WO2020046011A1 - Structure de montage de module pour un drone à bloc d'alimentation de pile à combustible intégré - Google Patents

Structure de montage de module pour un drone à bloc d'alimentation de pile à combustible intégré Download PDF

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Publication number
WO2020046011A1
WO2020046011A1 PCT/KR2019/011077 KR2019011077W WO2020046011A1 WO 2020046011 A1 WO2020046011 A1 WO 2020046011A1 KR 2019011077 W KR2019011077 W KR 2019011077W WO 2020046011 A1 WO2020046011 A1 WO 2020046011A1
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WIPO (PCT)
Prior art keywords
stack
disposed
case
drone
fuel cell
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Application number
PCT/KR2019/011077
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English (en)
Korean (ko)
Inventor
성명훈
심규정
Original Assignee
(주)두산 모빌리티 이노베이션
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Publication of WO2020046011A1 publication Critical patent/WO2020046011A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/16—Flying platforms with five or more distinct rotor axes, e.g. octocopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B64D37/04—Arrangement thereof in or on aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/32—Supply or distribution of electrical power generated by fuel cells
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/08—Mounting arrangements for vessels
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/24—Grouping of fuel cells, e.g. stacking of fuel cells
    • H01M8/2465—Details of groupings of fuel cells
    • H01M8/2484—Details of groupings of fuel cells characterised by external manifolds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/005—Fuel cells
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0189—Planes
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2250/00—Fuel cells for particular applications; Specific features of fuel cell system
    • H01M2250/20—Fuel cells in motive systems, e.g. vehicle, ship, plane
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

Definitions

  • the present invention relates to a module mounting structure of a fuel cell power pack integrated drone, and more particularly, to a balanced mounting structure of a fuel cell related module that is integrally coupled to the inside of a drone.
  • Drone is a general term for an unmanned drone. Radio-controlled drones were initially used militaryly to intercept air force aircraft, AA guns, or missiles.
  • drone operation is whether it can be operated for a long time.
  • Most drones on the market today do not have long flight times.
  • the drone must be operated by driving a plurality of propellers because a lot of power is consumed to drive the propellers.
  • the size and weight of the battery may increase the size and weight of the drone, which may be inefficient.
  • payload values should be considered in the case of delivery-related drones, and the size and weight of the drone itself is one of the important factors in drone operation, and it is limited to increase the general battery in the market for long-term operation. There is.
  • An object of the present invention is to supply power from the fuel cell to reduce the weight and at the same time to operate the drone for a long time, improve the air circulation structure to maintain the stable operating environment temperature of the stack and at the same time contribute to the lift capacity of the drone, tilting Increased user convenience to easily mount and detach the gas tank through a long removable structure,
  • the present invention provides a module mounting structure of a fuel cell power pack integrated drone that achieves an overall weight balance by implementing a balanced fuel cell module mounting structure and enables stable drone startup.
  • the present invention for achieving the above object relates to a module mounting structure of the fuel cell power pack integrated drone, the module frame; A tank accommodating part formed at a central portion of the module frame and equipped with a gas tank; Stack portion accommodating portions formed at both sides of the module frame and having a stack portion; And a manifold accommodating part formed on a front surface of the module frame and having a manifold part connecting the regulator valve and the stack part mounted to the gas tank.
  • the stack portion accommodating portion includes: a first accommodating surface on which a first fastening unit for fixing one side of the stack portion is disposed; And a second receiving surface formed at a right angle with respect to the first receiving surface, and having a second fastening unit fixing the lower surface of the stack portion.
  • the stack portion accommodating portion may be disposed to be inclined at a predetermined angle range at both sides of the module frame with respect to the vertical line H1 of the case.
  • the first receiving surface may be inclined while looking outwardly downward of the module frame with respect to the vertical line H1 of the case.
  • the embodiment of the present invention includes a fixed panel disposed on both sides of the case, the opening window is formed to be connected to one surface of the stack portion, wherein the fixed panel is inclined angle range of the stacking surface facing the first receiving surface It can be arranged as.
  • the embodiment of the present invention may be disposed along the circumference of the opening of the fixing panel, the sealing unit of the elastic material is in close contact along the circumference of the first receiving surface of the stack portion;
  • the embodiment of the present invention is connected to the air outlet of the case, the duct is disposed inside a plurality of blinds; And an airtight housing disposed between the duct and the opening window of the fixing panel.
  • the manifold receiving portion the first bracket plate protruding toward the front portion of the module frame; And a second bracket plate spaced apart from the first bracket plate at a predetermined interval and protruded toward the front surface of the module frame.
  • the embodiment of the present invention may include; a receiving pad of elastic material disposed along the inner circumference of the tank accommodating portion so that the gas tank is in close contact with the gas tank.
  • the embodiment of the present invention may include a tank fixing bar disposed inside the rear portion of the case, the grip portion of the tongs shape is inserted into the tank handle of the gas tank.
  • the embodiment of the present invention may include a control panel accommodating portion formed on the front side of the module frame, the lower side of the manifold receiving portion, the control panel for controlling the regulator valve and the stack of the gas tank;
  • the embodiment of the present invention may include a plurality of auxiliary power brackets disposed at positions symmetrical with each other on both sides of the front portion of the case and mounted with an auxiliary power supply.
  • the present invention is a drone driven by a fuel cell power pack, and has a superior power to weight ratio compared to a general battery applied to a drone in the market, enabling long-term operation of the drone and increasing payload value of the drone.
  • the present invention is designed to streamline the case to minimize the air resistance that can be generated according to the various directions of the drone.
  • the present invention is to arrange the hydrogen tank in the center side of the case, by placing a plurality of stacks in positions symmetrical to both sides of the hydrogen tank inside the case, to achieve a weight balance, it is possible to achieve stable starting operation of the drone have.
  • the present invention is arranged so that the lid is placed on the upper surface of the case, the lid is opened so that the hydrogen tank is inclinedly inserted into the pressurized manifold block.
  • the user may insert the hydrogen tank into the manifold block, and then lightly press the rear part of the hydrogen tank downward to mount the hydrogen tank.
  • the regulator valve of the hydrogen tank when the hydrogen tank is inserted into the case by arranging the pressurized manifold block, the regulator valve of the hydrogen tank is placed in a pressurized state and is firmly coupled to the manifold block, Leakage can be shut off.
  • the present invention can be arranged in the manifold block by controlling the flow rate of the hydrogen gas supplied to the stack by placing an electronically controlled flow control valve, such as a solenoid valve, which is on / off the fuel cell at the timing desired by the user This allows the fuel cell to shut down in an emergency.
  • an electronically controlled flow control valve such as a solenoid valve
  • the present invention is a simple operation of the user inserts the regulator valve connected to the hydrogen tank in the manifold block, the opening and closing bar disposed inside the regulator valve is pressed by the pressing portion formed in the manifold block, the gas flow path is communicated It has a structure, which improves work convenience.
  • the present invention is connected to the gas supply pipe branching from the manifold block to the top of the stack, when the condensed water generated in the electrochemical reaction between hydrogen gas and air moves downward by gravity, hydrogen supplied to the stack from the gas supply pipe By preventing the inflow of gas to occur, the efficiency of chemical reaction in the stack was increased.
  • the present invention disposed condensate discharge portion at the bottom of the front window and the bottom of the rear window formed in the lower portion of the case.
  • the condensate condensed inside the case and the condensate discharged from the stack are collected in the discharge and discharged to the outside. This keeps the interior of the case relatively clean, and can prevent exposure to condensate from controls such as circuit boards.
  • the control device can of course be insulated or waterproofed.
  • the drain pipe is disposed so that the drain pipe flows along a leg disposed at the bottom of the case, thereby preventing indiscriminate discharge of condensate.
  • the present invention by placing a hot wire coil, an ultrasonic humidification sensor or a natural convection humidifier on the sump, to evaporate the condensate collected in the sump, to create a humidification environment for the operation of the stack, thereby the electrochemical reaction in the stack By promoting the efficiency of the fuel cell can be improved.
