KR102226748B1 - Energy supply apparatus for drones using hydrogen fuel cell - Google Patents

Abstract

The present invention relates to an energy supply device for a drone using a hydrogen fuel cell, comprising: a drone body including a housing unit configured to produce and store electric energy using hydrogen; A hydrogen tank built in the upper part of the housing and storing a predetermined amount of hydrogen fuel; A regulator connected to the hydrogen tank and reducing a supply pressure of the supplied hydrogen fuel; A stack connected to the regulator and generating electricity by inducing a reaction between hydrogen fuel and external air, which has been depressurized; A controller that controls whether or not the generated electricity is supplied, driving and flying the drone; And a battery in which the generated electricity is stored.

Description

Energy supply apparatus for drones using hydrogen fuel cell

The present invention relates to an energy supply device for a drone using a hydrogen fuel cell, and more particularly, by maximizing the efficiency of electric energy supplied to the drone using a hydrogen fuel cell, the flight time and the mission execution radius of the drone are improved. , It relates to an energy supply device for a drone using a hydrogen fuel cell capable of maximizing the stability of fuel supply by stably reducing the supply pressure of hydrogen fuel supplied from the hydrogen storage tank step by step.

In general, Unmanned Aerial Vehicle (UAV) is also called a drone, and refers to an unmanned aerial vehicle that can be controlled by radio waves. Such unmanned aerial vehicles are equipped with cameras, sensors, and communication systems, and vary in weight and size according to their use. In the early days, unmanned aerial vehicles were first created for military use, but according to the continuous development of electronic communication technology, they are spreading not only to military use but also to various other fields, and are preferred as unmanned aerial vehicles suitable for performing various missions for a long time.

On the other hand, in order to perform the various missions described above, a stable flight time of the drone must be secured, and for this purpose, the secondary battery used as a battery to increase the reserves of the energy source provided in the drone increases in volume and weight when the capacity is increased. There was an increasing problem, which means that the size of the lift generated by the rotor for flight must be increased, and the size of the rotor generating the lift and the drive unit that drives the rotor also increases, increasing the overall weight and volume of the drone. It has consequences.

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

For example, in Korean Patent Registration No. 10-1924225 (hereinafter referred to as Prior Art Document 1), in a drone flying with a driving control system equipped, electricity is supplied by hydrogen supplied from a fuel tank provided in the drone. A fuel cell that produces; A secondary battery provided in the drone to supply power; By receiving the status information of the fuel cell and the status information of the secondary battery, the power generated by the fuel cell is used to charge the secondary battery while controlling whether the fuel cell and the secondary battery use power or whether the secondary battery is charged. A hydrogen fuel cell drone equipped with a hybrid controller including a hybrid controller that controls so that it can be supplied and supplied to the drive control system at the same time has been published.

However, according to the above-described Prior Art Document 1, there is a problem in that the weight of the drone is not achieved by increasing the weight of the drone itself, as both a fuel cell and a secondary battery using hydrogen are provided.

In addition, when electric energy is produced from a fuel cell, it is configured not to control the supply amount of hydrogen supplied, so there was a problem with safety during the production of electric energy, and the surrounding environment of the drone, flight time, or flight It is difficult to supply energy smoothly due to the difference in power consumed during the time, and rather, there is a problem that the flight time of the drone is reduced.

Korean Patent Registration No. 10-1924225

In order to solve such a problem, the present invention was conceived by the above-described background technology, and the efficiency of electric energy supplied to the drone is maximized using a hydrogen fuel cell, thereby improving the flying time and the mission execution radius of the drone. Its purpose is to provide an energy supply device for drones using hydrogen fuel cells.

In addition, the present invention reduces the weight of the hydrogen storage cylinder and the hydrogen fuel cell stack, and at the same time stably reduces the supply pressure of hydrogen fuel supplied from the hydrogen storage cylinder in stages, thereby maximizing the stability of fuel supply. Its purpose is to provide an energy supply device for drones using fuel cells.

