WO2017048016A1

WO2017048016A1 - Wired air vehicle energy supply system

Info

Publication number: WO2017048016A1
Application number: PCT/KR2016/010263
Authority: WO
Inventors: 이승규
Original assignee: 이승규
Priority date: 2015-09-14
Filing date: 2016-09-12
Publication date: 2017-03-23
Also published as: KR102096039B1; KR20180045027A

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

Specification

Title of invention: Technical field of energy supply system of wired aircraft

[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.

Background

[2] surveillance and communication relays, facility surveillance, search, etc.

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] Unmanned aerial vehicles require sufficient power to perform a variety of missions,

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] To solve these problems, ground power supplies

Systems (or devices) that power vehicles by wired cables have traditionally been used.

[5] 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 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] 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] Due to these problems, the altitude (or The flight distance is currently not exceeding tens of meters under practical operating conditions.

[8] Wired aircraft also moved horizontally from the point where ground cables were fed.

When moving, ground due to the inclination of the cable and the deflection of the cable

Interference with obstacles occurs, i.e., the obstacles in the horizontal direction due to obstacles on the cable are hindered.

[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] Also, when the aircraft changes its position due to rotation and turning, it is fixed to the aircraft.

Cables can be damaged by twisting. In order to prevent this problem, the cable is normally detected by twisting the cable.

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.

Detailed description of the invention

Technical task

[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] In addition, cable carriers can move horizontally (or even fly) horizontally on cable bases.

It is aimed at not being disturbed by obstacles.

[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

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.

The fuel cell fuel may be hydrogen.

[16] 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.

[19] 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.

[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.

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.

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.

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.

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] 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.

In the wired vehicle energy supply system, the cable may include a communication line capable of transmitting a communication signal.

In the wired flight energy supply system, 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;

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.

In the wired aircraft energy supply system, the drum is 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.

In the wired vehicle energy supply system, the cable control unit may be a hydrogen storage unit inside the drum rotation center.

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] 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.

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] The cable router is located on the rotation axis of the drum or the alignment unit of the cable control unit.

May be located.

[44] 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.

[45] The cable carrier support part is provided in the drum rotation center of the rotary cable control unit.

It may be installed.

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] 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.

[48] 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.

[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] 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.

Effects of the Invention

[52] The airplane energy supply system according to the present invention is wired from the ground.

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] In addition, obstacles on the ground of the cable can be avoided even if the wired vehicle moves horizontally.

Undisturbed

[54] In addition, even if the wired vehicle changes its position due to rotation and turning flight, The kink can be eliminated.

Brief description of the drawings

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.

3 is an example of a cable control unit

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. FIG.

6 is a sectional view of Embodiment 1 of a transmission cable

7 is a cross-sectional view and perspective view of a second embodiment of a transmission cable

8 is a sectional view of Embodiment 3 of a transmission cable;

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

[65] Figure 11 shows the interference between the ground obstacle and the cable

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;

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

[76] Figure 22 is a daisy chain connection diagram for securing the diagonal field of view

23 shows an embodiment of a slip ring unit.

24 is a configuration diagram with Example 1 of the cable twist prevention

25 is a configuration diagram of cable twist prevention Example 2

26 is a configuration diagram of a cable twist prevention Example 3

Best Mode for Carrying Out the Invention

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] 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] Also, 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.

In the present invention, the fuel supply energy supply system uses fuel cells to generate power for wired aircraft.

[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] 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.

[88] Several fuels and oxidants are available. Hydrogen fuel cells use hydrogen.

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] The main body of the fuel cell is introduced hydrogen, oxygen in the air, direct current electricity, water and

Generates byproducts.

[90] Fuel cells may include a fuel reformer, which is a fuel reformer.

If the incoming fuel is fuel other than hydrogen (eg methanol, methane, LPG, LNG, gasoline), hydrogen can be derived from the fuel.

[91] From a fuel cell fuel supply located on the ground or above ground, to a flying vehicle

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] 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] Second, the conventional wired power supply method uses a metal with a high density of cables.

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] Especially when the fuel cell fuel is hydrogen, hydrogen is very light and has a fast diffusion rate.

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] 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] In other words, through the fuel transmission cable to the internal combustion engine of the aircraft on the ground

It is a structure that supplies fuel (hydrogen, gasoline, diesel, LNG, etc.) from the ground.