  • the present invention is to arrange a secondary battery, such as a lithium ion battery, and to control the power to be supplied in parallel with the fuel cell, to enable a stable power supply to the drone.
  • a secondary battery such as a lithium ion battery
  • auxiliary batteries were arranged in symmetrical positions on both sides of the case with respect to the hydrogen tank, and even if one of the auxiliary batteries failed, the remaining auxiliary batteries enabled stable operation of the drone.
  • the present invention is disposed in the air inlet on both sides of the case, the air inlet at the bottom of the front and rear of the case, respectively, the fan is disposed on the air outlet, the fan is driven, through the bottom of the front and rear
  • the introduced air was allowed to pass through the stack, and the inside of the case was formed in a negative pressure state or a low pressure state, thereby enabling smooth supply and supply of air supplied to the stack.
  • the controller for controlling the fuel cell can adjust the flow rate of air supplied to the stack through the rotational speed control of the fan motor, thereby enabling efficient operation of the fuel cell according to the operating environment and conditions.
  • the present invention by placing a circuit board on the air inlet, the heated circuit board is naturally cooled by the outside air during operation, thereby improving the cooling effect of the circuit board.
  • the present invention constitutes a sealed housing between the stack and the air outlet, and by forming a recirculation flow path on the sealed housing, a part of the air passing through the stack is recycled into the case through the recirculation flow path, the sudden The operating temperature of the stack was prevented.
  • the internal temperature of the case can maintain the optimized temperature of the fuel cell.
  • the present invention is to arrange a plurality of blinds on the air outlet, and to arrange each of the blinds to be inclined or curvature downwards to be relatively matched with the air flow direction by the propeller of the drone, to help the lift composition of the drone It is designed to prevent rain or moisture from entering the system even in snow and rainy environments.
  • the present invention is to arrange the handle in the hydrogen tank to easily handle the hydrogen tank, and to arrange the lid (lid) on the upper part of the case to facilitate the internal operation between maintenance / maintenance for user convenience.
  • the fuel cell power pack integrated drone according to the present invention may be partially made of reinforced plastics, carbon, titanium, aluminum, etc., and thus, may reduce weight, improve payload value, and reduce power consumption.
  • FIG. 1 is a perspective view of a fuel cell power pack integrated drone of the present invention
  • Figure 2 is a plan view of the present invention fuel cell power pack integrated drone.
  • Figure 3 is a side view of the present invention fuel cell power pack integrated drone.
  • Figure 4 is a front view of the present invention fuel cell power pack integrated drone.
  • FIG. 5 is a rear view of the present invention fuel cell power pack integrated drone.
  • Figure 6 is a bottom view of the fuel cell power pack integrated drone of the present invention.
  • Figure 7 is a plan view showing the inside in the open state the lid of the present invention fuel cell power pack integrated drone.
  • Figure 8 is a plan view showing the internal structure of the fuel cell power pack integrated drone of the present invention.
  • Figure 9 is a side view showing the internal structure of the present invention fuel cell power pack integrated drone.
  • Figure 10 is a front view showing the internal structure of the present invention fuel cell power pack integrated drone.
  • Figure 11 is a rear view showing the internal structure of the present invention fuel cell power pack integrated drone.
  • Figure 12 is a bottom view showing the internal structure of the fuel cell power pack integrated drone of the present invention.
  • Figure 13 is a rear perspective view showing the internal structure of the present invention fuel cell power pack integrated drone.
  • Figure 14 is a front perspective view showing the interior of the fuel cell power pack integrated drone of the present invention.
  • 15 is a schematic sectional view showing a first embodiment of the inventors' discharge portion
  • 16 is a schematic cross-sectional view showing a second embodiment of the discharge unit of the present inventors.
  • 17 is a plan view showing an air circulation control structure in the present invention fuel cell power pack integrated drone.
  • FIG. 18A is a sectional view taken along line P-P in FIG. 27; FIG.
  • FIG. 18B is an enlarged view of the portion M posted in FIG. 18A.
  • FIG. 18B is an enlarged view of the portion M posted in FIG. 18A.
  • 19A is a cross-sectional view taken along line B-B in FIG.
  • FIG. 19B is an enlarged view of the L portion posted in FIG. 19A.
  • FIG. 19B is an enlarged view of the L portion posted in FIG. 19A.
  • 20 is a plan view showing the gas tank mounting detachment tilting and gas supply structure in the fuel cell power pack integrated drone of the present invention.
  • FIG. 21 is an enlarged view of a portion N posted in FIG. 20.
  • FIG. 21 is an enlarged view of a portion N posted in FIG. 20.
  • Figure 22 is a perspective view showing the structure of the pressing unit of the present invention.
  • Figure 23 is a cross-sectional view of the gas supply unit structure of the present invention.
  • FIG. 24 is an enlarged view of a portion H posted in FIG. 24.
  • 25 is a cross-sectional view showing an arrangement of the flow control valve of the present invention.
  • 26 is a perspective view of another embodiment of the present invention fuel cell power pack integrated drone.
  • 27 is a plan view of another embodiment of the present invention fuel cell power pack integrated drone.
  • 28 is a side view of another embodiment of the present invention fuel cell power pack integrated drone.
  • 29 is a front view of another embodiment of the present invention fuel cell power pack integrated drone.
  • FIG. 30 is a rear view of another embodiment of the present invention fuel cell power pack integrated drone.
  • Figure 31 is a bottom view of another embodiment of the present invention fuel cell power pack integrated drone.
  • FIG. 1 is a perspective view of a fuel cell power pack integrated drone of the present invention
  • FIG. 2 is a plan view of a fuel cell power pack integrated drone of the present invention
  • FIG. 3 is a side view of a fuel cell power pack integrated drone of the present invention
  • FIG. 4 is a fuel cell power pack of the present invention
  • 5 is a rear view of the fuel cell power pack integrated drone of the present invention
  • FIG. 6 is a bottom view of the fuel cell power pack integrated drone of the present invention.
  • FIG. 7 is a plan view showing the interior of the fuel cell power pack integrated drone of the present invention in an open state
  • Figure 8 is a plan view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 9 is a fuel cell of the present invention
  • Figure 10 is a side view showing the internal structure of the power pack integrated drone
  • Figure 10 is a front view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 11 is a rear view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 12 is a bottom view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 13 is a rear perspective view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 14 is a rear view of the fuel cell power pack integrated drone of the present invention.
  • FIG. 15 is a schematic sectional view showing a first embodiment of the discharge unit of the present invention
  • FIG. 16 is a schematic sectional view showing a second embodiment of the discharge unit of the present invention.
  • the fuel cell power pack integrated drone 100 of the present invention may include a case 200, a module frame 900, a gas tank 300, and a fuel cell unit 400.
  • the fuel cell power pack integrated drone 100 of the present invention may be a device that is integrally mounted inside a flying object such as a drone to supply power. Therefore, it can be configured with an optimal design for flying on a drone.
  • the outer shape of the case 200 may be a flying object such as a drone. Accordingly, the wing 210 may be disposed along the outer circumference of the case 200.
  • the wing 210 may include a wing beam 211, a drive motor 212 and a propeller 213.
  • the wing beams 211 may be disposed in plural numbers at predetermined intervals along the outer circumference of the case 200, and may be implemented to protrude in an outward direction of the case 200.
  • the drive motor 212 may be disposed at an end of the wing beam 211, and the propeller 213 may be connected to the rotation shaft of the drive motor 212.
  • the driving motor 212 may receive power from the fuel cell unit 400 to rotate the propeller 213.
  • case 200 and the wing 210 may have an overall appearance in a streamlined shape so as to minimize air resistance during starting.
  • the outer shape of the case 200 may be determined in a form corresponding to the arrangement structure of the fuel cell unit 400 disposed inside the case 200. Even at this time, each corner may be processed into a smooth streamline to reduce air resistance.