In addition, the present invention further configures a buoyancy tube in which helium gas is charged around the drone to extend the flight time and movement distance of the drone, to maintain stable flight, and to maintain high air resistance when the drone descends or falls. It is an object of the present invention to provide an energy supply device for drones using a hydrogen fuel cell that can secure a preparation time by a collision.

However, the object of the present invention is not limited thereto, and objects or effects that can be grasped from the solutions or embodiments of the problem are also included therein even if not explicitly mentioned.

According to an embodiment of the present invention for achieving such a problem, a drone body including a housing unit configured to produce and store electric energy using hydrogen; A hydrogen tank built in the upper portion of the housing and storing a predetermined amount of hydrogen fuel; A regulator connected to the hydrogen tank and reducing a supply pressure of the supplied hydrogen fuel; A stack connected to the regulator and generating electricity by inducing a reaction between hydrogen fuel and external air having been depressurized; A controller that controls whether or not the generated electricity is supplied, driving and flying the drone; And a battery in which the generated electricity is stored.

According to an embodiment of the present invention, the regulator includes: a supply line configured inside the housing unit and connected to the hydrogen tank; A decompression housing connected to one side of the supply line and supporting the supplied hydrogen fuel to be depressurized; A discharge housing configured under the pressure reducing housing and discharging the reduced pressure hydrogen fuel to the stack side; A first decompression unit configured on one surface of the discharge housing and operating the first decompression member so that the first decompression of supplied hydrogen fuel is achieved; And a second decompression unit for raising and lowering the second decompression member so that the first decompressed hydrogen fuel can be secondarily decompressed.

According to an embodiment of the present invention, the decompression housing includes a first supply hole having an end of the supply line inserted and fixed, receiving and transferring a predetermined amount of hydrogen fuel from the supply line, the first supply hole, and A first operation hole formed at a position opposite to the first operation hole for guiding the operation of the first decompression member, a second operation hole formed in the upper center and guiding the operation of the second decompression member, and the second operation hole It is formed at a position opposite to and is configured to form orthogonal to the first supply hole, characterized in that it is composed of a second supply hole for supplying the reduced pressure hydrogen fuel to the discharge housing side.

According to an embodiment of the present invention, the first pressure reducing member opens and closes the first supply hole, and includes a pressure reducing plate formed through a front central portion and configured to form a predetermined inclined surface, and an extension formed on the rear side. It is characterized in that it is composed of a transport shaft connected to the first depressurization unit and configured to move in the axial direction, and an elastic body that provides a predetermined elastic restoring force to restore the first decompression member to its original position.

According to an embodiment of the present invention, when the initial pressure of the hydrogen fuel is about 300 Bar, the regulator first decompresses to 12 Bar, and secondarily reduces the supply pressure of the first depressurized hydrogen fuel to 0.5 Bar. It is characterized by that.

According to an embodiment of the present invention, the drone body is characterized in that a buoyancy member for providing a predetermined buoyancy is further configured.

According to such an embodiment of the present invention, by maximizing the efficiency of electric energy supplied to the drone using a hydrogen fuel cell, there is an effect of improving the flight time and the mission execution radius of the drone.

In addition, according to an embodiment of the present invention, by reducing the weight of the hydrogen storage cylinder and the hydrogen fuel cell stack and stably reducing the supply pressure of hydrogen fuel supplied from the hydrogen storage cylinder in stages, the stability of the fuel supply is improved. There is an effect that can be maximized.

In addition, according to an embodiment of the present invention, a buoyancy tube filled with helium gas around the drone is further configured to extend the flight time and the possible movement distance of the drone, and to maintain a stable flight, and the descent or fall of the drone. Provides high air resistance during the event, and has the effect of securing a preparedness time due to collision.

