를통과할 때마찰력이최소화되도록，케이블이동경로에접선방향의접촉면을제공하는 회전체와상기회전체의회전축에수직하는회전축을제공하는것을특징으로 한다. In addition, the structure of FIG. 19 (b) has a rotating body and the rotating body providing a tangential contact surface to the cable movement path so that the frictional force is minimized when the cable 300 passes through the cable router 500. It is characterized by providing a rotation axis perpendicular to the rotation axis of the motor.
[257] 상기케이블경유기는케이블에가해지는장력과케아블의내구성에따라  The cable router depends on the tension applied to the cable and the durability of the cable.
다양한형상과구조로구현될수있음은물론이다.  Of course, it can be implemented in various shapes and structures.
[258] 도 20은다수의비행체에케이블이직렬로면결되는데이지체인구성방식을 보여준다. 20 shows a method of configuring an easy chain, in which cables are connected in series to a plurality of vehicles.
[259] 도 20은다수의비행체 (100a~100n)가케이블 (300)에의해연속적으로직렬로 연결되는"데이지체인 (Daisy chain) "구성방식를보여준다. [260] 따라서상기 데이지체인 (Daisy chain)구성방식은총케이블길이의중량을 다수의비행체들이나누어분담하므로써，수직비행고도를최대로구현할수 있는장점을가지는구조이다. FIG. 20 shows a configuration of a "daisies chain" in which a plurality of flying bodies 100a to 100n are continuously connected in series by a cable 300. FIG. Accordingly, the daisy chain configuration has an advantage of maximizing vertical flight altitude by dividing the weight of the total cable length by a plurality of airplanes.
[261] 도 20(b)에서비행체 l(100a)의위치와비행체 2(100b)의위치가상호연동되게 제어되면，비행체 1과버행체 2는지상의장애물과간섭되지않으면서요구되는 비행위치 (수직고도,수평거리)로이동할수있다. In FIG. 20 (b), when the position of the flight l (100a) and the position of the flight 2 (100b) are controlled to be interlocked, the required flight position without interfering with the obstacle on the flight 1 and the flight 2 (vertical) Altitude, horizontal distance).
[262] 최하단에위치하는상기비행체 l(100a)의케이블 (300)은지상에위치하는 The cable 300 of the vehicle l (100a), which is located at the bottom, is located on the ground.
케이블조절부 (240)에의해길이와장력이조절된다.  The length and tension are adjusted by the cable adjuster 240.
[263] 또한상기비행체 l(100a)에서분기되어비행체 2(100b)에연결되는 In addition, branched from the flight l (100a) is connected to the flight 2 (100b)
케이블 (300)은비행체 l(100a)에케이블조절부 (240)가더포함되어，  The cable 300 further includes a cable control unit 240 in the airplane l (100a),
비행체 2(100b)에연결되는케이블 (300)길이와장력을조절하도록할수있으나， 비행체 l(100a)의부하증가를최소화하기위하여케이블조절부를생략하여 비행체 2의께이블길이가고정되도록할수도있다ᅳ  The length and tension of the cable 300 connected to the aircraft 2 (100b) may be adjusted, but the cable length of the aircraft 2 may be fixed by omitting the cable control unit to minimize the increase in load of the aircraft l (100a). ᅳ
[264] 또한장력감지기는케이블조절부의케이블이동경로에설치되거나또는, 케이블에병렬로설치되어케이블의장력을감지할수있다. In addition, the tension sensor can detect the tension of the cable is installed in the cable path of the cable control unit or in parallel to the cable.
[265] 상기비행체 1에연결된케이블 (300)은케이블조절부 (240)에서장력을감지할 수있으나，상기비행체 2는케이블에병렬로연결된장력감지기 (999)에의해 장력을감지하는것이바람직하다. The cable 300 connected to the flight body 1 can sense the tension in the cable control unit 240, but the flight body 2 preferably senses the tension by the tension sensor 999 connected in parallel with the cable. .
[266] 도 20의유선비행체에너지공급시스템에대해다시정리하면，비행체는 [266] When the wired vehicle energy supply system of FIG. 20 is rearranged, the vehicle is
제 1비행체를포함하는복수의비행체를포함하고,케이블은제 1비행체를 경유하여나머지비행체들에직렬로연결되고,상기복수의비행체는상기 . 케이블로부터에너지를공급받으며，상기복수의비행체를연결하는케이블은 길아가고정되어 있다.또한，상가비행체에는상기케이블의장력을감지하는 장력감지기가설치되어 있다.  A plurality of flying vehicles comprising a first flying vehicle, the cable being connected in series with the remaining flying vehicles via the first flying vehicle, wherein the plurality of flying vehicles comprises:. The cable is supplied with energy from the cable, and the cable connecting the plurality of airplanes is fixed to be long. Further, the commercial vehicle is provided with a tension sensor that senses the tension of the cable.
[267] 도 21은케이블에병렬로설치되는스프링식장력감지기의실시예이다. 21 is an embodiment of a spring tension sensor installed in parallel with a cable.