  • FIG. 26 it may be adopted as a case 200 having a round shape to minimize air resistance in all directions during starting.
  • case 200 may be made of a material such as reinforced plastic, carbon, titanium, aluminum, etc. to reduce weight.
  • a lead 204 may be disposed above the case 200.
  • the lid 204 may be provided with a lead handle for opening and closing the lid 204. The user may hold the lid handle and open the lid 204 to maintain various parts disposed in the case 200.
  • the user can open and detach the gas tank 300 by opening the lid 204.
  • Leg portion 250 may be disposed below the case 200 to take off and land of the case 200.
  • the leg part 250 may include a first leg 251, a second leg 253, and a seating beam 255.
  • the first leg 251 is arcuately disposed at the lower side of the front window 221 disposed below the front part 201 of the case, and the second leg 253 is lower than the rear part 203 of the case.
  • the lower portion of the rear window 222 is disposed in the arcuate may be disposed.
  • the seating beam 255 may be configured in a straight line connecting end portions of the first and second legs 251 and 253 so that the drone may be stably seated on the ground.
  • the module frame 900 may be disposed inside the case 200 and may be a portion in which the fuel cell unit 400 and the gas tank 300 are mounted.
  • the structure of the module frame 900 will be described later.
  • the gas tank 300 may be mounted to the module frame 900, and may be connected to the fuel cell unit 400 to supply fuel gas.
  • a tank handle 301 may be disposed at a rear end of the gas tank 300 so that a user may easily handle the gas tank 300.
  • 301 may be formed in a disk shape a plurality of holes that the user's finger can hold.
  • the tank fixing bar 241 may be disposed inside the rear portion 203 of the case 200.
  • the tank fixing bar 241 may be formed with a grip portion 242 of the tongs shape so that the tank handle 301 can be fitted. When the user grasps the tank handle 301 and descends downward, the tank handle 301 is fitted to the grip part 242 of the tank fixing bar 241 to be fixed.
  • the gas filled in the gas tank 300 may be hydrogen gas.
  • a power switch 820 for operating the fuel cell unit 400 disposed inside the case 200 may be disposed at the rear portion 203 of the case 200. have. The user may simply click the power switch 820 to determine whether the fuel cell power pack integrated drone 100 is operated.
  • a fuel state display window 810 may be arranged to be connected to the gas tank 300 and to display a gas remaining amount of the gas tank 300. The user may check the remaining amount of gas by recognizing the color of the fuel state display window 810.
  • the fuel state display window 810 may be in the form of an indicator LED, but is not limited thereto.
  • the remaining gas amount may be 80 to 100%, and in the case of yellow, the remaining gas amount may be 40 to 70%. Insufficient 0 to 30% can indicate a state requiring gas filling. Other settings are possible.
  • a front window 221 and a rear window 222 may be disposed on the front part 201 and the rear part 203 of the case 200, and the front window 221 may be disposed.
  • the rear window 222 may be an air inlet 220 through which external air is introduced into the case 200.
  • the front window 221 may be disposed to be inclined in one direction at the bottom of the front part 201 of the case, and the rear window 222 is opposite to the front window 221 at the bottom of the rear part 203 of the case. It may be disposed inclined in the direction.
  • This inclined arrangement allows the amount of air flowing from the front window 221 to increase by the starting speed when the drone starts up in the front direction, and on the contrary, when the drone starts up in the rear direction, the rear window goes down by the starting speed.
  • the amount of air introduced from 222 may be increased.
  • the window blinds 221a and 222a disposed in a plurality of rows are formed in the front window 221 and the rear window 222, and foreign materials having relatively bulky volume may be prevented from flowing into the case 200. .
  • a filter may be disposed on the front window 221 and the rear window 222 to effectively remove foreign matter contained in the air.
  • the case 200 may be disposed in the plurality of air inlets 220, and the position of the air inlet 220 is not limited on the case 200.
  • the air outlet 230 having a plurality of blinds 740 may be disposed in the side portion 202 of the case 200, and the air introduced from the air inlet 220 may be disposed in the case 200. After circulating the inside of the 200, it may go through a flow process discharged to the outside through the air outlet 230.
  • the fuel cell unit 400 may be disposed on the module frame 900 in a weight balance in the case 200. Since the fuel cell power pack is mounted on a flying object such as a drone to fly together, the case 200, the module frame 900, the gas tank 300, and the fuel cell unit 400 may not interfere with the drone's maneuverability. Can be placed in an overall weight balance.
  • the fuel cell unit 400 may include a manifold unit 420 and a stack unit 410.
  • the manifold portion 420 may be a portion connected to the regulator valve 320 coupled to the gas tank 300.
  • the stack 410 is connected to the manifold 420 and may receive gas from the manifold 420.
  • the manifold portion 420 and the stack portion 410 of the case 200 with respect to the second direction V2 of the case 200 based on the center line P of the first direction V1 of the case 200. It can be arranged in a weight balance.
  • the manifold portion 420 may be disposed on the front portion of the module frame 900 in the inside of the case 200, the plurality of the stack portion 410 is disposed, the case 200 It may be disposed at positions symmetrical to each other on both sides of the module frame 900 in the interior.
  • the gas tank 300 and the plurality of stack portions 410 may be formed based on the center line P of the first direction V1 of the case 200.
  • the module frame 900 may be arranged to achieve a weight balance with respect to the second direction V2 of the case 200, that is, both sides.
  • the gas tank 300 is disposed on the center line P of the first direction V1 of the case 200, and the plurality of stack portions 410 are the case 200.
  • the inner both sides of the gas tank 300 with respect to each other may be disposed in a position symmetrical with respect to.
  • the gas tank 300 is disposed in the tank accommodating part 910 formed at the inner center of the case 200, that is, the central part of the module frame 900, and the stack part 410 is composed of two, As shown in FIG. 7, the gas tanks 300 may be disposed at the same positions in the stack receiving portions 920 formed at both sides of the module frame 900. Accordingly, the fuel cell power pack integrated drone 100 of the present invention may have a weight balance in the second direction V2 based on the center line P of the first direction V1.
  • This weight balance arrangement can reduce the influence on drone maneuver by minimizing the variation of the center of gravity of the drone when the fuel cell power pack is integrated with the drone.
  • the auxiliary power source 500 is disposed in the auxiliary power bracket 510 provided inside the case 200, and is connected to the fuel cell unit 400 in parallel and controlled to supply power to the drone. Can be.
  • the fuel cell unit 400 and the auxiliary power source unit 500 are connected in parallel on the control panel 830, thereby selectively supplying power to the drone.
  • the auxiliary power supply 500 may supply the insufficient output in parallel.
  • the auxiliary power supply 500 supplies emergency power to stop the drone in flight. It can prevent.
  • the auxiliary power supply unit 500 may be provided in plural numbers.
  • the auxiliary power supply unit 500 may be disposed on the basis of the center line P of the first direction V1 of the case 200 so as not to interfere with the maneuvering of the flying object.
  • the front parts 201 of the case 200 may be disposed at positions symmetrical with each other.
  • the auxiliary power supply unit 500 includes a plurality of stacking units.
  • the stack unit 410 constituting the fuel cell unit 400 also includes a plurality of stacking units.
  • the plurality of auxiliary power supply units 500 are disposed in a weight balance at positions symmetrical with respect to the inside of the case 200 with respect to the center line P of the first direction V1 of the case 200.
  • the stack unit 410 and the auxiliary power supply unit 500 are each composed of two, and each of the stack unit 410 and the auxiliary power unit 500 is symmetrical with respect to the inside of the case 200 based on the center line P of the first direction V1. Placed in a position to achieve a weight balance can be seen that.
  • the gas tank 300, the manifold portion 420, and the control panel 830 are disposed on the center line P in the first direction V1. This may be arranged to achieve a weight balance between the front part 201 of the case 200 and the rear part 203 of the case 200 along the center line P of the first direction V1.
