KR102447512B1 - Hydrogen Fuel Wired Drone System - Google Patents

Abstract

The present invention relates to a hydrogen-fueled wired drone system comprising: a drone body; a fuel cell provided in the drone body to supply power, generated by receiving hydrogen fuel, to the drone body; a hydrogen fuel tank provided in the drone body to store the hydrogen fuel to be supplied to the fuel cell; a hydrogen fuel supply device for supplying the hydrogen fuel to the fuel cell and the hydrogen fuel tank; a battery tube connected to the fuel cell; a tank tube connected to the hydrogen fuel tank; a supply tube connected to the hydrogen fuel supply device; a three-way tube for connecting the battery tube, the tank tube, and the supply tube; a battery valve for opening and closing the battery tube; a tank valve for opening and closing the tank tube; a supply valve for opening and closing the supply tube; and a controller for selectively controlling the flight of the drone body, the opening and closing of the battery valve, the opening and closing of the tank valve, and the opening and closing of the supply valve. Therefore, the hydrogen-fueled wired drone system can supply the hydrogen fuel to be used through power conversion by a wire, thereby enabling the long flight of drones.

Description

Hydrogen Fuel Wired Drone System {SYSTEM FOR HYDROGEN CABLE DRONE}

The present invention relates to a hydrogen fueled wireline drone system.

A drone refers to an airplane or helicopter-shaped vehicle that does not get on and flies by induction of radio waves.

Drones were initially used for military purposes, but in recent years, the use of drones has been expanding. For example, the popularization of drones is gradually expanding, such as developing small drones and using them for leisure, and in the delivery industry using drones to deliver ordered products. In line with this trend, major companies around the world are focusing on investment and technology development, considering the drone-related industry as a promising new business.

There are two types of power supply methods for drones: a wireless method that receives power from a battery provided in the drone body, and a wired method that receives power from a power supply device connected to the drone body by a cable.

However, in the case of the wireless method, although the flight area of the drone may be wide, there is a problem in that it is difficult to fly the drone for a long time because the power consumption of the battery is high due to the nature of the drone flight.

In order to solve this problem, when the capacity of the battery provided in the drone is increased, the volume and weight of the drone are increased. As the size of the driving unit that drives the rotor increases, the overall weight and volume of the drone increase.

Therefore, it is necessary to develop a technology capable of increasing the flight and mission execution time without significantly increasing the weight of the drone.

Domestic Registered Patent Publication No. 10-2226748 (2021.03.05)

The present invention has been devised to solve the above-described problems, and an object of the present invention is to provide a hydrogen fuel wireline drone system capable of flying a drone for a long time by supplying hydrogen fuel to be used for power conversion by wire.

Another object of the present invention is to provide a hydrogen fuel wireline drone system that can safely make an emergency landing by using a reserve hydrogen fuel in a hydrogen fuel tank when a wire supplying hydrogen fuel is separated.

The problems to be solved by the present invention are not limited to the problems mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the following description.

A hydrogen fuel wired drone system according to an embodiment of the present invention includes a drone body; a fuel cell provided in the drone body and supplying power generated by receiving hydrogen fuel to the drone body; a hydrogen fuel tank provided in the drone body, in which hydrogen fuel for supply to the fuel cell is stored; a hydrogen fuel supply device for supplying hydrogen fuel to the fuel cell and the hydrogen fuel tank; a cell tube connected to the fuel cell; a tank pipe connected to the hydrogen fuel tank; a supply pipe connected to the hydrogen fuel supply device; a three-way pipe connecting the battery pipe, the tank pipe, and the supply pipe; a battery valve for opening and closing the battery tube; a tank valve for opening and closing the tank pipe; a supply valve for opening and closing the supply pipe; and a control unit for selectively controlling the flight of the drone body, opening and closing of the battery valve, opening and closing of the tank valve, and opening and closing of the supply valve.