[268] 스프링식장력감지기는케이블 (300)에 병렬로탄성체 (예:스프링)를연결하여 케이블장력에따른탄성체 (999_1)변위를측정하여장력을감지하는구조이다. The spring-type tension sensor is a structure that senses the tension by measuring the displacement of the elastic body (999_1) according to the cable tension by connecting the elastic body (for example, a spring) in parallel to the cable (300).
[269] 도 21에서탄성체 (999_1)의변위에따라슬라이더가 (999_2)이동하면 In FIG. 21, when the slider moves (999_2) according to the displacement of the elastic body (999_1).
저항 (999_3)이변하게되는테，상기저항값을측정하여장력을감지한다ᅳ  As the resistance 999_3 changes, the tension value is measured to detect the tension.
[270] 상기장력감지기에병렬로연결되는케이블 (300)의길이는케이블파손을막기 위해도 21에서와같이탄성체 (999_1)의최대변위보다길다. The length of the cable 300 connected in parallel to the tension sensor is longer than the maximum displacement of the elastic body 999_1 as in FIG. 21 to prevent cable breakage.
[271] 도 22는사각지대의시야확보를위한데이지체인의연결구성도이다. FIG. 22 is a connection diagram of a daisy chain for securing a field of view of a blind spot.
[272] 도 22에서같이비행체 l(100a)은장애물 (2)보다높게위치하고 As shown in FIG. 22, the vehicle l (100a) is positioned higher than the obstacle (2).
비행체 2(100b)는장애물 (2)보다낮게위치하면，비행체 l(00a)은높은시야를 확보할수있고,비행체 2(100b)는장애물 (2)에의해가려져 있는사각지대의낮은 시야를확보할수있다.  If aircraft 2 (100b) is positioned lower than obstacle (2), vehicle l (00a) can secure a higher field of view, and aircraft 2 (100b) can secure a low field of view obscured by the obstacle (2). have.
[273] 본발명의실시예에서 "데이지체인 (Daisy chain)"구성의비행체를 [273] In the embodiment of the present invention, the "Daisy chain" configuration of the aircraft
비행체 l(100a)과비행체 2(100b)의두대로한정하여설명하였지만，다수의 비행체에도똑같이적용할수있음은물론이다. Although two aircraft, l (100a) and 2 (100b), were described as limited, Of course, the same applies to the aircraft.
[274] 또한본발명의 "데이지체인 (Daisy chain)"으로구성되는유선비행체에너지 공급시스템은，비행체에연결되는총케이블무게가다수의비행체에분산되는 구조로인하여，최고비행고도를극대화할수있는구조를제공한다. [274] The wired flight energy supply system, which consists of the "Daisy chain" of the present invention, has the structure that maximizes the highest flight altitude, because the total cable weight connected to the flight is distributed to a large number of vehicles. To provide.
[275] 또한다수의비행체위치좌표가적절하조합되면,지상의장애물간섭을 [275] In addition, when many vehicle position coordinates are combined properly,
배제하면서유선비행체에요구되는수직고도와수평이동 (비행)을제공하는 것을특징으로한다.  It is characterized by providing the vertical altitude and horizontal movement (flight) required for wired aircraft while excluding it.
[276] 이러한임의의수직고도와수평이동 (비행)을제공하는데이지 체인방식의 유선비행체는고고도의수평이동뿐만아니라，저고도의수평이동이요구되는 분야에다양한활용이가능하다.  [276] This arbitrary vertical altitude and horizontal movement (flight) is provided, and the chain-chain wired aircraft can be used in various fields that require not only high altitude horizontal movement but also low altitude horizontal movement.
[277] 한편비행체가회전하면케이블꼬임이발생되는데,다수의비행체가직렬로 구성되는테이지체인방식에서는매우심각하다， [277] On the other hand, when the airplane rotates, cable twist occurs, which is very serious in the case of a tape chain system in which a large number of vehicles are arranged in series.
[278] 따라서데이지체인 (Daisy chain)방식으로연결되는다수의비행체가 [278] Therefore, a number of airplanes connected by a daisy chain method
독립적으로회전하더라도，상호케이블꼬임이발생하지않는케이블꼬임방지 장치가요구된다.  Cable twist protection, which does not cause cross cable twisting, is required even when rotating independently.
[279] 본발명에서 데이지체인방식으로구성되는，유선비행체의에너지공급  [279] In the present invention, the supply of energy for wired aircraft, which is configured in a daisy chain manner.
시스템은,고공정체비행시에는최대비행고도를제공하고，수평이동시에는 지상장애물과간섭없이최대수평이동을제공하는것을특징으로한다.  The system is characterized by providing maximum flight altitude for high-floor flight and maximum horizontal movement without horizontal interference with horizontal obstacles.