In addition, various and beneficial advantages and effects of the present invention are not limited to the above description, and may be more easily understood in the course of describing specific embodiments of the present invention.

1 is a plan view schematically showing a drone using a hydrogen fuel cell according to an embodiment of the present invention;
2 is a front view schematically showing a drone using a hydrogen fuel cell according to an embodiment of the present invention;
Figure 3 is a block diagram schematically showing the configuration of the energy supply device for a drone using a hydrogen fuel cell according to an embodiment of the present invention.
4 is a view showing an energy supply device for a drone using a hydrogen fuel cell according to an embodiment of the present invention.
5 and 6 are diagrams showing a regulator of an energy supply device for a drone using a hydrogen fuel cell according to an embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. First, in adding reference numerals to elements of each drawing, it should be noted that the same elements are assigned the same numerals as possible even if they are indicated on different drawings. In addition, in describing the present invention, when it is determined that a detailed description of a related known configuration or function may obscure the subject matter of the present invention, a detailed description thereof will be omitted.

In addition, in describing the constituent elements of the present invention, terms such as first, second, A, B, (a) and (b) may be used. These terms are for distinguishing the constituent element from other constituent elements, and the nature, order, or order of the constituent element is not limited by the term. When a component is described as being "connected", "coupled" or "connected" to another component, the component may be directly connected or connected to that other component, but another component between each component It will be understood that elements may be “connected”, “coupled” or “connected”.

On the other hand, the drone of the present invention can be configured in various shapes or shapes, provided that it can fly in the air, and the spoke arm 120 and the propeller 130 are also 3 (tri drone), 4 (quad Drones), 6 (hexa drones), 8 (octo drones), etc. can be configured in various forms.

As shown, the drone of the present invention includes a plurality of spoke arms 102 extending radially, a propeller 104 provided at an end of the spoke arm 120 to generate lift, and the spoke arm. The arm driving unit 108 and the arm driving unit 108 for controlling the driving are mounted, and the hydrogen tank 200, the regulator 300, and the stack 400 are internally provided to produce and supply electrical energy required for driving the drone. ), the controller 500 and the battery 600 is configured to include the drone body 100 is mounted.

The drone body 100 forms an upper portion, and is configured under the storage body 112, in which a hydrogen tank 200 for storing a certain amount of hydrogen is mounted, and a regulator 300 and a stack therein. A production body 116, which is equipped with 400 and generates electric energy using hydrogen, and a control body 114 configured under the production body 116, in which the controller 500 and the battery 600 are mounted. A housing unit 110 including) is configured.

In this case, the arm driving unit 108 may be disposed between the storage body 112 and the production body 116, but is not limited thereto.

In addition, the storage body 112 is preferably configured so that the gas storage tank 708 of the buoyancy member 700 to be described later can be further mounted therein, and is configured to be spaced apart from the hydrogen tank 200 by a predetermined interval, and It is preferable to further configure a separate partition panel in the spaced space between the tanks 200 and 708.

The storage body 112 forms an upper outer surface of the housing unit 110, and the outer frame 120 and the outer frame 120 protect the hydrogen tank 200 and the gas storage tank 708 from external impact. It forms an inner surface and may be configured with a protective frame 130 that absorbs an external shock to minimize the transmission of the external shock to the hydrogen tank 200 and the gas storage tank 708.

At this time, the protection frame 130 may be made of FRP (Fiber Reinforced Plastic) or FRTP (Fiber Reinforced Thermo Plastic), and may be made of various rubbers or resins such as rubber, silicone, and polyurethane by a rotation molding method. However, it can be manufactured by various methods as long as it is possible to minimize external shock from each of the tanks 200 and 708 stored in the interior by a person skilled in the art and at the same time prevent gas from leaking to the outside. Of course.