In addition, further comprising a supply pressure sensor for measuring the internal pressure of the supply pipe, the control unit, if the pressure data measured by the supply pressure sensor is less than a set value, close the supply valve and close the battery valve and the tank valve It opens and induces an emergency landing of the drone body, and when the pressure data measured by the supply pressure sensor is greater than or equal to a set value, the battery valve, the tank valve, and the supply valve may be opened.

In addition, further comprising a tank pressure sensor for measuring the internal pressure of the tank pipe, the control unit, the pressure data measured by the supply pressure sensor is greater than or equal to a set value and the pressure data measured by the tank pressure sensor is less than the set value After opening the battery valve, the tank valve, and the supply valve, if the pressure data measured by the supply pressure sensor is equal to or greater than the set value and the pressure data measured by the tank pressure sensor is equal to or greater than the set value, the tank valve is closed. and open the battery valve and the supply valve.

In addition, further comprising a battery pressure sensor for measuring the internal pressure of the battery tube, the control unit, if the pressure data measured by the battery pressure sensor is less than a set value, closes the supply valve and closes the battery valve and the tank valve may be opened, and an emergency landing of the drone body may be induced.

In addition, provided in the hydrogen fuel supply device, the pulley for winding or unwinding the supply pipe; a driving motor that rotates the pulley forward and reverse; and a tension sensor for measuring the tension of the supply pipe, wherein the controller may control the driving motor to maintain the tension of the supply pipe within a predetermined range based on the tension data measured by the tension sensor.

Other specific details of the invention are included in the detailed description and drawings.

The hydrogen fuel wired drone system according to an embodiment of the present invention has the effect of enabling the drone to fly for a long time by supplying hydrogen fuel to be used for power conversion by wire.

In addition, the hydrogen fuel wireline drone system according to an embodiment of the present invention has the effect of safely emergency landing by utilizing the reserve hydrogen fuel in the hydrogen fuel tank when the wire supplying hydrogen fuel is separated.

Effects of the present invention are not limited to the effects mentioned above, and other effects not mentioned will be clearly understood by those skilled in the art from the following description.

1 is a perspective view illustrating a hydrogen fueled wired drone system according to an embodiment of the present invention.
2 to 4 are perspective views illustrating an operation process of a hydrogen fueled wired drone system according to an embodiment of the present invention.

Advantages and features of the present invention and methods of achieving them will become apparent with reference to the embodiments described below in detail in conjunction with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but may be implemented in various different forms, and only these embodiments allow the disclosure of the present invention to be complete, and those of ordinary skill in the art to which the present invention pertains. It is provided to fully inform those skilled in the art of the scope of the present invention, and the present invention is only defined by the scope of the claims.

Unless otherwise defined, all terms (including technical and scientific terms) used herein will have the meaning commonly understood by those of ordinary skill in the art to which this invention belongs. In addition, terms defined in a commonly used dictionary are not to be interpreted ideally or excessively unless clearly specifically defined.

Spatially relative terms "below", "beneath", "lower", "above", "upper", etc. It can be used to easily describe the correlation between a component and other components. A spatially relative term should be understood as a term that includes different directions of components during use or operation in addition to the directions shown in the drawings. For example, when a component shown in the drawing is turned over, a component described as "beneath" or "beneath" of another component may be placed "above" of the other component. can Accordingly, the exemplary term “below” may include both directions below and above. Components may also be oriented in other orientations, and thus spatially relative terms may be interpreted according to orientation.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a perspective view illustrating a hydrogen fueled wired drone system according to an embodiment of the present invention.

As shown in FIG. 1 , the hydrogen fuel wired drone system according to an embodiment of the present invention includes a drone body 10 , a fuel cell 20 , a hydrogen fuel tank 30 , a hydrogen fuel supply device 40 , and a It includes a branch pipe 50 , a tank pipe 60 , a supply pipe 70 , a three-way pipe 80 , a battery valve 90 , a tank valve 100 , a supply valve 110 , and a control unit 120 .