[280] 또한본발명에서케이블경유기를사용하는케이블경유방식과데이지체인 방식의유선비행체에너지공급시스템은케이블이지상물과간섭없이저고도 수평비행 (이동)을제공한다.  In addition, in the present invention, the cable transit system using cable transiters and the wired chain energy supply system of the daisy chain method provide low altitude horizontal flight (movement) without interference with the cable ground.
[281] 따라서저고도수평비행아요구되는다양한분야 (예：농업용방제,방송용  [281] Therefore, various areas requiring low altitude flight (eg agricultural control, broadcasting)
촬영，군사용지뢰탐지등)에본발명의유선비행체에너지공급시스템이 적용될수있다.  Wired energy supply systems of the present invention may be applied to shooting, military mine detection, etc.).
[282] 또한본발명의유선비행체에너지공급시스템은저고도수평비행의다양한 임무 (예:농약살포，비료공급등)수행을위한유체전송케이블을더구비하는 것을특징으로한다.  [282] The wired flight energy supply system of the present invention is further characterized by the provision of a fluid transmission cable for the performance of a variety of low-altitude horizontal flights (eg pesticide spraying, fertilizer supply, etc.).
[283] 또한상기다양한임무를수행하기위한임무장비 (예:유체살포기，카메라, 지뢰탐지기등)를비행체에더포함하여탑재할수있음은물론이다.  It is, of course, possible to include in the aircraft additional mission equipment (eg, fluid sprayers, cameras, mine detectors, etc.) to carry out these various missions.
[284] 한편비행체가회전및선회비행으로인하여비행체자세가변경되면  [284] On the other hand, if the flight posture changes due to the turning and turning flight,
비행체에고정되어 있는케이블은꼬임현상이발생되어，케이블이손상을받을 수있다.  Cables fixed to the aircraft can be twisted, which can damage the cables.
[285] 이러한문제점을방지하가위해，종래에는꼬임을감지하여꼬임의  [285] To prevent this problem, conventionally, the kink is detected to
반대방향으로비행체를희전시키는방식을해결했으나，이러한방식은  We solved the way of flying the plane in the opposite direction, but this
비행체의자세변경을초래하는문제점이 있다.  There is a problem that causes a change in the attitude of the aircraft.
[286] 이러한경우케이블 (300)이비행체와독립적으로회전하는구조를가지면된다.  In this case, the cable 300 may be configured to rotate independently of the vehicle.
[287] 즉,상기연료전지와비행체가상호독립적인회전구조를갖도록연료전지의 회전연결부는비행체몸체와연료전지를기계적으로연결하는베어링과 연료전지출력를전기적으로연결하는슬립링으로구성하면,케이블꼬임을 방지할수있다. That is, the rotary connection portion of the fuel cell has a bearing for mechanically connecting the flying vehicle body and the fuel cell such that the fuel cell and the flying vehicle have a mutually independent rotating structure. A slip ring that electrically connects the fuel cell output can prevent cable twisting.
[288] 상기슬립링은회전부와고정부간에연결되는전기케이블을꼬임없이전기를 전달해주는기능을제공한다. ：  The slip ring provides a function of transferring electricity without twisting an electrical cable connected between the rotating part and the fixing part. ：
[289] 도 23은슬립링유닛의실시예이다. 23 shows an embodiment of a slip ring unit.
[290] 도 23에서회전부케이블 (115_4)과연결되어 있는 3개의슬립링 (115_1)이  In FIG. 23, three slip rings 115_1 connected to the rotary part cable 115_4 are provided.
3개의브러쉬 (115_2)에접촉하고있으면， 3가닥의회전부케이블 (115_4)과 슬립링 (115_1)이회전하더라도 3개의슬립링과 3개의브러쉬 (115_2)의접촉은 유지되므로， 3가닥의회전부케이블 (115_4)은슬립링 (1 15_1)을통하여 3가닥의 고정부케이블 (115_6)과전기적연결은유지될수있다.  When the three brushes 115_2 are in contact with each other, the three slip rings and three brushes 115_2 are kept in contact with each other even if the three-turn cable 115_4 and the slip ring 115_1 rotate. 115_4 can maintain the electrical connection with the three-strand cable 115_6 via the slip ring 1 15_1.
[291] 여기서,최대허용되는케이블가닥수는슬립링 (115_1)의개수로정해지므로 요구되는케이블가닥수만큼슬립링 (115_1)개수를구성하면된다;  Here, the maximum allowable number of cable strands is determined by the number of slip rings 115_1, so the number of slip rings 115_1 may be configured as many as the required number of cable strands;
[292] 도 24는연료전지와비행체가상호독립적인회전구조를갖도록하여케이블 꼬임방지을위한실시예 1의구성도이다.  24 is a configuration diagram of Embodiment 1 for preventing cable twist by allowing the fuel cell and the flying vehicle to have mutually independent rotating structures.