On the other hand, the drone of the present invention uses a hydrogen fuel cell that converts chemical energy generated by a chemical reaction of oxygen into electrical energy, and supplies electric energy required for driving the drone, thereby extending the flight time and the mission execution radius of the drone. To further maximize the efficiency response of drones, a hydrogen tank 200 in which a certain amount of hydrogen fuel is stored, and a regulator 300 connected to the hydrogen tank 200 to reduce the supply pressure of the supplied hydrogen fuel, and The stack 400 is connected to the regulator 300 and generates electricity by inducing a reaction between the depressurized hydrogen fuel and external air (oxygen), the hydrogen tank 200, the regulator 300, and the stack 400. It is configured to include a controller 500 for controlling the driving and flight of the drone by controlling whether the generated electricity is supplied, and a battery 600 in which electricity generated in the stack 400 is stored.

The hydrogen tank 200 may be a hydrogen storage cylinder made of a carbon fiber storage alloy. In addition, the hydrogen tank 200 is configured to have a maximum storage capacity of 3L and a storage pressure of 350bar so that high-pressure hydrogen fuel can be stably stored.

This hydrogen tank 200 is built in one side of the storage body 112, the upper is a charging port through which hydrogen fuel is charged, and a connection connector configured at the lower end and connected to the supply line 310 of the regulator 300 Is further composed.

In addition, the hydrogen tank 200 may be composed of a multi-structure container to provide excellent durability against external shock or vibration, and is preferably composed of an inner tank, an intermediate tank and an outer tank, and an intermediate and an external tank, A vacuum forming means for forming a vacuum may be further configured between the intermediate and the inner tank.

The regulator 300 is configured in the production body 116 of the housing unit 110, and a supply line 310 connected to the hydrogen tank 200 to receive a predetermined amount of hydrogen fuel, and a supply line 310 to one side thereof. A decompression housing 320 connected and supporting the decompression of the supplied hydrogen fuel, and a discharge housing 330 configured under the decompression housing 320 and discharging the decompressed hydrogen fuel to the stack 400 side. And, a first decompression unit 340 configured on one side of the discharge housing 340 to first depressurize the supplied hydrogen fuel, and a second decompression unit 360 to secondly depressurize the hydrogen fuel. It consists of including.

The supply line 310 is made of a hollow pipe made of a multi-layered structure in which carbon fibers are embedded, and the upper end is connected to the connection connector of the hydrogen tank 200, and the lower end is a sensing unit 325 configured in the pressure reducing housing 320. ).

The decompression housing 320 includes a first supply hole 322 through which an end of the supply line 310 is inserted and fixed, and receives and transports a predetermined amount of hydrogen fuel from the supply line 310, and the first supply hole 322 ) Is formed in a position opposite to the first operation hole 324 to guide the operation of the first decompression member 340, and is formed in the upper center, the secondary to guide the operation of the secondary decompression member (360) An operation hole 326 and a second supply hole 328 formed at a position facing the secondary operation hole 326 and supplying the depressurized hydrogen fuel to the discharge housing 330 side are formed.

Here, the first and second supply holes 322 and 328 are configured to be orthogonal to each other, and the first and second operation holes 324 and 326 are also configured to be orthogonal to each other.

In addition, the first supply hole 322 and the primary operation hole 324, the supply supply hole 328 and the secondary operation hole 326 are configured to be located on the same center line, respectively.

In addition, the end of the supply line 310 is inserted and fixed in the first supply hole 322, and the supply pressure of the hydrogen fuel supplied from the supply line 310 is measured and transmitted to the controller 500, and the controller ( According to the control of 500), a sensing unit 325 may be further configured to control the supply pressure of hydrogen fuel and maintain it at a constant time.

In addition, the primary operation hole 324 guides the operation of the primary depressurization member 350 in which the sliding movement is performed according to whether the primary decompression unit 340 is operated, and when the secondary decompression is performed, the primary decompression member ( It is configured to prevent the occurrence of interference with the secondary decompression member 362 is inserted 350.