The drone body 10 is a basic body of the present invention, and serves to accommodate the flight and main parts of the drone. Here, the main components may include a controller 120 for flight control, a communication module for external communication, and a secondary battery for charging and discharging power.

A plurality of rotating blades 12 that rotate and generate lift may be provided on the upper side of the drone body 10 . The plurality of rotating blades 12 may be rotated by a driving device. For example, the driving device is not particularly limited, but a pneumatic motor, an electric motor, and the driving motor 170 may be used. Also, the driving device may receive power from the secondary battery.

A landing member 14 for landing upon landing may be provided on the lower side of the drone main body 10 . For example, the landing member 14 may be formed in a tubular shape or a bar shape.

The drone body 10 basically receives hydrogen fuel to be used for power conversion through the supply pipe 70 for a relatively long time, but in an unexpected situation, hydrogen fuel to be used for power conversion is supplied from the hydrogen fuel tank 30 for a relatively short period can be supplied while

For example, the unexpected situation may be a situation in which the supply pipe 70 for supplying hydrogen fuel by wire is cut or removed. Also, the unexpected situation may be a situation in which hydrogen is not supplied from the hydrogen fuel supply device 40 to the supply pipe 70 . Details on this will be described later.

The fuel cell 20 is provided in the drone body 10 , and serves to supply power generated by receiving hydrogen to the drone body 10 . More specifically, the fuel cell 20 uses hydrogen as a power source to generate electricity by chemically reacting with oxygen in the air. When water is electrolyzed, it is decomposed into hydrogen and oxygen, and conversely, by combining hydrogen and oxygen, When water is made, energy is generated, and at this time, the generated energy is converted into electricity. The converted power serves to charge the secondary battery provided in the drone body 10 .

The fuel cell 20 includes a pair of electrodes adjacent to an electrolyte to which hydrogen is supplied, and when oxygen in the air reaches the other electrode via one electrode, an electrochemical reaction occurs, and electrical energy, water, heat this is created

The hydrogen fuel tank 30 is provided in the drone body 10 , and hydrogen to be supplied to the fuel cell 20 is stored. For example, the hydrogen fuel tank 30 may be a compressed tank that compresses and stores hydrogen.

The hydrogen fuel supply device 40 is disposed on the ground and serves to supply hydrogen to the fuel cell 20 and the hydrogen fuel tank 30 . For example, the hydrogen fuel supply device 40 may be a fuel processing system (FPS) that supplies a required amount of hydrogen to the fuel cell 20 through hydrogen pressure control.

The cell pipe 50 is connected to the fuel cell 20, the tank pipe 60 is connected to the hydrogen fuel tank 30, the supply pipe 70 is connected to the hydrogen fuel supply device 40, and a three-way pipe ( 80 , the battery pipe 50 , the tank pipe 60 , and the supply pipe 70 are connected. Here, the battery tube 50 , the supply tube 70 , the intubation tube and the supply tube 70 may include a flexible material to facilitate winding or unwinding, for example, may include a rubber material.

The battery valve 90 opens and closes the battery pipe 50 , the tank valve 100 opens and closes the tank pipe 60 , and the supply valve 110 opens and closes the supply pipe 70 . For example, the battery valve 90 , the tank valve 100 , and the supply valve 110 may be a solenoid valve.

The control unit 120 serves to selectively control the flight of the drone body 10 , the opening and closing of the battery valve 90 , the opening and closing of the tank valve 100 , and the opening and closing of the supply valve 110 . The control unit 120 is not particularly limited, but a microcomputer, a terminal having an application embedded therein, a programmable logic controller (PLC), or the like may be used. Specifically, the control unit 120 controls the flight of the drone body 10 and the battery valve 90 according to the internal pressure of the battery pipe 50 , the internal pressure of the tank pipe 60 , and the internal pressure of the supply pipe 70 . It controls opening and closing, opening and closing of the tank valve 100, and opening and closing of the supply valve 110, which will be described in detail later.