  • the stack unit 410 and the auxiliary power supply unit 500 are disposed at symmetrical positions on both sides of the center line P of the first direction V1 in the case 200 to achieve a weight balance, and the gas
  • the tank 300, the manifold 420, and the control panel 830 are located on the center line P of the first direction V1 in the case 200 and are located at the front part 201 of the case 200.
  • the rear surface 203 of the case 200 may be disposed in a balance of weight.
  • the stack part 410, the auxiliary power supply part 500, the gas tank 300, the manifold part 420, and the control panel 830 are generally disposed inside the case 200. Since the weight balance is arranged in both directions V1 and V2, even if the fuel cell power pack is mounted on the drone, the weight balance of the drone can also be maintained without being biased to either side.
  • the weight balance arrangement of the above components contributes to the smooth running of the drone by minimizing the influence on the drone's starting environment.
  • the discharge part 600 is formed at an inner lower surface of the case 200 and is external from the inside of the case 200 or the condensed water discharged from the stack 410.
  • the condensate generated by condensation of air may be collected and discharged.
  • the discharge part 600 may include a first drain passage 620, a first drain tube 621, a second drain passage 630, and a second drain tube 631.
  • the first drain passage 620 is disposed in a recessed shape in the longitudinal direction of the front window 221 at the bottom surface of the front window 221, and collects condensed water condensed at the inner front part of the case 200. It may be a part.
  • the first drain pipe 621 may be connected to lower ends of both ends of the first drain channel 620 so that the condensed water collected in the first drain channel 620 is discharged to the bottom of the drone.
  • the first drain pipe 621 is connected to the lower end of the first drain channel 620 and has an arch shape along the first leg 251. It can be arranged as.
  • the condensed water collected into the first drain passage 620 moves to the seating beam 255 along the first drain pipe 621 and is disposed outside.
  • the second drain passage 630 is disposed in a recessed shape in the longitudinal direction of the rear window 222 at the bottom surface of the rear window 222 and collects condensed water condensed at the inner rear part of the case 200. It may be a part.
  • the second drain pipe 631 may be connected to lower ends of both ends of the second drain channel 630 so that the condensed water collected in the second drain channel 630 is discharged to the lower part of the drone.
  • the second drain pipe 631 is connected to a lower end of the second drain passage 630 and has an arch shape along the second leg 253. It can be arranged as.
  • the condensed water collected into the second drain passage 630 is moved to the seating beam 255 along the second drain pipe 631 and then discharged to the outside.
  • the first and second drain pipes 621 and 631 may be disposed along the leg part 250 to prevent indiscriminate discharge of condensed water from the lower part of the drone.
  • the discharge part 600 is disposed in the first drain passage 620 and / or the second drain passage 630, and the first and second drain passages 620 and 630. It may further include a humidifying unit 640 to evaporate the condensed water collected in to form a humidifying environment in the case 200.
  • the stack of a fuel cell may promote the electrochemical reaction of oxygen and hydrogen in a humid environment rather than in a dry environment, thereby increasing the power generation efficiency of the fuel cell.
  • the humidifying unit 640 is arranged in the first and second drain passages 620 and 630 to evaporate the condensate collected again to create a humidifying environment in which the electrochemical reaction may be promoted in the stack 410.
  • the stack unit 410 contributes to increasing the power generation efficiency.
  • the humidifying unit 640 may be configured in the form of a hot wire coil as shown in FIG. Hot wire coils may be disposed on the first and second drain passages 620 and 630, and the condensed water collected in the first and second drain passages 620 and 630 may receive heat from the hot coil and evaporate to form a humidified environment.
  • the control of the heating coil may be controlled by the control panel 830, and the power supplied to the heating coil may be supplied by the stack unit 410 or the auxiliary power supply unit 500.
  • the humidifying unit 640 may be an ultrasonic humidification sensor as shown in FIG.
  • Ultrasonic humidification sensors may be disposed on the first and second drain passages 620 and 630, and the condensed water collected in the first and second drain passages 620 and 630 may become steam by vibration generated by ultrasonic waves.
  • the inside of the) can be created as a humid environment.
  • the control of the ultrasonic humidification sensor is possible in the control panel 830, the power supplied to the ultrasonic humidification sensor may be supplied from the stack unit 410 or the auxiliary power supply unit 500.
  • the humidifying unit 640 may be a natural convection humidifier.
  • 17 is a plan view illustrating an air circulation control structure in a fuel cell power pack integrated drone according to the present invention.
  • FIG. 18A is a cross-sectional view taken along line P-P shown in FIG. 27, and FIG. 18B is an enlarged view of a portion M shown in FIG. 18A.
  • FIG. 19A is a cross-sectional view taken along line B-B shown in FIG. 2, and FIG. 19B is an enlarged view of a portion L shown in FIG. 19A.
  • one embodiment of the air circulation control structure of the fuel cell power pack integrated drone 100 of the present invention is the air inlet 220, air outlet 230 and air circulation control It may be configured to include a unit 700.
  • the air inlet 220, the air outlet 230, and the air circulation control unit 700 may be disposed in the case 200 of the fuel cell power pack integrated drone 100.
  • the air inlet 220 may be disposed below the front part 201 or the rear part 203 of the case 200, and may be a part into which outside air is introduced.
  • the front window 221 in which the plurality of window blinds 221a are disposed in the front part 201 of the case 200 and the rear window 222 in which the plurality of window blinds 222a are disposed in the rear part 203. ) May be an air inlet 220.
  • the position of the air inlet 220 is not limited on the case 200.
  • control panel 830 is disposed above the front window 221, which is one of the air inlets 220, inside the case 200, and configured to be cooled by the air introduced from the front window 221. Can be. That is, when the fuel cell is operated, the circuit disposed in the control panel 830 is heated. In this case, the circuit is arranged to be naturally cooled by the flow of air introduced from the outside.
  • the position of the control panel 830 is not limited to the upper side of the front window (221).
  • the air outlet 230 may be spaced apart from the air inlet 220 in the case 200, and may be a portion from which air introduced into the case 200 is discharged. In this case, the air outlet 230 may be disposed adjacent to the stack 410.
  • the module frame 900 may be disposed inside the case 200.
  • the tank accommodating part 910 may be formed at the central side of the module frame 900, and the gas tank 300 may be disposed.
  • the stack part accommodating part 920 may be formed at both sides of the module frame 900, and a plurality of stack parts 410 may be disposed. Accordingly, the air outlet 230 may be disposed at the side portion 202 of the case 200 adjacent to the stack 410.
  • the air flows from the air inlet 220 and passes through the stack 410 to be guided by the air circulation control unit 700 to be discharged to the air outlet 230.
  • the air circulation control unit 700 is disposed in association with the stack part 410 and the air outlet 230, and passes through the stack part 410 in the case 200 to the air outlet. It may be provided to adjust the flow of air flowing in the direction (230).
  • the air circulation control unit 700 may include a sealed housing 710, a fan member 730, a recirculation flow path 720 and a blind 740.
  • the airtight housing 710 has a duct disposed around the one surface of the stack 410 and the air outlet 230 so that air passing through the stack 410 flows in the direction of the air outlet 230. It may be disposed sealing the outer periphery of 760.
  • it may be composed of a plurality of plates of the hermetic housing 710, wrap around one surface of the stack portion 410, one plate is connected to the outer circumference of the duct 760 may form a sealed space have.
  • the air passing through the stack 410 flows only in the direction of the duct 760 of the air outlet 230.
  • a fixing panel 713 may be disposed to connect and fix the side part of the case 200 and the sealing housing 710 so that the position of the sealing housing 710 is fixed inside the case 200.
  • the fixing panel 713 may have an opening window 713a having a rectangular cross-sectional shape connecting one surface of the stack part 410 and one surface of the sealed housing 710.
  • the sealing unit 714 may be disposed along a circumference of the opening window 713a facing the stack 410.