[293] 도 24에서는전송케이블 (300a)에연결된연료전지 (110)는회전부 (116)수단의 내륜 (116_2,내측회전체)에연결하고,비행체몸체 (100_1)는회전부 (1 16)수단의 외륜 (116_1，외측회전체)에연결하여비행체몸체 (10으 1)와연료전지 (1 10)가 독립적으로자유회전할수있는구조로만들어,상기슬립링유닛 (115)을 이용하여연료전지 (110)와배터리 (120)의전기적연결을유지한다.따라서 비행체 (100)가회전및선회하거나연료전지 (110)가회전하더라도  In FIG. 24, the fuel cell 110 connected to the transmission cable 300a is connected to the inner ring 116_2 (inner rotating body) of the rotating unit 116, and the flying vehicle body 100_1 is connected to the rotating unit 1 16 of the rotating unit 116. Connected to the outer ring (116_1, the outer rotating body) to make the structure of the flying vehicle body (10 1) and the fuel cell (10) independently freely, the fuel cell 110 using the slip ring unit 115 And maintain electrical connection of the battery 120. Thus, even if the vehicle 100 rotates and turns or the fuel cell 110 rotates,
배터리 (120)와의전기적연결은케이블꼬임없아유지된다.  The electrical connection with the battery 120 is maintained without cable twist.
[294] 도 24에서상기연료전지의출력단자 (111)는슬립링유닛의고정부단자와 연결되어한몸체로회전하는구조이고，상기슬립링유닛의회전부  In FIG. 24, the output terminal 111 of the fuel cell is connected to the fixing terminal of the slip ring unit to rotate in one body, and the rotary part of the slip ring unit is rotated.
케이블 (112)은비행체몸체 (100_1)에고정되는비행체전기기기 (130)의 전력변환기 (140)에연결되는구조이다. :  The cable 112 is a structure that is connected to the power converter 140 of the flight electric device 130 is fixed to the flight body (100_1). :
[295] 따라서상기케이블꼬임방지장치는상기연료전지 (110)와비행체 (100)가 상호독립적인회전구조를갖도록,연료전지의회전연결부는비행체 (100)와 연료전지 (110)를기계적으로연결하는회전부 (116)와，전력변환기 (140)와 연료전지출력를전기적으로연결하는슬립링유닛 (115)으로구성하여，케이블 꼬임을방지한다.  Therefore, the cable twist prevention device is such that the fuel cell 110 and the flying vehicle 100 have a mutually independent rotation structure, the rotary connection portion of the fuel cell mechanically connects the flying body 100 and the fuel cell 110. It consists of a rotating unit 116, and a slip ring unit 115 for electrically connecting the power converter 140 and the fuel cell output, to prevent the cable twist.
[296] 도 25는케이블꼬임방지실시예 2의구성도이다.  25 is a configuration diagram of cable twist prevention Example 2;
[297] 도 25에서보듯이전송케이블 (300a)는로터리조인트 (118)를통해  As shown in FIG. 25, the transmission cable 300a is connected via a rotary joint 118.
연료전지 (1 10)에연결된다.  Is connected to the fuel cell 1 10.
[298] 일반적으로널리사용되는로터리조인트는회전부와고정부간에  [298] A commonly used rotary joint is used between the rotary part and the fixed part.
유체 (예:공기,액체，가스등)매질을전달하는기능을제공한다.따라서전송 케이블 (300a)을로터리조인트 (1 18)를통하여연료전지 (110)에연결하는경우，도 23의슬립링은사용하지않고，연료전지 (110)는회전하지않는구조로구성할수 있다ᅳ [299] 특히，수소가스를전달매체로하는로터리조인트는안전성을위해수소가스 누설에대한엄격한기밀성이보장되어야한다는단점이있는반면，슬립링은 전기를전달매체로하므로 (가스누출에대한)안전성이보장되는장점을 가진다. 23 provides the ability to transfer fluid (eg air, liquid, gas, etc.) media. Thus, when the transmission cable 300a is connected to the fuel cell 110 via a rotary joint 1 18, the slip ring of FIG. Is not used, the fuel cell 110 can be configured in a non-rotating structure. [299] In particular, rotary joints, which use hydrogen gas as a delivery medium, have the disadvantage of ensuring strict confidentiality against hydrogen gas leakage for safety purposes, while slip rings are used as a carrier medium for safety. This has the advantage of being guaranteed.
[300] 도 26은슬립링을사용하여케이블꼬임방지을위한실시예 3의구성도이다.  FIG. 26 is a configuration diagram of Embodiment 3 for preventing cable twist using a slip ring.
[301] 유선비행체 (100)에 전력케이블 (300b)을통하여 전력공급을하는경우에는，도In the case of supplying power to the wired aircraft 100 through the power cable 300b, FIG.
24에서와같이슬립링유닛 (115)에직접전력케이블 (300b)이연결되는구조로 구성된다. As in 24, the power cable 300b is directly connected to the slip ring unit 115.