The discharge housing 330 is formed integrally with the lower portion of the pressure reducing housing 320, the discharge hole 332 located on the same center line as the second supply hole 328, and the discharge housing 330 is composed of a lower portion. , It is connected to the stack 400 and is composed of a discharge nozzle 334 for discharging the hydrogen fuel supplied to the discharge hole 332 to the stack 400. A lower portion of the is formed.

At this time, the secondary decompression member 362 moves downward to the boundary line between the second supply hole 328 and the discharge hole 332 and is formed through the second supply hole 328 and the area in which the discharge hole 332 communicates. 2nd decompression is achieved while controlling.

The primary depressurization unit 340 slides and moves the primary decompression member 350 configured in the primary operation hole 324 under the control of the controller 500, and may be configured as a conventional solenoid valve. .

The first decompression member 350 is configured to seal the first supply hole 322 according to the driving direction of the first decompression unit 340 or to open the first supply hole 322 by a certain area to reduce the supply pressure of the hydrogen fuel. .

This primary pressure reducing member 350 is formed to extend to the front side, that is, to the first supply hole 322 side, the pressure reducing plate 352 for opening and closing the first supply hole 322, and is formed to extend to the rear side, It includes a transfer shaft 354 connected to the primary decompression unit 340 and configured to move in the axial direction, and an elastic body 356 that provides a predetermined elastic restoring force to restore the primary decompression member 350 to its original position. It is composed of.

The pressure reducing plate 352 is formed through the front central portion and the lower surface is configured to form a predetermined inclined surface, and the inclined surface has a primary pressure reducing member 350 toward the primary operation hole 324 to control the supply amount of hydrogen fuel. When the pull-in operation is performed, it may serve to guide the hydrogen fuel to move toward the second supply hole 328 along the slope.

In addition, the penetrating central portion guides downward movement while the secondary decompression member 362 passes, and prevents interference with the decompression plate 352 from occurring.

In addition, the elastic body 356 provides an elastic restoring force so that the first pressure reducing member 350 is inserted into the first supply hole 322 and sealed after the supply of hydrogen fuel is completed.

On the other hand, the secondary decompression unit 360 of the present invention is detachably coupled to the upper surface of the decompression housing 320, and moves downward along the inner circumferential surface of the secondary operation hole 326 to transfer hydrogen fuel with primary decompression. It is configured to be supplied to the discharge hole 332 of the discharge housing 330 by secondary pressure reduction, and may be made of a conventional solenoid valve, and a second pressure reducing member 362 is configured to perform an elevating operation at the lower end. .

The secondary decompression member 362 is a shaft member that lifts and descends to seal the discharge hole 332 or to be opened by a certain area, and the inclined portion formed to be inclined by a predetermined angle along the circumferential surface thereof. Further configuration, is formed extending at the end of the inclined portion, to further form an extension shaft inserted into the discharge hole (332).

At this time, the extension shaft is configured such that a predetermined space is formed between the outer circumferential surface of the discharge hole 332 and the amount of hydrogen fuel supplied to the discharge hole 332 is adjusted.

The regulator 300 of the present invention is preferably made of a titanium material, and is configured to perform 2 to 3 step operations for stable decompression.

For example, when the initial pressure of the hydrogen fuel supplied to the first supply hole 322 is about 300 Bar, the supply pressure of the hydrogen fuel is reduced to about 12 Bar by the operation of the first pressure reducing member 350, and 2 It is configured to reduce the supply pressure of hydrogen fuel of about 0.5 Bar through the operation of the secondary decompression member 360 so that the supply to the discharge hole 322 is made.

The stack 400 is configured in the production body 116 of the housing unit 110, and transfers the hydrogen fuel supplied through the regulator 300 to an anode, and at the same time, an air supply device 410 such as an air blower. ), the air in the atmosphere is directly supplied to the cathode of the fuel cell.