  • the sealing unit 714 is in close contact with the circumference of one surface of the stack portion 410, so that the air passing through the stack portion 410 may flow in the sealed housing 710 without leaking.
  • the fan member 730 may be disposed to be connected to the duct 760 of the air outlet 230.
  • the air inside the case 200 is discharged to the outside through the air outlet 230, the interior of the case 200 relative to the external environment The negative pressure or low pressure is formed.
  • the present invention operates the fan member 730 to forcibly create an air circulation environment inside the case 200.
  • the fan member 730 is disposed in a space formed by the duct 760 of the air outlet 230, the sealing housing 710, and the stack 410, and thus, the fan member 730 may not be operated. Air discharge by adjusting the air flow environment to force the air introduced into the air inlet 220 to pass through the stack 410.
  • the user may control the rotational speed of the fan member 730 with the controller to adjust the amount of air introduced into the case 200 by the pressure difference. This ultimately controls the amount of air supplied to the stack 410, which may be a means of controlling the output of the stack 410.
  • the fan member 730 may include a fan bush 731, a driving motor 733, and a fan blade 735.
  • the fan bush 731 may be provided in a cylindrical shape and may be connected to the inner circumference of the duct 760 of the air outlet 230.
  • a driving motor 733 may be disposed at the central portion of the fan bush 731.
  • the fan blade 735 may be connected to the rotation shaft of the driving motor 733.
  • the operating environment of the fuel cell stack needs to be optimally maintained.
  • the operating environment temperature is an important factor, and the operating environment temperature of the fuel cell stack is affected by the external environment temperature in which the drone is operated.
  • the operating environment temperature of the stack unit 410 disposed inside the case 200 may not be maintained at an appropriate temperature. In this case, it is necessary to increase the internal temperature of the case 200 to an appropriate temperature.
  • the operating environment temperature of the stack unit 410 disposed inside the case 200 may not be maintained at an appropriate temperature. In this case, it is necessary to lower the internal temperature of the case 200 to an appropriate temperature.
  • the recirculation flow path 720 on the sealed housing 710 May be arranged.
  • the air passing through the stack part 410 is air after cooling the stack part 410 which is air-cooled, and maintains a temperature relatively similar to that of the stack part 410, and thus remains on the sealed housing 710.
  • the internal temperature of the case 200 may be similar to the operating environment temperature of the stack 410.
  • the internal temperature may be lowered to an operating environment temperature of the stack unit 410.
  • the internal temperature of the case 200 is adjusted to the operating environment temperature of the stack 410, thereby increasing the operating efficiency of the stack 410.
  • the air circulation control unit 700 may further include a recirculation control mechanism 722.
  • the recirculation control mechanism 722 may be disposed in the recirculation flow path 720 and configured to control the flow rate of the recirculated air.
  • the recirculation control mechanism 722 may be a slide type on / off valve or a butterfly type on / off valve through electronic control, but is not limited thereto.
  • the user may adjust the degree of opening and closing of the recirculation control mechanism 722 by using a controller.
  • the user may close the recirculation control mechanism 722 to close the recirculating housing 710. All of the air remaining inside the) can be discharged to the outside through the air outlet 230.
  • the blind 740 of the present invention is disposed to be inclined or curved in a downward direction, when all the air of the closed housing 710 is discharged to the air outlet 230, the lifting force of the flying object Can contribute to the composition.
  • the internal temperature of the case 200 can be quickly adjusted to the operating environment temperature of the stack 410.
  • the blind 740 may be disposed in the duct 760 of the air outlet 230 and may be provided to guide the flow direction of the outflowing air.
  • the air circulation control structure of the fuel cell power pack integrated drone 100 of the present invention ultimately when the air introduced from the air inlet 220 is discharged to the air outlet 230 after circulating the inside of the case 200. It can be designed to show a flow that can contribute to the lift of the drone.
  • the stack part 410 may be disposed to be inclined downward within a predetermined angle ⁇ 1 on the stack part accommodating part 920 of the module frame 900.
  • the sealed housing 710 may also be connected to be inclined downward in a predetermined angle ⁇ 2 on one surface of the stack 410.
  • the fan member 730 may also be disposed on the air outlet 230 to be inclined downward in a predetermined angle ( ⁇ 3) range.
  • the blind 740 may be disposed to be inclined or curved in a downward direction so that air discharged from the air outlet 230 flows downward.
  • the stack portion receiving portion 920 of the module frame 900 is provided in a form inclined downward in a predetermined angle ( ⁇ 1) range relative to the vertical direction (H1), the stack portion 410 Is inclined to the stack portion receiving portion 20.
  • the inclination angle ⁇ 1 of the stack 410 may be in a range of 5 ° to 15 °, and an inclination angle of about 5 ° may be adopted in the embodiment of the present invention.
  • the opening window 713a of the fixing panel 713 is in close contact with one surface of the stack portion 410 by the sealing unit 714. Since the stack part 410 is disposed to be inclined downward in the stack part accommodating part 920, the fixing panel 713 is also downward in the inclined angle ⁇ 2 corresponding to the stack part 410. It is arranged to be inclined.
  • the sealed housing 710 since the sealed housing 710 is connected along the circumference of the opening window 713a of the fixing panel 713, the sealed housing 710 is basically inclined downward at an angle corresponding to the inclination angle of the stack 410. Can be.
  • the inclination angle ⁇ 2 of the hermetic housing 710 may be in the range of 5 ° to 15 °, in the same manner as the stack 410, and may be about 5 °.
  • the sealed housing 710 may be arranged to be further inclined downward in a predetermined angle range on one surface of the stack 410.
  • the inclination angle ⁇ 2 of the hermetic housing 710 is greater than the inclination angle range of the stack 410.
  • the inclination angle of the sealed housing 710 may be connected to be inclined more in a range of 10 ° to 20 ° than the stack part 410 with respect to one surface of the fixed panel 713.
  • the air outlet 230 may also be arranged to face downward basically. Accordingly, the fan member 730 may also be disposed to face downward in the same manner as the air outlet 230.
  • the fan member 730 since the fan member 730 is connected to the sealed housing 710, in one embodiment, the fan member 730 may be inclined downward at an angle corresponding to the inclination angle ⁇ 2 of the sealed housing 710. In this case, the inclination angle ⁇ 3 of the fan member 730 may be in the range of 5 ° to 15 ° in the same manner as the sealed housing 710, and may be about 5 °.
  • the inclination angle ⁇ 3 of the fan member 730 may be greater than the inclination angle ⁇ 2 of the sealed housing 710.
  • the inclination angle range of the fan member 730 may be in the range of 10 ° to 25 °.
  • the inclination angle ⁇ 3 of the fan member 730 may be greater than the inclination angles ⁇ 1 and ⁇ 2 of the stack part 410 and the sealed housing 710.
  • the inclination angle ⁇ 1 range of the stack portion 410 is 5 ° to 15 °
  • the inclination angle ⁇ 2 range of the sealed housing 710 inclined more than the stack portion 410 is 10 °. If it is ⁇ 20 °, the inclination angle ⁇ 3 of the fan member 730 may be in a range of 15 ° to 30 °.
  • the inclination angles of the stack 410, the sealed housing 710, and the fan member 730 are gradually inclined according to the air flow direction, so that the air flows smoothly downward.
  • the blind 740 is formed to be inclined or curved in the downward direction on the air outlet 230.
  • the propeller 213 may be disposed above the air outlet 230.
  • the air outlet 230 The discharge direction of the air flows downward from the air flowing downward through the propeller 213 of the drone coincides with the flow direction of the outside air, thereby contributing to the lift composition of the drone.
  • the inclination angles ⁇ 11 and ⁇ 12 of the blind 740 are downward based on the horizontal direction H2.
  • the angle of inclination ⁇ 11 may be in the range of 5 ° to 45 °, and the inclination angle ⁇ 12 may be in the range of 30 ° to 80 °.
  • the inclination angle ⁇ 11 may be about 30 °, and the inclination angle ⁇ 12 may be about 60 °.