Claims

청구범위 Claim
[청구항 1] 연료전지와비행체전기기기를포함하는비행체；  Claim 1 A flying vehicle comprising a fuel cell and a flying electric machine;
비행체의외부에위치하는연료전지연료공급장치;  A fuel cell fuel supply device located outside of the vehicle;
상기비행체와상기연료전지연료공급장치를연결하는전송케이블; 을포함하고,  A transmission cable connecting the flying vehicle and the fuel cell fuel supply device; Including,
상기전송케이블은연료전지연료를전송하는연료전송통로를 포함하고,  The transmission cable includes a fuel transmission passage for transmitting fuel cell fuel,
상기연료전지는상기연료전송통로를통해연료전지연료를공급받아 전기를생산한；후상기비행체전기기기에공급하는것을특징으로하는 유선비행체에너지공급시스템.  The fuel cell is supplied with the fuel cell fuel through the fuel transmission passage to produce electricity; wired airplane energy supply system, characterized in that for supplying to the flying vehicle electrical equipment.
[청구항 2] 청구항 1에 있어서，  Claim 2 The method according to claim 1,
상기연료전지연료는수소인것을특징으로하는유선비행체에너지 공급시스템.  A wired vehicle energy supply system, wherein the fuel cell fuel is hydrogen.
[청구항 3] 청구항 1에 있어서，  Claim 3 The method according to claim 1,
상기전송케이블은 1가닥의류브에다중전송통로를갖는전송 케이블인것을특징으로하는유선비행체에너지공급시스템.  The transmission cable energy supply system, characterized in that the transmission cable is a transmission cable having multiple transmission passages on a single strand of a rib.
[청구항 4] 청구항 1에 있어서， Claim 4 The method according to claim 1,
상기전송케이블의연료전송통로내부에광섬유통신선이관통하는 것을특징으로하는유선비행체에너지공급시스템.  A wired airplane energy supply system, characterized in that an optical fiber communication line passes through a fuel transmission path of the transmission cable.
[청구항 5] 청구항 4에있어서，  [Claim 5] In Claim 4,
상기광섬유통신선은연료전송튜브를외피로하는것을특징으로하는 유선비행체에너지공급시스템.  The fiber optic communication line is wired airplane energy supply system, characterized in that the outer shell of the fuel transmission tube.
[청구항 6] 청구항 1에 있어서,  Claim 6 The method according to claim 1,
상기전송케이블의연료전송통로내부를고강도중심선이관통하는 것을특징으로하는유선비행체에너지공급시스템.  A wired airplane energy supply system, characterized in that a high-strength center line passes through a fuel transmission path of the transmission cable.
[청구항 7] 청구항 1에 있어서，  Claim 7 The method according to claim 1,
상기비행체는상기연료전지에서생산한전기를저장할수있는 배터리를포함하는것을특징으로하는유선비행체에너지공급시스템. The flying vehicle energy supply system, characterized in that it comprises a battery capable of storing the electricity produced by the fuel cell.
[청구항 8] 청구항 1에 있어서， Claim 8 The method according to claim 1,
상기전송케이블은상기연료전지에연결되어고정되고， 상기연료전지와상기비행체가복립적으로회전할수있도록기계적 연결을제공하는회전부와연료전지에연결된슬립링으로구성되는 케이블꼬임방지장치를포함하여，상기케이블의꼬임을유발시키는 회전모멘트가발생되면상기연료전지와비행체몸체간의상대 회전운동으로상기케이블의꼬임이해소되는것을특징으로하는유선 비행체에너지공급시스템.  The transmission cable includes a cable twist prevention device comprising a rotary part fixed to the fuel cell, the rotating part providing a mechanical connection for rotating the fuel cell and the vehicle, and a slip ring connected to the fuel cell. Wireline energy supply system, characterized in that the twist of the cable is eliminated by the relative rotational movement between the fuel cell and the vehicle body when the rotation moment causing the twist of the cable is generated.
[청구항 9] 청구항 1에 있어서， 상기연료전지연료공급장치는수소를발생시키는수소발생부를 [Claim 9] The method according to claim 1, The fuel cell fuel supply unit includes a hydrogen generator that generates hydrogen
포함하는것을특징으로하는유선비행체에너지공급시스템.  Wired aircraft energy supply system characterized by including.
[청구항 10] 청구항 1에 있어서, Claim 10 The method according to claim 1,
상기연료전지연료공급장치는상기케이블의장력및길이를조절하는 케이블조절부를포함하는것을특징으로하는유선비행체에너지공급 시스템.  And the fuel cell fuel supply device includes a cable control unit for adjusting the tension and length of the cable.
[청구항 11] 청구항 1에있어서，  [Claim 11] In Claim 1,
상기비행체에연결되는전송케이블은로터리조인트를통하여 연결되는것을특징으로하는유선비행체에너지공급시스템.  And a transmission cable connected to the vehicle, wherein the transmission cable is connected through a rotary joint.
[청구항 12] 청구항 1에있어서，  [Claim 12] In claim 1,
상기연료전지연료공급장치는공급하는수소의양또는압력을제어할 수있는공급제어부를더포함하는것을특징으로하는유선비행체 에너지공급시스템.  The fuel cell fuel supply apparatus further comprises a supply control unit capable of controlling the amount or pressure of hydrogen to be supplied.