The hydrogen fuel wired drone system according to an embodiment of the present invention includes a supply pressure sensor 130 , a tank pressure sensor 140 , a battery pressure sensor 150 , a pulley 160 , a drive motor 170 , and a tension sensor 180 . ) may be further included.

The supply pressure sensor 130 serves to measure the internal pressure of the supply pipe 70 . For example, the supply pressure sensor 130 may be provided at one end of the supply pipe 70 adjacent to the three-way pipe 80 .

Through this, if the pressure data measured by the supply pressure sensor 130 is less than the set value, the control unit 120 closes the supply valve 110, opens the battery valve 90 and the tank valve 100, and the drone body 10 ) to induce an emergency landing. Here, since the pressure data measured by the supply pressure sensor 130 is less than the set value, hydrogen cannot be supplied from the hydrogen fuel supply device 40 to the supply pipe 70 or the supply pipe 70 is cut or removed. , to induce an emergency landing of the drone body 10 .

In addition, when the pressure data measured by the supply pressure sensor 130 is equal to or greater than a set value, the control unit 120 opens the battery valve 90 , the tank valve 100 , and the supply valve 110 .

Here, when the pressure data measured by the supply pressure sensor 130 is equal to or greater than the set value, since hydrogen is normally supplied from the hydrogen fuel supply device 40 to the supply pipe 70 , the battery valve 90 and the tank valve 100 . and to open the supply valve 110 .

The tank pressure sensor 140 serves to measure the internal pressure of the tank pipe 60 . For example, the tank pressure sensor 140 may be provided at one end of the tank pipe 60 adjacent to the three-way pipe 80 .

Through this, when the pressure data measured by the supply pressure sensor 130 is greater than or equal to the set value and the pressure data measured by the tank pressure sensor 140 is less than the set value, the control unit 120 controls the battery valve 90 and the tank valve 100 ) and after opening the supply valve 110, if the pressure data measured by the supply pressure sensor 130 is equal to or greater than the set value and the pressure data measured by the tank pressure sensor 140 is equal to or greater than the set value, the tank valve 100 is closed. Close and open the battery valve 90 and the supply valve 110 .

Here, when the pressure data measured by the supply pressure sensor 130 is greater than or equal to the set value and the pressure data measured by the tank pressure sensor 140 is less than the set value, since the hydrogen fuel tank 30 is not completely filled with hydrogen, the battery The valve 90, the tank valve 100, and the supply valve 110 are opened, and the hydrogen fuel tank ( 30 ), and hydrogen is supplied from the hydrogen fuel supply device 40 to the fuel cell 20 through the supply pipe 70 , the three-way pipe 80 , and the cell pipe 50 .

In addition, since the pressure data measured by the supply pressure sensor 130 is greater than or equal to the set value and the pressure data measured by the tank pressure sensor 140 is greater than or equal to the set value, the hydrogen fuel tank 30 is completely filled with hydrogen, the tank valve 100 is closed, the cell valve 90 and the supply valve 110 are opened, and the hydrogen fuel tank from the hydrogen fuel supply device 40 through the supply pipe 70 , the three-way pipe 80 , and the tank pipe 60 . The supply of hydrogen to 30 is stopped, and hydrogen is supplied only to the fuel cell 20 through the supply pipe 70 , the three-way pipe 80 , and the cell pipe 50 from the hydrogen fuel supply device 40 .

The battery pressure sensor 150 serves to measure the internal pressure of the battery tube 50 . For example, the battery pressure sensor 150 may be provided at one end of the battery tube 50 adjacent to the three-way tube 80 .