  • the stack unit 410, the sealed housing 710, and the fan member 730 will be described in connection with the arrangement inclination angles ⁇ 1, ⁇ 2, and ⁇ 3.
  • the inclination angle of the stack 410, the sealed housing 710, and the fan member 730 may be in a range of 5 ° to 15 °, and preferably about 5 °.
  • the inclination angles ⁇ 1, ⁇ 2, ⁇ 3 of the stack 410, the sealed housing 710, and the fan member 730 may gradually increase according to the air flow direction. It may be arranged obliquely.
  • the discharge flow of air may smoothly proceed in a direction in which lift composition contributes.
  • a plurality of blinds 740 may be disposed on the duct 760 of the air outlet 230, and lengths of the plurality of blinds 740 are reduced from the upper side to the lower side of the air outlet 230. Can be formed.
  • the air outlet 230 on the case 200 may be formed to be inclined or curved toward the inside of the case 200 from the upper side to the lower side.
  • the length of the blind 740 is also formed to be reduced toward the lower side from the upper side of the air outlet 230, the air flowing out also flows downward.
  • the length of the blind 740 is reduced at a predetermined ratio, which may correspond to the ratio angle ⁇ 2 of which the air outlet 230 decreases from the upper side to the lower side.
  • the air passing through the blinds 740 arranged in a plurality of rows may exhibit a relatively uniform flow.
  • the length of the lower blind 742 disposed below is shorter than that of the upper blind 741 disposed above, so that it is not disturbed by the downward flow.
  • any one of the lower blinds 742 is longer than the upper blinds 741 disposed thereon.
  • the lower blind 742 disposed below the lower serves as an obstacle, and mixes with the air discharged along the lower blind 742
  • turbulent flow may be generated around the air outlet 230. This makes it difficult to release the air and can rather hinder the maneuvering of the drone.
  • the length reduction of the blind 740 may be maintained at a constant rate for creating a drone's maneuvering environment, such as smooth downward discharge of air and lift lift.
  • the air flowing out by the downward slope angles ⁇ 11 and ⁇ 12 of the blind 740 and the length change according to the predetermined ratio angle ⁇ 2 of the blind 740 may be strongly discharged downward.
  • This overlapping configuration contributes to the drone's maneuvering environment, such as lifting lift.
  • the blind 740 is disposed on the air outlet 230. It may be disposed to be inclined downward.
  • the propeller 213 may be disposed above the air outlet 230, so that the inclined direction of the blind 740 is downward. As set, the flow direction of the air discharged from the air outlet 230 flows downward and the air flow flowing downward through the propeller 213 of the drone coincides with each other, thus contributing to the lift composition of the drone. .
  • the inclination angle ⁇ 3 of the blind 740 is 5 in the downward direction based on the horizontal direction H2. It may be formed between ° ⁇ 80 °, preferably the inclination angle ( ⁇ 3) may be around 60 °.
  • the stack unit 410, the sealed housing 710, and the fan member 730 will be described in connection with the inclination angles ⁇ 1, ⁇ 2, and ⁇ 3.
  • the inclination angle of the stack 410, the sealed housing 710, and the fan member 730 may be in a range of 5 ° to 15 °, and preferably about 5 °.
  • the inclination angles ⁇ 1, ⁇ 2, ⁇ 3 of the stack 410, the sealed housing 710, and the fan member 730 may gradually increase according to the air flow direction. It may be arranged obliquely.
  • the air passing through the stack portion 410 and flowing in the direction of the blind 740 is gradually induced to flow downward, the discharge flow of air smoothly contributes to the lift composition. It can proceed to.
  • FIG 17 shows an air flow according to the air circulation control structure of the fuel cell power pack integrated drone 100 as described above.
  • the internal air of the case 200 is discharged to the air outlet 230 so that the inside of the case 200 is in a negative pressure or low pressure state compared to the outside.
  • the outside air is introduced through the front window 221 and the rear window 222 due to the pressure difference, and some of the introduced air is disposed in the upper part of the front part 201 of the case 200. 830 is naturally cooled, and is circulated and flows into the case 200.
  • the air circulated in the case 200 passes through one surface of the stack 410 as shown in FIG. 17, and generates power by an electrochemical reaction with hydrogen in the stack 410.
  • the stack unit 410 is cooled by air and flows in the sealed housing 710 direction.
  • Air flowing into the sealed housing 710 passes through the fan member 730 and is discharged to the outside through the air outlet 230.
  • a user sets an opening and closing degree of the recirculation control mechanism 722 through a controller to recirculate the case through the recirculation flow path 720.
  • the air flow rate circulated to the inside of the 200 can be adjusted.
  • a part of the air passing through the recirculation passage 720 circulates again inside the case 200 and maintains a temperature relatively similar to the operating environment temperature of the stack 410.
  • FIG. 20 is a plan view showing the gas tank detachable tilting and gas supply structure in a fuel cell power pack integrated drone of the present invention
  • FIG. 21 is an enlarged view of the N portion shown in FIG. 20
  • FIG. 22 is a pressure unit structure of the present invention
  • 23 is a cross-sectional view of a gas supply unit structure of the present invention
  • FIG. 24 is an enlarged view of a portion H shown in FIG. 24,
  • FIG. 25 is a layout view of a flow control valve of the present invention. It is a cross section.
  • the gas tank mounting and detachment tilting and gas supply structure of the present invention fuel cell power pack integrated drone 100 includes a module frame 900, a gas supply unit 430, a pressurizing unit 480, and a tilting structure. It may be configured to include a unit 470.
  • the module frame 900 may be equipped with components constituting the fuel cell, it may be disposed inside the case 200. The detailed structure of the module frame 900 will be described later.
  • the gas supply unit 430 may be inserted into the inclined direction of the case 200 and tilted and connected to the regulator valve 320 of the gas tank 300 mounted on the module frame 900. And it may be disposed on the front portion of the module frame 900 to supply gas to the stack portion 410 mounted to both sides of the module frame 900.
  • the detailed structure of the gas supply unit 430 will be described later.
  • One side of the pressurizing unit 480 is fixed to the front of the module frame 900, the other side is connected to the gas supply unit 430, the gas supply unit 430 to the regulator valve 320 It can be configured to press in the direction.
  • the pressing unit 480 may include a housing block 482, a support plate 485, a pressing beam 483, and a pressing elastic body 481.
  • the housing block 482 is rotatably connected by a hinge part 475 between the first bracket plate 941 and the second bracket plate 942 formed to protrude from the front surface of the module frame 900. Can be.
  • protrusions 482e are formed at both sides of the housing block 482, and the protrusions 482e may be connected to the first and second bracket plates 941 and 942 by hinge pins 475a, respectively.
  • the hinge bush 475b may be disposed at a connection portion of the first and second bracket plates 941 and 942 to smoothly rotate the hinge pin 475a.
  • the housing block 482 may be generally formed in a cylindrical shape, and through holes 482b and 482c may be formed at both ends of the housing block 482 so that the pressing beam 483 may be disposed therethrough.
  • the housing plate 482f having the through hole 482b may be fixed to the housing block 482 by a fastening piece 488a.
  • an opening 482a may be cut in the upper and lower portions of the housing block 482 to reduce weight.
  • the support plate 485 may be disposed at one end of the manifold block 450 constituting the gas supply unit 430.
  • the support plate 485 is provided to prevent one surface of the manifold block 450 from being worn or damaged by the elastic force of the pressure elastic body 481, and may be a rigid metal material.
  • the pressure beam 483 may be disposed to penetrate the inside of the housing block 482 and be connected to the support plate 485.
  • the pressing beam 483 may be disposed through the through holes 482b and 482c formed at both ends of the housing block 482, and one end of the pressing beam 483 may be disposed on one surface of the support plate 485. And a fastening piece 488b.
  • the pressurized beam 483 may be generally provided in the form of a cylindrical beam, and in order to prevent the pressurized beam 483 from being separated from the housing block 482, a disc is provided at the other end of the joining beam 483.