[청구항 13] 청구항 12항에 있어서，  Claim 13 The method of claim 12,
상기연료전지의최대출력전력제어는상기공급제어부에서수소 공급량을조절함으로써수행되는것을특징으로하는유선비행체 에너지공급시스템.  Wireline energy supply system, characterized in that the maximum output power control of the fuel cell is performed by adjusting the hydrogen supply amount in the supply control unit.
[청구항 14] 유선으로전력을공급하는비행체;  [Claim 14] A flying vehicle that supplies power by wire;
비행체의외부에위치하는전력공급시스템;  A power supply system located outside of the vehicle;
상기비행체와상기전력공급시스템를연결하는전력케이블;  A power cable connecting the flying vehicle and the power supply system;
을포함하고，  Including,
상기비행체는슬립링을포함하고，  The vehicle comprises a slip ring,
상기전력케이블은상기슬립링을통하여연결되는것을특징으로하는 유선비행체에너지공급시스템.  And said power cable is connected via said slip ring.
[청구항 15] 내연기관와비행체전기기기를포함하는비행체； Claim 15 A flying vehicle comprising an internal combustion engine and flying electrical equipment;
비행체의외부에위치하는내연기관연료공급장치 ;  An internal combustion engine fuel supply device located outside of the vehicle;
상기비행체와상기내연기관연료공급장치를연결하는전송케이블; 을포함하고,  A transmission cable connecting the flying vehicle and the internal combustion engine fuel supply device; Including,
상기케이블은내연기관연료를전송하는연료전송통로를포함하고， 상기내연기관은상기연료전송통로를통해내연기관연료를공급받아 비행체의회전동력을발생시키고,상기발생된회전동력에의해전기를 생산한후상기비행체전기기기에공급하는것을특징으로하는유선 비행체에너지공급시스템.  The cable includes a fuel transmission passage for transmitting the internal combustion engine fuel, wherein the internal combustion engine receives the internal combustion fuel through the fuel transmission passage to generate rotational power of the vehicle, and generates electricity by the generated rotational power. And a wired vehicle energy supply system characterized by supplying the flying vehicle electrical equipment.
[청구항 16] 청구항 1,청구항 14，청구항 15중어느하나의청구항에 있어서，  [Claim 16] The method according to any one of claims 1, 14 and 15,
임무용유체를공급하기위한임무용유체공급부와상기임무용유체를 전송하기위한유체전송케이블을추가적으로더포함하는것을 특징으로하는유선비행체에너지공급시스템ᅳ  A wired vehicle energy supply system further comprising a mission fluid supply for supplying a mission fluid and a fluid transmission cable for transporting said mission fluid.
[청구항 17] 청구항 1,청구항 14，청구항 15중어느하나의청구항에 있어서, 상기비행체는제 1비행체를포함하는복수의비행체를포함하고， [Claim 17] The method according to any one of claims 1, 14 and 15, The flying vehicle includes a plurality of flying vehicles including a first flying vehicle,
상기케이블은계 1비행체를경유하여나머지비행체들에직렬로 연결되고,  The cable is connected in series with the rest of the vehicles via system 1,
상기복수의비행체는상기케아블로부터에너지를공급받으며， 상기복수의비행체를연결하는케이블은길이가고정된것을특징으로 하는유선비행체에너지공급시스템.  The plurality of flying vehicles are supplied with energy from the cable, and the cable connecting the plurality of flying bodies is characterized in that the length is fixed.
[청구항 18] 청구항 17에 있어서，  Claim 18 The method of claim 17,
상기비행체에는상기케이블의장력을감지하는장력감지기가설치되는 것을특징으로하는유선비행체:에너지공급시스템.  A wired vehicle: an energy supply system, characterized in that the vehicle is provided with a tension sensor for sensing the tension of the cable.
[청구항 19] 청구항 1，청구항 14,청구항 15중어느하나의청구항에 있어서, [Claim 19] The method according to any one of claims 1, 14 and 15,
상기케이블은통신신호를전송할수있는통신선을포함하는것을 특징으로하는유선비행체에너지공급시스템.  Wherein said cable comprises a communication line capable of transmitting a communication signal.
[청구항 20] 청구항 1,청구항 14,청구항 15중어느하나의청구항에 있어서， [Claim 20] The method according to any one of claims 1, 14 and 15,
상기케이블의장력및길이를조절하는케이블조절부를포함하는것을 특징으로하는유선비행체에너지공급시스템.  Wireline energy supply system, characterized in that it comprises a cable control unit for adjusting the tension and length of the cable.