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] 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] Therefore, even when using an internal combustion engine and a generator, conventional wired power supply

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.

1 is a view of an embodiment of a wired vehicle energy supply system according to the present invention.

It is a block diagram.

The wired airplane energy supply system according to the present invention may be referred to as a wired airplane energy supply device.

[102] 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.

Include.

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. 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] 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

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.

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).

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.

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] 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. 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] Hydrogen storage methods include liquid storage, gas storage,

There is a method of storing as a solid in the form of metal hydride.

[114] And to store a lot of hydrogen gas in small volumes,

It is desirable to use a carbon fiber based hydrogen gas storage container with excellent durability.

The supply control unit 230 from the hydrogen generating unit 210 or the hydrogen storage unit 220

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] included in the feed control unit 230 functionally hydrogen stored in unit 220 in the present ^invention, can eu

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

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.

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.

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] In other words, 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.

In FIG. 3, the cable adjusting unit 240 includes a motor driving unit 241 and a drum 242.

Guide 244, aligner 243, and auxiliary guide 255.

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

When the aligner 243 rotates around the drum by the motor driver 241, it becomes fixed.

In the fixed type, the cable 300 is connected to the cable 300 according to the direction of rotation of the aligner.

Unwinding and winding operations are performed on the drum 242.

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] movements that allow the cable to be unwound or wound smoothly without twisting the cable

The guide 244 is composed of a rotating body (for example, a roller) that tangentially moves the path of the cable 300.

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.

In FIG. 3, the auxiliary guide 255 is stably connected to the drum 242 in a stable manner.

It is intended to be able to be wound or unwound.

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.

In addition, even if the flying vehicle 100 turns 360 degrees, the twisting of the cable 300 does not occur.

It further comprises a sorter (243) to avoid.

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.

That is, the drum 242 is rotated by the motor driving unit 241, the sorter 243 is

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] 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.

For this purpose, if the sorter 243 rotates to change the sorting position of the sorter,

Alignment between the sorter 243 and the drum 242 provided by the position sensor 245

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".

In other words, when the vehicle is turning, the drum 242 is placed in the alignment position of the sorter 243.

It is characterized by performing a sorter following control that follows the position (rotation angle).

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.

As shown in Figure 4, the two rotors (BB) are fixed and the cable 300

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.

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.

Therefore, in FIG. 3, the tension sensor display of the rotor displacement detection method is omitted.

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.

That is, 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.

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.

In FIG. 5 (a), the hydrogen storage unit 220 is located outside the drum 242, while FIG.

In 5 (b), a cylindrical hydrogen storage unit 220 is placed inside the center of rotation of the drum 242 to increase space utilization.

5, the rotary cable control unit 240 of the motor driving unit 241, the rod rum 242 and hydrogen

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.

On the other hand, in the case where the cable control unit 240 is fixed in Figure 5,

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.

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.

The transmission cable 300a connects a fuel transmission path for transmitting fuel cell fuel.

Include.

6 is a sectional view of Embodiment 1 of a transmission cable.

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.

As a result, the transmission cable 300a is light and excellent in durability.

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.

7 is a sectional view and perspective view of Embodiment 2 of a transmission cable.

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] The high-strength center line 370 is a line-shaped object that can withstand strong forces and is transmitted.

It is located at the center of the cable and is called the central line.

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] In Fig. 7, a material having excellent tensile strength and strength (eg, aramid fiber, high strength).

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.

In addition, the tube 360 may include a communication line 350 for wired communication with the aircraft 100.

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.

8 is a sectional view of Embodiment 3 of a transmission cable.

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. .

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.

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] First, the fuel transmission cable 300a and the optical fiber 350a communication line can be integrated into a single-stranded cable.

[172] Second, the protective sheath (or sheath) of the optical fiber or optical fiber communication line was transferred to the tube 360.

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] 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.

In this case, the fuel transmission is performed by the optical fiber 350a communication line in the space of the fuel transmission passage 310.

This is accomplished through the remaining space, excluding the occupied space.

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.

10 is an example of a cable connection diagram including a plurality of fluid transmission cables.

In FIG. 10, the cable 300 of the flying vehicle 100 is connected to the energy supply unit 2000.

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).

The energy supply cable 3000 and the fluid transmission cable 3000a are cables

It is connected to the vehicle 100 via the adjusting unit 240.