The stack 400 is configured such that the supplied hydrogen fuel is separated into hydrogen ions and electrons in a catalyst of an anode, and the separated hydrogen ions are transferred to a cathode through a polymer electrolyte membrane. In addition, oxygen supplied to the cathode is combined with hydrogen ions that have entered the cathode through an external conductor to generate water, thereby generating electrical energy.

In addition, the stack 400 is configured to transmit the generated electrical energy to the controller 500 to be transmitted to the arm driving unit 108 and the propeller driving unit under the control of the controller 500.

In addition, the stack 400 may be configured to transmit electrical energy produced under the control of the controller 500 to the battery 600 to be stored.

The controller 500 controls whether to open or close the hydrogen tank 200 to control the supply and cut off of the supply of hydrogen fuel, and control the supply amount of hydrogen fuel according to the supply pressure of the supplied hydrogen fuel by interlocking with the sensing unit 325 Is configured to That is, the degree of opening and closing of the hydrogen tank 200 is controlled.

In addition, the controller 500 is configured to control the driving of the first decompression unit 340 and the second decompression unit 360 to control the supply pressure of hydrogen fuel so that it can always be supplied to the stack 400 at a constant pressure. .

In addition, the controller 500 controls the driving of the stack 400 to control the production of electric energy. In this case, the controller 500 may control the driving of the stack 400 according to the storage amount of the electric energy stored in the battery 600, and may control the production of electric energy during the flight of the drone.

Accordingly, unlike conventional drones that are driven using only the electric energy stored in the battery, a certain amount of electric energy can be produced even during flight, thereby improving the flight time and the mission execution radius of the drone.

In the present invention, depending on the amount of hydrogen fuel stored in the hydrogen tank 200, the flight time of the drone can be extended to 5 hours, and the radius of the mission can be extended to 60 km.

The controller 500 implements a built-in reverse protection circuit function, and a DC-DC converter 510 having a condition of using a maximum of 75V high voltage and a switching noise of 50mV or less is configured.

Accordingly, the electric energy transmitted from the stack 400 is reduced through the DC-DC converter 510 to be transmitted to the arm driving unit 108 and the propeller driving unit.

The controller 500 of the present invention configured as described above may be formed of a Trench FET Power MOSFET device and an STM32 ARM Cortex MCU having high processing speed and excellent expandability, but is not limited thereto.

On the other hand, in the present invention, a predetermined buoyancy is provided to the drone body 100 to reduce take-off weight to enable rapid initial take-off, and to further extend the flight time and movement distance of the drone, and the descent of the drone, or It is possible to further configure the buoyancy member 700 to maintain stable flight by providing high air resistance in case of a fall to secure a preparation time due to a collision.

The buoyancy member 700 has a propeller 104 located in the center, and is connected to a buoyancy tube 702 and a buoyancy tube 702 that provide a predetermined buoyancy while a certain amount of gas is filled therein, and is controlled by the controller 500 In accordance with the buoyancy control device 704 for supplying gas into the interior of the buoyancy tube 702, the buoyancy control device 704 is coupled, the inside of the spoke arm 102, the buoyancy frame 706 and the storage body ( A gas storage tank 708 that is mounted on 112, stores a gas providing buoyancy, and supplies a certain amount of gas to the buoyancy control device 704.

The buoyancy tube 702 is made in the form of a hollow donut, and the propeller 104 is located in the center, and is connected to the gas control member 740 of the buoyancy control device 704 to operate the gas control member 740 It is configured to be filled with a certain amount of gas depending on whether or not.

In the buoyancy control device 704, the upper part is connected to the buoyancy tube 702, and the lower part is connected to the gas storage tank 708 to transfer the gas supplied from the gas storage tank 708 to the buoyancy tube 702 to be filled. It is a component that makes it happen.

As shown in FIG. 7, the buoyancy control device 704 includes a gas supply housing 710, a gas supply part 720, a sealing stopper 730, a gas control member 740, an adjustment member 750, and a supply chamber. It consists of 760.