[청구항 21] 청구항 20에 있어서, According to [Claim 21] of claim 20,
상기케이블조절부는  The cable control unit
케이블의감김과풀림을수행하는드럼;  A drum that performs the winding and unwinding of the cable;
상기드럼의증심축으로 360도희전하는정렬기;  A sorter that rotates 360 degrees with the amplification axis of the drum;
상기정렬기를구동하는모터구동부;  A motor driver for driving the sorter;
상기케이블의이동경로를제공해주는이동가이드;  A movement guide providing a movement path of the cable;
를포함하여상기정렬기가회전하여상기드럼에케이블을감거나푸는 것을특징으로하는유선비행체에너지공급시스템.  Wireline energy supply system, characterized in that for rotating the sorter, including winding the cable to the drum.
[청구항 22] 청구항 20에 있어서, Claim 22: The method of claim 20,
상기케이블조절부는  The cable control unit
케이블의감김과풀림을수행하는드럼;  A drum that performs the winding and unwinding of the cable;
상기드럼을구동하는모터구동부;  A motor driving part for driving the drum;
상기케이블의이동경로를제공해주는이동가이드;  A movement guide providing a movement path of the cable;
를포함하여상기드럼이회전하여상기드럼에케이블을감거나푸는 것을특징으로하는유선비행체에너지공급시스템.  Wireline energy supply system, characterized in that the drum is rotated, including the winding or unwinding cable to the drum.
[청구항 23] 청구항 20에 있어서, Claim 23 The method of claim 20,
상기케이블조절부는  The cable control unit
케이블의감김과풀림을수행하는드럼;  A drum that performs the winding and unwinding of the cable;
상기드럼을구동하는모터구동부;  A motor driving part for driving the drum;
상기케이블의이동경로를제공해주는이동가이드;  A movement guide providing a movement path of the cable;
상기드럼의회전축으로 360도회전하는정렬기;  A sorter which rotates 360 degrees with the rotation axis of the drum;
상기드럼과정렬기의위치를감지하는위치센서;  A position sensor for detecting a position of the drum processor;
를포함하는것을특징으로하는유선비행체에너지공급시스템. [청구항 24] 청구항 23에 있어서, A wired aircraft energy supply system, characterized in that it comprises a. Claim 24 The method of claim 23,
상기케이블의길이를일정하기유지하기위해상기정렬기의정렬 위치에드럼이상기모터구동부에의해추종제어가되어정렬기와 드럼간의정렬위치오차가 0이되도록하는것을특징으로하는유선 비행체에너지공급시스템.  A wire vehicle energy supply system, characterized in that a drum is tracked by the motor driver in order to maintain a constant length of the cable so that the alignment position error between the sorter and the drum becomes zero.
[청구항 25] 청구항 21내지청구항 23중어느하나의청구항에 있어서，  [Claim 25] The method according to any one of claims 21 to 23,
상기드럼은안정적으로균일하게풀림과감김이수행되도록드럼의 회전축방향으로케이블의직선운동을제공하는보조가이드를더 포함하는것을특징으로하는유선비행체에너지공급시스템.  Wherein said drum further comprises an auxiliary guide that provides a linear movement of the cable in the direction of the rotational axis of the drum such that the drum is stably unrolled and wound.
[청구항 26] 청구항 22내지청구항 23중어느하나의청구항에 있어서，  [Claim 26] The method according to any one of claims 22 to 23,
상기케이블조절부는드럼회전중심내부에수소저장부를위치하는 것을특징으로하는유선비행체에너지공급시스템.  The cable control unit is a wired vehicle energy supply system, characterized in that the hydrogen storage located in the center of the drum rotation.
[청구항 27] 청구항 22내지청구항 23중어느하나의청구항에 있어서,  [Claim 27] The method according to any one of claims 22 to 23,
상기케이블조절부의드럼은수소저장부와한몸체로형성되어드럼의 회전축을중심으로회전하는것을특징으로하는유선비행체에너지 공급시스템. ：  The drum of the cable control unit is formed in one body with the hydrogen storage unit, the wired aircraft energy supply system, characterized in that the rotation of the drum around the axis. ：
[청구항 28] 청구항 1，청구항 14，청구항 15중어느하나의청구항에 있어서,  [Claim 28] The method according to any one of claims 1, 14, 15,
상기케이블은소정의높이에위치하는케이블 :경유기를경유하도록 케이블경유기와상기케이블경유기가설치되는케이블경유비행체를 더포함하는것을특징으로하는유선비행체에너지공급시스템.  The cable is a cable located at a predetermined height: a wired vehicle energy supply system, characterized in that it further comprises a cable transit body through which the cable transiter and the cable transiter are installed via the transiter.
[청구항 29] 청구항 1，청구항 14,청구항 15증어느하나의청구항에 있어서，  Claim 29 In claim 1, claim 14 and claim 15, wherein any one of the claims
상기케이블은소정의높이에위치하는케이블경유기를경유하도록 케이블경유기와상기케이블경유기를지지하는케이블경유기 지지대를더포함하는것을특징으로하는유선비행체에너지공급 시스템  The cable system further comprises a cable router and a cable router support for supporting the cable router, via a cable router positioned at a predetermined height.