[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.

FIG. 11 shows how the obstacle 2 and the cable 300 of the ground 1 are interfered with.

[183] Above the ground (1), when the aircraft (100) moves horizontally, the cable (300)

The obstacles (2) can be hindered by the movement.

12 is a conceptual diagram of an embodiment of a support cable route method.

12 (a) is due to the inclination angle and deflection of the cable during horizontal flight in the present invention.

This is a conceptual diagram of the cable route by the support to prevent interference between the obstacle and the cable if it occurs.

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.

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.

By way of the transiter 500, the cable 300 is displaced when the vehicle moves horizontally.

Provide vertical height so as not to interfere with ground (2).

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.

And the cable carrier support (5000) of the cable control unit 240

Depending on the method (rotary, fixed), the position and structure of the cable control unit 240 is different.

13 is a view of a rotary cable control unit 240 including a cable passer

In one embodiment.

FIG. 13 (a) is a front view of one embodiment, and FIG. 13 (b) is a perspective view of FIG. 13 (a).

FIG. 13 (c) shows a perspective view of an embodiment with a gasoline. ：

13 (a) and 13 (b), the cable 300 of the cable control unit 240 is a cable

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.

In addition, the cable transit 500 is a cable according to the movement of the cable and the position of the flying vehicle.

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

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] Accordingly, the cable passer 500 is connected to the cable at the time of movement and change of direction. Minimize the friction at work.

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.

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, and FIG. 14 (c) is a perspective view of one embodiment of a support movement guide. .

In FIG. 14 (a), the fixed cable adjustment unit 240 is rotated by the alignment unit 243.

Winding and unwinding operations are performed on the drum 242 of the cable 300.

In Figure 14 (a) by the rotation of the sorter 243 rotation radius and fixed formula of the sorter

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.

Therefore, the cable passer that is installed in the fixed cable control unit 240

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.

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.

The cable 300 is connected to the cable adjusting unit 240 via the cable passer 500.

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.

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.

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).

As shown in FIG. 14 (a), a cable router on the axis of rotation of the above sorter 243 is shown.

The support 5000 has a hollow pipe shape through which the cable 300 is constrained.

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.

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] In addition, as shown in FIG. 14 (c), the support movement guide 544 includes the cable of FIG. 14 (b).

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.

And fixed cable control unit 240 of Figure 14, the sorter 243 is fixed

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.

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.

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.

15 is a perspective view of one embodiment of FIG. 14.

[214] The cable of FIGS. 14 and 15 in the cable routing method by the support.

The diesel engine 500 and the support movement guide 544 are used for moving the cable and

Provides the ability to minimize friction and twist on the cable when turning (or turning).

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] In order to solve this problem, the incremental support can be removed by using the support cable of FIG.

In addition, you can include more.

FIG. 16 is a conceptual diagram of one embodiment of the intermediate support cable route method. FIG.

16 (a) shows a method of via a support cable including an intermediate support (5000a).

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.

As shown in FIG. 16 (a), an incremental support 5000a including a cable transiter 500 is provided.

Installed at the intermediate point from the cable control section to the maximum horizontal travel distance

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] In addition, the load on the cable exerted on the vehicle by the cable transiter (500,500a)

Is reduced.

[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. '

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] where the cable supporter of the intermediate support is 500a

The cable route can be provided for horizontal movement to a position beyond the support (5000a).

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.

It is installed on the intermediate support (5000a) to provide the function as described above.

The structure of the cable route 500a is configured to be routed or routed through the cable depending on the position of the vehicle.

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.

It is preferable to have a structure in which one side of the diesel engine 500a is opened.

As shown in FIG. 16 (b), a number of incremental supports 5000a and cable passers 500a are

It provides a path to bypass a number of obstacles (2) so that the vehicle (100) can move horizontally between the obstacles (2).

[228] In this way, it is restricted to include the intermediate support via the magnetic pole cable.

The vertical height support provides long horizontal travel distances and bypass paths at low altitudes without obstacles and interference.

[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.

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, and FIG. 17 (b) is

Perspective view.

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] And as shown in Figure 17 (a), the cable passer (500a) fe cable of the intermediate support

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.

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.

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.

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.

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.

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, 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.

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.

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.