  • the stopper 484 having a shape may be fixed to the fastening piece 488c and disposed.
  • the stopper 484 is formed to have a larger diameter than the through hole 482b of the housing block 482. This prevents the through-hole 482b from passing through the pressurized beam 483 in the direction of the rear surface of the module frame 900, thereby limiting the moving range of the pressurized beam 483.
  • the pressure elastic body 481 may be disposed between the housing block 482 and the support plate 485.
  • the pressure elastic member 481 may be disposed between the inside of the housing block 482 and the support plate 485 to surround the outer circumference of the pressure beam 483.
  • the pressure elastic member 481 may be singular or plural along the radial direction around the outside of the pressure beam 483 between the interior of the housing block 482 and the support plate 485. Can be arranged. Other forms of deployment are also possible.
  • the center of gravity of the pressing beam 483 and the housing block 482 may be disposed on the module frame 900 to be positioned on the center line P of the first direction V1 of the case 200. .
  • the second direction V2 of the case is defined. This is to minimize the effect of the arrangement state of the pressurizing unit 480 on the start of the drone.
  • the pressurization unit 480 of the present invention by the above structure, when the regulator valve 320 of the gas tank 300 is inserted into the gas supply unit 430, the gas supply unit 430 to the regulator valve 320 Pressure in the direction of), the regulator valve 320 and the gas supply unit 430 may be tightly coupled.
  • the tilting unit 470 may be connected between the module frame 900 and the pressing unit 480, and may be provided to be mounted to the module frame 900 by tilting the gas tank 300.
  • the tilting unit 470 may include a base bar 473, a hinge portion 475, and a tilting elastic body 471.
  • the base bar 473 may be provided in a bar shape having a circular cross section, and may be connected to and disposed between the first and second bracket plates 941 and 942 protruding from the front surface of the module frame 900.
  • the tilting elastic body 471 has rings formed at both ends thereof, and a pair of rings may be connected to the center side of the base bar 473 and the center side of the support plate 485, respectively.
  • the tilting elastic member 471 may be positioned on the center line P of the first direction V1 of the case in consideration of the weight balance with respect to the second direction V2.
  • the support plate 485 is connected to the gas supply unit 430, the support plate 485 is pulled toward the base bar 473 by the elastic force of the tilting elastic body 471. do. Accordingly, the gas supply unit 430 connected to the support plate 485 is inclined upward.
  • the hinge part 475 is rotatably connected to the housing block 482 with respect to the module frame 900 by the hinge pin 475a and the hinge bush 475b.
  • the housing block 482, the support plate 485, and the gas supply unit 430 are integrally inclined upward by the elastic force of 471.
  • the gas tank 300 is still before being mounted to the module frame 900.
  • the user inserts the regulator valve 320 of the gas tank 300 in an oblique direction to the manifold block 450 of the gas supply unit 430 and presses the pressurized elastic body 481.
  • the regulator valve 320 of the gas tank 300 and the manifold block 450 of the gas supply unit 430 is in a tightly pressed state.
  • the user presses the tank handle 301 of the gas tank 300 in the downward direction, the position of the gas tank 300 is tilted with the hinge portion 475 as the rotation axis, and the module frame 900 It is to be mounted on the tank receiving portion 910.
  • the tank handle 301 of the gas tank 300 is inserted into the grip part 242 of the tank fixing bar 241.
  • the elastic force of the pressure elastic body 481 acts in the direction of the tank fixing bar 241, and fixes the gas tank 300 by pressing force.
  • the gas supply unit 430 is connected to the regulator valve 320 of the gas tank 300 to accommodate the stack portion accommodating part of the module frame 900. It may be disposed on the front portion 201 of the module frame 900 to supply gas to the stack portion 410 disposed in the 920.
  • the gas supply unit 430 may include a manifold block 450 and a gas supply pipe 440.
  • the manifold block 450 may be a portion connected to the regulator valve 320 of the gas tank 300, and the gas supply pipe 440 is between the manifold block 450 and the stack 410. It may be a portion that is connected to the arrangement.
  • the manifold block 450 may be located on the center line P of the first direction V1 of the case 200 to balance the weight. That is, the manifold block 450 may be formed in a symmetrical shape on both sides of the center line P in the first direction V1.
  • the gas tank 300 inserted into the manifold block 450 is seated in the tank accommodating part 910 of the module frame 900, and the tank accommodating part 910 is disposed on the module frame 900. It may be formed on the center line (P) of the first direction (V1) of the case 200, so that the gas tank 300 also balances the weight in the second direction (V2) of the case 200
  • the center of gravity may be disposed on the center line P of the first direction V1 of the case 200 to minimize the influence on the maneuver of the case 200.
  • the gas tank 300 is disposed such that the center of gravity is positioned on the centerline P of the first direction V1 of the case 200, and the gas tank 300 is disposed on the module frame 900.
  • a plurality of stack receiving portions 920 may be formed at positions symmetrical to both sides of the 300, and the stack 410 may be disposed.
  • the gas supply pipe 440 is branched from the manifold block 450 by the number corresponding to the plurality of stacks 410, the plurality of gas supply pipe 440 is the center line (P1) in the first direction (V1) ) May be arranged in a shape or a position symmetrical to each other on both sides of the module frame (900).
  • the gas supply pipe 440 may be connected to the upper side of the stack 410. This is to allow gas to be supplied from the upper side to the lower side of the stack 410 to be diffused downward and to cause an electrochemical reaction.
  • Condensate is generated as a by-product during the electrochemical reaction of oxygen and hydrogen, and the condensate drops downward due to gravity.
  • the gas supply pipe 440 is connected to the middle side or the bottom side of the stack 410, the fall of the condensed water may interfere with the diffusion of the gas, to prevent this.
  • the regulator valve 320 is connected to the outlet of the gas tank 300, and provides a gas to be supplied to the manifold flow path 456 of the manifold block 450 of the gas flowing out from the gas tank 300 Can be. Hydrogen gas may be discharged from the gas tank 300.
  • the regulator valve 320 may include a connector 325 and the opening and closing portion 330.
  • the connector 325 may be connected to the outlet of the gas tank 300.
  • the outlet of the gas tank 300 may be connected to the bolt / screw fastening structure, but is not necessarily limited thereto.
  • the connector 325 may be provided with a decompression unit 323, a gas filling unit 321, a pressure sensor 322 and the temperature response pressure discharge unit 324.
  • the decompression unit 323 may be provided to adjust the degree of decompression of the gas flowing out of the outlet of the gas tank 300.
  • the gas filling unit 321 may be provided in the form of a valve to fill the gas in the gas tank 300.
  • the user can simply charge the gas by opening the lid 204 of the case 200 without disconnecting the gas tank 300, by connecting an external gas supply device and the gas filling unit 321 with a hose. have.
  • the pressure sensor 322 may be provided to measure the internal gas pressure of the gas tank 300.
  • the internal gas pressure of the gas tank 300 may vary according to an operating environment, and in some cases, the internal gas pressure of the gas tank 300 may reach a limit and may explode.
  • a drone operating in a hot area may be started when exposed to high temperature, in which case the internal gas pressure of the gas tank 300 may increase due to the high temperature.
  • the pressure sensor 322 measures the internal gas pressure of the gas tank 300 and transmits the information to the user.
  • the temperature reactive pressure discharge part 324 may be provided to automatically discharge the internal gas pressure of the gas tank 300 in response to the internal gas temperature of the gas tank 300.
  • the gas tank 300 is exposed to a high temperature environment and the internal gas pressure of the gas tank 300 rises as the internal gas temperature of the gas tank 300 rises, the gas is automatically discharged. It is possible to prevent the explosion of the gas tank 300 in advance.
  • the opening and closing portion 330 is connected to one end of the connector portion 325, and the other end is inserted into the insertion space 452 of the manifold block 450 and the flow of gas. It may be provided to open and close.