[청구항 30] 청구항 29에 있어서,  Claim 30: The method of claim 29,
상기케이블경유기는케이블조절부의드럼또는정렬기의회전축 선상에위치하는것을특징으로하는유선비행체에너지공급시스템. And wherein said cable router is positioned along the axis of rotation of the drum or aligner of the cable adjuster.
[청구항 31] 청구항 29에 있어서， Claim 31 The method of claim 29,
상기케이블경유기는케이블조절부의드럼또는정렬기의회전축 선상에소정의높이에위치하도록상기케이블경유기지지대가 구성되는것을특징으로하는유선비행체에너지공급시스템ᅳ  Wire cable energy supply system characterized in that the cable cable carrier support is configured such that the cable cable is located at a predetermined height along the rotation axis of the drum or the alignment section of the cable control unit.
[청구항 32] 청구항 29에 있어서,  Claim 32: The method of claim 29,
상기케이블경유기지지대는회전식케이블조절부의드럼회전 중심부에설치되는것을특징으로하는유선비행체에너지공급시스템 . The cable carrier support is a wired vehicle energy supply system, characterized in that it is installed in the drum rotation center of the rotary cable control unit.
[청구항 33] 청구항 29에 있어서， 33. The apparatus of claim 29,
상기케이블경유기지지대는，상기정렬기의회전시형성되는원통의 외부에고정되고;상기원통상단의증심에서시작하여상기정렬기 회전축선상의소정의높이에설치된상기케이블경유기까지관통 The cable carrier supporter is fixed to the outside of the cylinder formed when the aligner rotates; starting from the core at the top of the cylinder, the aligner Pass through the cable router installed at a certain height along the axis of rotation
구멍을갖는파이프형상인것을특징으로하는유선비행체에너지공급 시스템 .  Wired airplane energy supply system characterized by the shape of a pipe with holes.
[청구항 34] 청구항 28내지청구항 29중어느하나의청구항에 있어서,  [Claim 34] The method according to any one of claims 28 to 29,
상기케이블경유기는,케이블이동경로의접선방향에접촉면을  The cable router, the contact surface in the tangential direction of the cable movement path
제공하는회전체，상기회전체의회전축에수직방향인중력방향을 회전축으로회전할수있는회전부를포함하는것을특징으로하는유선 비행체에너지공급시스템.  A wired vehicle energy supply system, characterized in that it comprises a rotating body for providing a rotating body, the rotating shaft in the vertical direction to the rotating shaft of the rotating shaft.
[청구항 35] 청구항 29에 있어서，  Claim 35 The method of claim 29,
상기케이블경유기와케이블경유기지지대는상기케이블조절부에서 이격되어장애물의우회경로와긴수평거리를제공하도록다수의지점에, 설치되는것을특징으로하는유선비행체에너지공급시스템.  The cable carrier and cable carrier support are spaced apart from the cable control unit, the wired airplane energy supply system, characterized in that it is installed at a plurality of points to provide a bypass path and a long horizontal distance of the obstacle.
[청구항 36] 청구항 35에 있어서,  Claim 36 The method of claim 35,
상기케이블조절부에서 이격되는지점에설치되는케이블경유기는 일측면의상단이개방되아케이블을구속하지않는것을특징으로하는 유선비행체에너지공급시스템.  Cable router is installed at the point that is separated from the cable control unit is a wired airplane energy supply system, characterized in that the upper side of one side is not bound to bind the cable.
[청구항 37] 청구항 36에 있어서，  Claim 37 The method of claim 36,
상기케이블조절부에서이격되는지점에설치되는케이블경유기는 케이블의이동:마찰을최소화하기위해이동경로의접선방향에접촉면을 제공하는하부:회전체와좌우회전체를포함하고， Movement of the cable through the cable to be installed in the branch group which is spaced apart from the cable adjusting unit: includes a rotator and the entire right and left once,: lower to provide a contact surface in the tangential direction of the moving path in order to minimize the friction
좌우회전체는케이블의좌우에위치하고，하부회전체는케이블의 하부에위치하여,하부회전체와좌우회전체는서로수직되는방향으로 회전하는것을특징으로하는유선비행체에너지공급시스템.  A wired vehicle energy supply system, characterized in that the left and right rotors are located at the left and right of the cable, and the lower rotor is located at the bottom of the cable, and the lower rotor and the left and right rotors rotate in a vertical direction.
[청구항 38] 청구항 36에 있어서,  Claim 38 The method of claim 36,
상기케이블경유기는비행체의케이블이하강하여상기케이블  The cable route is lower than the cable of the aircraft to the cable
경유기의회전체에쉽게접촉되도록케이블가이드를더포함하는것을 특징으로하는유 비행체에너지공급시스템.  A fluid energy supply system further comprising a cable guide for easy contact with the rotor of the diesel engine.
PCT/KR2016/010263 2015-09-14 2016-09-12 Wired air vehicle energy supply system WO2017048016A1 (en)

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