It does not interfere with the obstacles (2) on the cable (300), because it acts as a support (holding).

As shown in FIG. 18 (a), the cable of the cable adjusting unit passes through 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.

[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).

It has additional disadvantages.

[244] The cable transiter of the present invention schedules the cable load when the vehicle moves horizontally.

As it supports the part, the cable lowering

To reduce.

[245] When this facility is re-named, the vehicle will be driven to the vertical height provided by the cable router.

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.

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.

Therefore, the cable duct shown in FIG. 19 can be applied to the cable duct shown in FIG.

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.

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] In addition, the cable 300 and the cable passer 500

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.

In addition, the rotor support 510 is coupled to the two rotors 520, the two

Combined in a structure that allows rotation of the rotor.

In addition, the transmission cable 300 to pass between the two rotating bodies, and

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.

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.

The cable router depends on the tension applied to the cable and the durability of the cable.

Of course, it can be implemented in various shapes and structures.

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. 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.

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).

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.

In addition, branched from the flight l (100a) is connected to the flight 2 (100b)

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). ᅳ

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.

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] When the wired vehicle energy supply system of FIG. 20 is rearranged, the vehicle is

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.

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).

In FIG. 21, when the slider moves (999_2) according to the displacement of the elastic body (999_1).

As the resistance 999_3 changes, 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.

As shown in FIG. 22, the vehicle l (100a) is positioned higher than the obstacle (2).

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] In the embodiment of the present invention, the "Daisy chain" configuration of the aircraft

Although two aircraft, l (100a) and 2 (100b), were described as limited, Of course, the same applies to the aircraft.

[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] In addition, when many vehicle position coordinates are combined properly,

It is characterized by providing the vertical altitude and horizontal movement (flight) required for wired aircraft while excluding it.

[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] 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] Therefore, a number of airplanes connected by a daisy chain method

Cable twist protection, which does not cause cross cable twisting, is required even when rotating independently.

[279] In the present invention, the supply of energy for wired aircraft, which is configured in a daisy chain manner.

The system is characterized by providing maximum flight altitude for high-floor flight and maximum horizontal movement without horizontal interference with horizontal obstacles.

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] Therefore, various areas requiring low altitude flight (eg agricultural control, broadcasting)

Wired energy supply systems of the present invention may be applied to shooting, military mine detection, etc.).

[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.).

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] On the other hand, if the flight posture changes due to the turning and turning flight,

Cables fixed to the aircraft can be twisted, which can damage the cables.

[285] To prevent this problem, conventionally, the kink is detected to

We solved the way of flying the plane in the opposite direction, but this

There is a problem that causes a change in the attitude of the aircraft.

In this case, the cable 300 may be configured to rotate independently of the vehicle.

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.

The slip ring provides a function of transferring electricity without twisting an electrical cable connected between the rotating part and the fixing part. ：

23 shows an embodiment of a slip ring unit.

In FIG. 23, three slip rings 115_1 connected to the rotary part cable 115_4 are provided.

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.

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;

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.

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,

The electrical connection with the battery 120 is maintained without cable twist.

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.

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). :

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.

25 is a configuration diagram of cable twist prevention Example 2;

As shown in FIG. 25, the transmission cable 300a is connected via a rotary joint 118.

Is connected to the fuel cell 1 10.

[298] A commonly used rotary joint is used between the rotary part and the fixed part.

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.

FIG. 26 is a configuration diagram of Embodiment 3 for preventing cable twist using a slip ring.

In the case of supplying power to the wired aircraft 100 through the power cable 300b, FIG.

As in 24, the power cable 300b is directly connected to the slip ring unit 115.

Claims

Claim

Claim 1 A flying vehicle comprising a fuel cell and a flying electric machine;

A fuel cell fuel supply device located outside of the vehicle;

A transmission cable connecting the flying vehicle and the fuel cell fuel supply device; Including,

The transmission cable includes a fuel transmission passage for transmitting fuel cell fuel,

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.

Claim 2 The method according to claim 1,

A wired vehicle energy supply system, wherein the fuel cell fuel is hydrogen.

Claim 3 The method according to claim 1,

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.

Claim _{4 The} method according to claim 1,

A wired airplane energy supply system, characterized in that an optical fiber communication line passes through a fuel transmission path of the transmission cable.