Through this, when the pressure data measured by the battery pressure sensor 150 is less than the set value, the control unit 120 closes the supply valve 110 and opens the battery valve 90 and the tank valve 100, and the drone body ( 10) to induce an emergency landing. Here, the pressure data measured by the cell pressure sensor 150 is less than the set value from the hydrogen fuel supply device 40 to the fuel cell 20 through the supply pipe 70 , the three-way pipe 80 , and the battery pipe 50 . Since hydrogen cannot be supplied, the supply valve 110 is closed, the battery valve 90 and the tank valve 100 are opened, and the tank pipe 60, the three-way pipe 80, Hydrogen is supplied to the fuel cell 20 through the battery tube 50 , and an emergency landing of the drone body 10 is induced.

The pulley 160 is provided in the hydrogen fuel supply device 40 and serves to wind or unwind the supply pipe 70 .

The driving motor 170 rotates the pulley 160 forward and reverse, and serves to operate the supply pipe 70 to the pulley 160 to be wound or unwound.

The tension sensor 180 measures the tension of the supply pipe 70 . For example, the tension sensor 180 may be provided at a specific portion of the supply pipe 70 adjacent to the three-way pipe 80 .

Through this, the controller 120 may control the driving motor 170 to maintain the tension of the supply pipe 70 within a predetermined range based on the tension data measured by the tension sensor 180 .

In addition, as the supply pipe 70 is cut or removed, if the tension data measured by the tension sensor 180 is less than a set value, the control unit 120 closes the supply valve 110 and closes the battery valve 90 and the tank valve. (100) is opened, and hydrogen is supplied from the hydrogen fuel tank (30) to the fuel cell (20) through the tank pipe (60), the three-way pipe (80), and the battery pipe (50), and the drone body (10) induce an emergency landing.

Hereinafter, the operation process of the hydrogen fueled wired drone system will be described.

2 to 4 are perspective views illustrating an operation process of a hydrogen fueled wired drone system according to an embodiment of the present invention. The following operation process may be performed by the controller 120 .

First, as shown in FIG. 2 , as the control unit 120 opens all of the supply valve, the tank valve, and the battery valve, the supply pipe 70 , the three-way pipe 80 , and the tank pipe are supplied from the hydrogen fuel supply device 40 . Hydrogen is supplied to the hydrogen fuel tank 30 through 60 , and hydrogen is supplied from the hydrogen fuel supply device 40 to the fuel cell 20 through the supply pipe 70 , the three-way pipe 80 , and the cell pipe 50 . is supplied

At this time, when the hydrogen fuel tank 30 is not completely filled with hydrogen or there is no hydrogen, the pressure data measured by the supply pressure sensor 130 of the internal pressure of the supply pipe 70 is greater than or equal to the set value and the tank pressure sensor 140 ), since the pressure data measuring the internal pressure of the tank pipe 60 is less than the set value, the control unit 120 maintains the state in which the supply valve, the tank valve, and the battery valve are all opened.

After that, as shown in FIG. 3 , in a state in which hydrogen is completely filled in the hydrogen fuel tank 30 , the pressure data measuring the internal pressure of the supply pipe 70 is greater than or equal to the set value, and the tank pressure sensor 140 in the tank pipe Since the pressure data measuring the internal pressure of 60 is greater than or equal to the set value, the control unit 120 closes the tank valve and maintains the supply valve and the battery valve open, the hydrogen fuel supply device 40 Hydrogen is not supplied to the hydrogen fuel tank 30 through the supply pipe 70, the three-way pipe 80, and the tank pipe 60, but the supply pipe 70 and the three-way pipe 80 from the hydrogen fuel supply device 40 , hydrogen is supplied to the fuel cell 20 through the cell tube 50 .

Subsequently, as shown in FIG. 4 , in a state in which hydrogen is not supplied from the supply pipe 70 from the hydrogen fuel tank 30 or the supply pipe 70 is cut or removed, the pressure measured by the internal pressure of the supply pipe 70 . Since the data is less than the set value, as the control unit 120 opens the supply valve and opens the tank valve and the battery valve, the tank pipe 60, the three-way pipe 80, and the battery pipe are discharged from the hydrogen fuel tank 30. Hydrogen is supplied to the fuel cell 20 through 50 . In this case, the control unit 120 may attempt an emergency landing of the drone main body 10 .