The gas supply housing 710 forms a space therein so that the gas control member 740 and the control member 750 can move up and down.

In addition, the gas supply housing 710 is equipped with the driving means 756 of the adjusting member 750 on the lower surface, and both sides of the lower side are formed through so that the elevating member 752 and the driving means 756 are coupled to each other. It is configured, and a fixing bracket 754 for supporting the rotational operation of the elevating member 752 is mounted on the inner upper surface.

In addition, a gas supply unit 720 for discharging the gas supplied into the buoyancy tube 702 according to whether the gas adjustment loop member 740 is raised or lowered is formed on the upper portion of the gas supply housing 710.

The gas supply unit 720 is configured such that the lower portion is integrally formed with the gas supply housing 710, and the upper portion passes through the buoyancy tube 702 and is located in the inner space of the buoyancy tube 702.

Such a gas supply unit 720 is configured so that the upper surface of the gas control member 740 is elevated to the lower center, and transfers the gas supplied from the gas control member 740 to the inside of the buoyancy tube 702 And, by discharging the transferred gas is configured to be filled in the inside of the buoyancy tube 702.

That is, the gas supply unit 720 has a gas transfer hole 722 through which the gas moves, and communicates with the gas transfer hole 722 along the upper circumferential surface to transfer the transferred gas into the buoyancy tube 702. A gas discharge hole 724 for discharging is formed.

At this time, the gas supply unit 720 may be configured such that the upper end thereof is sealed by the sealing stopper 730, and as the sealing stopper 730 is separated from the gas supply unit 720, the charged gas can be discharged. Will be.

The gas control member 740 is configured to perform an elevating operation in the interior of the gas supply housing 710, and the gas configured in the gas transfer hole 722 of the gas supply unit 720 and the supply chamber 760 when the gas supply housing 710 is lowered. It is configured to be connected to each of the supply lines 762, and is configured to block the connection between the gas transfer hole 722 and the gas supply line 762 during the lifting operation.

The gas control member 740 is formed on the inner upper side, and has a gas discharge hole 744 formed therethrough so as to be connected to or disconnected from the gas transfer hole 722, and a lower end thereof is formed, and a gas supply line 762 ) And the gas supply hole 742 is formed to be connected to or disconnected from the connection, and the upper end thereof is connected to the gas discharge hole 744.

In addition, the gas control member 740 is configured on both sides of the outer surface or the outer circumferential surface, respectively, and the adjusting member 750 for raising and lowering the gas control member 740 is configured.

The adjusting member 750 may be formed of a conventional panel, and has a shape corresponding to each other on both sides of the gas adjusting member 740.

The adjusting member 750 has a spiral groove formed on the outer circumferential surface, and is coupled to the upper inner wall surface of the gas supply housing 710 and the elevating member 752 which rotates by receiving the rotational force, and the elevating member ( The fixing bracket 754 to which the 754 is rotatably coupled, the lower end of the elevating member 752 is connected, and the driving means 756 and the adjusting member ( 750), the elevating member 752 penetrates through the central part, and a helical protrusion corresponding to the elevating member 752 is formed on the inner circumferential surface to control gas by receiving the rotational force of the elevating member 752 It is configured to include an operation block 758 for elevating the member 740.

The supply chamber 760 is formed integrally with the lower part of the gas supply housing 710, forms an open groove in which the upper part is opened, and the lower part of the gas control member 740 is configured to enable an elevating operation, and one side As a result, a gas supply line 762 through which a certain amount of gas is introduced is formed by being connected to the gas storage tank 708.

Accordingly, when a certain amount of gas is supplied from the gas storage tank 708 under the control of the controller 500, the control member 750 operates to lower the gas control member 740 to control the gas supply line 762 and the gas. By allowing the member 740 to be connected, the supplied gas is transferred to the buoyancy tube 702 to be filled, so that a certain buoyancy can be provided to the drone even if a separate gas filling operation is not performed. It is possible to maintain constant buoyancy as gas can be charged even during flight.