[Claim 5] In Claim 4,

The fiber optic communication line is wired airplane energy supply system, characterized in that the outer shell of the fuel transmission tube.

Claim 6 The method according to claim 1,

A wired airplane energy supply system, characterized in that a high-strength center line passes through a fuel transmission path of the transmission cable.

Claim 7 The method according to claim 1,

The flying vehicle energy supply system, characterized in that it comprises a battery capable of storing the electricity produced by the fuel cell.

Claim 8 The method according to claim 1,

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.

[Claim 9] The method according to claim 1, The fuel cell fuel supply unit includes a hydrogen generator that generates hydrogen

Wired aircraft energy supply system characterized by including.

Claim 10 The method according to claim 1,

And the fuel cell fuel supply device includes a cable control unit for adjusting the tension and length of the cable.

[Claim 11] In Claim 1,

And a transmission cable connected to the vehicle, wherein the transmission cable is connected through a rotary joint.

[Claim 12] In claim 1,

The fuel cell fuel supply apparatus further comprises a supply control unit capable of controlling the amount or pressure of hydrogen to be supplied.

Claim 13 The method of claim 12,

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.

[Claim 14] A flying vehicle that supplies power by wire;

A power supply system located outside of the vehicle;

A power cable connecting the flying vehicle and the power supply system;

Including,

The vehicle comprises a slip ring,

And said power cable is connected via said slip ring.

Claim 15 A flying vehicle comprising an internal combustion engine and flying electrical equipment;

An internal combustion engine fuel supply device located outside of the vehicle;

A transmission cable connecting the flying vehicle and the internal combustion engine fuel supply device; Including,

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.

[Claim 16] The method according to any one of claims 1, 14 and 15,

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.

[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,

The cable is connected in series with the rest of the vehicles via system 1,

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.

Claim 18 The method of claim 17,

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.

[Claim 19] The method according to any one of claims 1, 14 and 15,

Wherein said cable comprises a communication line capable of transmitting a communication signal.

[Claim 20] The method according to any one of claims 1, 14 and 15,

Wireline energy supply system, characterized in that it comprises a cable control unit for adjusting the tension and length of the cable.

According to [Claim ^21] of claim ^20,

The cable control unit

A drum that performs the winding and unwinding of the cable;

A sorter that rotates 360 degrees with the amplification axis of the drum;

A motor driver for driving the sorter;

A movement guide providing a movement path of the cable;

Wireline energy supply system, characterized in that for rotating the sorter, including winding the cable to the drum.

Claim 22: The method of claim 20,

The cable control unit

A drum that performs the winding and unwinding of the cable;

A motor driving part for driving the drum;

A movement guide providing a movement path of the cable;

Wireline energy supply system, characterized in that the drum is rotated, including the winding or unwinding cable to the drum.

Claim 23 The method of claim 20,

The cable control unit

A drum that performs the winding and unwinding of the cable;

A motor driving part for driving the drum;

A movement guide providing a movement path of the cable;

A sorter which rotates 360 degrees with the rotation axis of the drum;

A position sensor for detecting a position of the drum processor;

A wired aircraft energy supply system, characterized in that it comprises a. Claim 24 The method of claim 23,

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.

[Claim 25] The method according to any one of claims 21 to 23,

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.

[Claim 26] The method according to any one of claims 22 to 23,

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.

[Claim 27] The method according to any one of claims 22 to 23,

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. ：

[Claim 28] The method according to any one of claims 1, 14, 15,

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.

Claim 29 In claim 1, claim 14 and claim 15, wherein any one of the claims

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.

Claim 30: The method of claim 29,

And wherein said cable router is positioned along the axis of rotation of the drum or aligner of the cable adjuster.

Claim 31 The method of claim 29,

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.

Claim 32: The method of claim 29,

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.

33. The apparatus of claim 29,

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

Wired airplane energy supply system characterized by the shape of a pipe with holes.

[Claim 34] The method according to any one of claims 28 to 29,

The cable router, the contact surface in the tangential direction of the cable movement path

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.

Claim 35 The method of claim 29,

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.

Claim 36 The method of claim 35,

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.

Claim 37 The method of claim 36,

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

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.

Claim 38 The method of claim 36,

The cable route is lower than the cable of the aircraft to the cable

A fluid energy supply system further comprising a cable guide for easy contact with the rotor of the diesel engine.