Also, if necessary, the controller 120 may emit an alarm sound or a warning sound when the drone main body 10 attempts an emergency landing.

According to the present invention, the hydrogen fuel wired drone system according to an embodiment of the present invention has the effect that the drone can fly for a long time by supplying hydrogen fuel to be used for power conversion by wire.

In addition, the hydrogen fuel wireline drone system according to an embodiment of the present invention has the effect of safely emergency landing by using the reserve hydrogen fuel of the hydrogen fuel tank when the wire supplying hydrogen fuel, that is, the supply pipe is separated. have.

As mentioned above, although embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art to which the present invention pertains can realize that the present invention can be embodied in other specific forms without changing its technical spirit or essential features. you will be able to understand Therefore, it should be understood that the embodiments described above are illustrative in all respects and not restrictive.

10: drone body
12: rotating blade
14: landing member
20: fuel cell
30: hydrogen fuel tank
40: hydrogen fuel supply
50: battery tube
60: tank pipe
70: supply pipe
80: three-way tube
90: battery valve
100: tank valve
110: supply valve
120: control unit
130: supply pressure sensor
140: tank pressure sensor
150: battery pressure sensor
160: pulley
170: drive motor
180: tension sensor

Claims (5)

drone body;
a fuel cell provided in the drone body and supplying power generated by receiving hydrogen fuel to the drone body;
a hydrogen fuel tank provided in the drone body, in which hydrogen fuel for supply to the fuel cell is stored;
a hydrogen fuel supply device for supplying hydrogen fuel to the fuel cell and the hydrogen fuel tank;
a cell tube connected to the fuel cell;
a tank pipe connected to the hydrogen fuel tank;
a supply pipe connected to the hydrogen fuel supply device;
a three-way pipe connecting the battery pipe, the tank pipe, and the supply pipe;
a battery valve for opening and closing the battery tube;
a tank valve for opening and closing the tank pipe;
a supply valve for opening and closing the supply pipe;
a control unit for selectively controlling the flight of the drone body, opening and closing of the battery valve, opening and closing of the tank valve, and opening and closing of the supply valve; and
A supply pressure sensor for measuring the internal pressure of the supply pipe,
The control unit is
When the pressure data measured by the supply pressure sensor is less than a set value, the supply valve is closed, the battery valve and the tank valve are opened, and an emergency landing of the drone body is induced,
When the pressure data measured by the supply pressure sensor is greater than or equal to a set value, the battery valve, the tank valve, and the supply valve are opened, a hydrogen fuel wired drone system.
delete According to claim 1,
Further comprising a tank pressure sensor for measuring the internal pressure of the tank pipe,
The control unit is
When the pressure data measured by the supply pressure sensor is greater than or equal to the set value and the pressure data measured by the tank pressure sensor is less than the set value, after opening the battery valve, the tank valve and the supply valve,
When the pressure data measured by the supply pressure sensor is equal to or greater than a set value and the pressure data measured by the tank pressure sensor is equal to or greater than the set value, the tank valve is closed and the battery valve and the supply valve are opened, a hydrogen fuel wired drone system .
According to claim 1,
Further comprising a battery pressure sensor for measuring the internal pressure of the battery tube,
The control unit is
When the pressure data measured by the battery pressure sensor is less than a set value, the supply valve is closed, the battery valve and the tank valve are opened, and an emergency landing of the drone body is induced.
According to claim 1,
a pulley provided in the hydrogen fuel supply device to wind or unwind the supply pipe;
a driving motor that rotates the pulley forward and reverse; and
Further comprising a tension sensor for measuring the tension of the supply pipe,
The control unit controls the driving motor so that the tension of the supply pipe is maintained within a predetermined range based on the tension data measured by the tension sensor, a hydrogen fuel wired drone system.

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