The terms such as "include", "consist of" or "have" described above mean that the corresponding component may be embedded, unless otherwise specified, and thus other components are not excluded. It should be construed as being able to further include other components, and all terms including technical or scientific terms are generally understood by those of ordinary skill in the technical field to which the present invention belongs, unless otherwise defined. Has the same meaning as

In addition, the above description is merely illustrative of the technical idea of the present invention, and those of ordinary skill in the art to which the present invention pertains will be able to make various modifications and variations without departing from the essential characteristics of the present invention. . Accordingly, the embodiments disclosed in the present invention are not intended to limit the technical idea of the present invention, but to explain the technical idea, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed by the following claims, and all technical ideas within the scope equivalent thereto should be construed as being included in the scope of the present invention.

100: drone body 110: housing
120: outer frame 130: protection frame
200: hydrogen tank 300: regulator
310: supply line 320: pressure reducing housing
330: discharge housing 340: primary pressure reducing part
350: primary decompression member 360: secondary decompression unit
400: stack 500: controller
600: battery 700: buoyancy member
710: gas supply housing 720: gas supply
730: sealing plug 740: gas control member
750: adjustment member 760: supply chamber

Claims (6)

A drone body including a housing unit configured to produce and store electric energy using hydrogen;
A hydrogen tank built in the upper part of the housing and storing a predetermined amount of hydrogen fuel;
A regulator connected to the hydrogen tank and reducing a supply pressure of the supplied hydrogen fuel;
A stack connected to the regulator and generating electricity by inducing a reaction between hydrogen fuel and external air, which has been depressurized;
A controller that controls whether or not the generated electricity is supplied, driving and flying the drone; And
A battery in which generated electricity is stored;
Including,
The regulator,
A supply line configured inside the housing and connected to the hydrogen tank;
A decompression housing connected to one side of the supply line and supporting the supplied hydrogen fuel to be depressurized;
A discharge housing configured under the decompression housing and discharging the depressurized hydrogen fuel to the stack side;
A first decompression unit configured on one surface of the discharge housing and operating the first decompression member so that the first decompression of the supplied hydrogen fuel is achieved; And
A second decompression unit for raising and lowering the second decompression member so that the first decompressed hydrogen fuel can be secondarily decompressed;
Including,
The pressure reducing housing,
A first supply hole in which an end of the supply line is inserted and fixed, and receives and transports a predetermined amount of hydrogen fuel from the supply line;
A first operation hole formed at a position opposite to the first supply hole and guiding the operation of the first pressure reducing member,
A secondary operation hole formed in the upper center and guiding the operation of the secondary decompression member,
A hydrogen fuel cell, characterized in that it is formed at a position opposite to the secondary operation hole, is configured to form orthogonal to the first supply hole, and is configured as a second supply hole for supplying depressurized hydrogen fuel to the discharge housing side. Drone energy supply device using.
delete delete The method of claim 1,
The primary pressure reducing member,
A pressure-sensitive plate configured to open and close the first supply hole, and formed through the front central portion and configured to have a lower surface forming a predetermined inclined surface;
A transfer shaft extending on the rear side and configured to be connected to the primary depressurization unit so as to move in the axial direction;
An elastic body that provides a predetermined elastic restoring force to restore the primary pressure reducing member to its original position
Drone energy supply device using a hydrogen fuel cell, characterized in that consisting of.
The method of claim 1,
The regulator,
When the initial pressure of hydrogen fuel is 300 Bar, the first pressure is reduced to 12 Bar and the second pressure is reduced to 0.5 Bar. .
The method of claim 1,
An energy supply device for a drone using a hydrogen fuel cell, characterized in that the drone body further includes a buoyancy member providing a predetermined buoyancy.

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