  • the opening and closing portion 330 may include a valve body 334, the valve elastic body 337 and the opening and closing bar 336, the inner flow passage 332 and the dispersion flow passage 333 is formed.
  • the valve body 334 may be substantially cylindrical in shape, and may be inserted into an insertion space 452 formed in the manifold block 450.
  • One side of the valve body 334 may be connected to the connector portion 325, the other side may be formed with a valve protrusion 335 protruding toward the manifold block 450 in the center portion.
  • the valve protrusion 335 may have a cylindrical shape.
  • the diameter of the valve protrusion 335 may be smaller than the diameter of the valve body 334 connected to the connector 325.
  • the internal passage 332 is connected to the connector portion 325 and may be disposed in the valve body 334.
  • the internal flow path 332 may be a flow path through which hydrogen gas reduced in pressure by the set pressure of the decompression unit 323 in the connector unit 325 flows.
  • the inner passage 332 includes an opening and closing space 331 extending radially from the other side of the valve body 334.
  • the dispersion passage 333 may be formed in communication with the internal passage 332 in the valve protrusion 335 of the valve body 334.
  • the dispersion flow path 333 may be formed in the radial direction inside the valve protrusion 335 so that the gas may be dispersed in the radial direction.
  • a plurality of dispersion passages 333 may be formed along the circumferential direction of the valve protrusion 335.
  • Hydrogen gas flowing out of the dispersion passage 333 is introduced into the manifold passage 456 of the manifold block 450, which will be described later, and is supplied to each stack unit 410 through the gas supply pipe 440. .
  • the valve elastic body 337 may be disposed in the open / close space 331.
  • the valve elastic body 337 applied to the present invention may be a coil spring or a leaf spring.
  • the valve elastic body 337 provides an elastic force to the opening / closing bar 336 so that the opening / closing bar 336 is pressed toward the pressing part 460 of the manifold block 450.
  • One end 336a of the opening / closing bar 336 is supported by the valve elastic body 337 and may be disposed in the opening / closing space 331 of the inner passage 332.
  • the other end 336b of the opening / closing bar 336 is disposed in the through hole 335a formed in the valve protrusion 335, and is disposed in the form of protruding toward the pressing part 460 of the manifold block 450. Can be.
  • the manifold block 450 may be connected between the regulator valve 320 and the stack unit 410, and may be provided to flow gas discharged through the regulator valve 320 into the stack unit 410.
  • the manifold block 450 may include a body part 451, a link part 455, and a pressing part 460.
  • the body 451 may have a generally cylindrical shape, and an insertion space 452 may be formed at one side thereof in a shape corresponding to the regulator valve 320.
  • the insertion space 452 may include a valve protrusion accommodating hole 453 in which the valve protrusion 335 of the valve body 334 is accommodated in the direction of the center line of the insertion space 452.
  • the valve body 334 and the valve protrusion 335 may be inserted into the insertion space 452 and the valve protrusion receiving hole 453.
  • the insertion space 452 and the valve protrusion receiving hole 453 may be formed in a shape corresponding thereto to accommodate the valve body 334 and the valve protrusion 335, respectively.
  • the link part 455 is disposed at the other side of the body part 451.
  • the link part 455 may be provided with a manifold flow path 456 formed so that the gas discharged from the regulator valve 320 inserted into the insertion space 452 flows into the stack part 410.
  • a plurality of manifold flow passages 456 may be formed on the link portion 455 corresponding to the number of stack portions 410 to supply hydrogen gas.
  • the pressing part 460 may be disposed in contact with the other end 336b of the opening / closing bar 336 in the body 451 so that the opening / closing bar 336 may be pressed.
  • the pressing part 460 may be implemented in a groove shape in which a part of the other end 336b of the opening and closing bar 336 is accommodated.
  • the pressing portion 460 may have a protrusion shape.
  • the other end portion 336b of the opening and closing bar 336 is positioned inside the through hole 335a, and the valve protrusion 335 is completely inserted into the insertion space 452 of the body portion 451.
  • the protrusion shape of the pressing portion 460 is inserted into the through hole 335a and pushes the other end portion 336b of the opening / closing bar 336.
  • one end 336a of the opening / closing bar 336 is separated from the contact surface of the opening / closing space 331 to open the inner passage 332 and the dispersion passage 333.
  • the opening and closing portion 330 which is a part of the regulator valve 320 is described and illustrated as being inserted into the manifold block 450 (exactly, the insertion space 452), but in another embodiment of the present invention, Accordingly, the manifold block 450 may be changed to be inserted into the regulator valve 320.
  • the first seal 471 disposed on the outer surface of the valve body 334 to prevent leakage of gas between the inner surface of the insertion space 452 and the outer surface of the valve body 334. ) May be included.
  • a second sealing disposed on an outer surface of the valve protrusion 335 so that gas leakage between the valve engagement portion 335 and the insertion engagement surface between the valve protrusion receiving hole 453 of the manifold block 450 is blocked. 473 may be further included.
  • the first and second seals 471 and 473 may be O-rings, but are not necessarily limited thereto.
  • At least one of the first and second seals 471 and 473 may be formed of a material having an elastic force.
  • the first and second seals may be made of a material such as rubber or soft plastic.
  • first sealing 471 is compressed between the outer circumferential surface of the valve body 334 and the inner circumferential surface of the insertion space 452 of the manifold block 450 to the valve body 334 and the manifold block ( 450) is press-bonded.
  • the second sealing 473 is compressed between the outer peripheral surface of the valve protrusion 335 of the valve body 334 and the inner peripheral surface of the valve protrusion receiving hole 453 of the manifold block 450 to seal the valve body 334.
  • the valve projection 335 and the manifold block 450 of the compression bonding are compressed between the outer peripheral surface of the valve protrusion 335 of the valve body 334 and the inner peripheral surface of the valve protrusion receiving hole 453 of the manifold block 450 to seal the valve body 334.
  • valve body 334 and the manifold block 450 may contribute to maintaining the coupling by applying a pressing force along with an improvement in sealing force to prevent gas leakage by the first and second seals 471 and 473. .
  • a flow control valve 490 disposed in the manifold passage 456 to control the flow rate of the gas discharged from the regulator valve 320 to the manifold passage 456. ) May be included.
  • the flow control valve 490 may be an electronic control valve such as a solenoid valve, and the user may control the flow rate of the gas supplied to the stack 410 through power control on the manifold flow passage 456. 490 can be adjusted.
  • a central hole 457 into which the valve protrusion 335 is inserted may be formed at the central portion of the manifold block 450.
  • the gas ejected from the through hole 335a of the valve protrusion 335 passes through the plurality of distribution passages 333 disposed along the circumference of the valve protrusion 335, and is ejected to the central hole 457.
  • Gas introduced into the central hole 457 is dispersed through the branch hole 458 to the manifold flow path 456, respectively.
  • the flow control valve 490 may include a valve housing 491, a stator 492, a rotor 493, and an opening / closing piece 494.
  • the valve housing 491 may be connected to the lower side of the manifold block 450.
  • a stator 492 may be disposed inside the valve housing 491, and a rotor may be disposed at the center of the stator 492.
  • 493 may be disposed.
  • An opening and closing piece 494 may be mounted at an end of the rotor 493.
  • the flow control valve 490 may be a valve of a normal close type which is normally closed at all times. In this case, the valve is opened when the user applies power.
  • the opening and closing piece 494 is basically inserted into the branch hole 458.
  • the rotor 493 moves in the opposite direction to the branch hole 458 by an electromagnetic reaction. Accordingly, the opening and closing piece 494 mounted at the end of the rotor 493 is discharged from the branch hole 458 to control the opening and closing of the branch hole 458.
  • the rotor 493 moves in the direction of the branch hole 458 again, the opening and closing piece 494 is inserted into the branch hole to block the flow of hydrogen gas. do.
  • the flow control valve 490 may be configured to automatically close when a failure or a dangerous situation of the fuel cell power pack occurs.
  • the flow control valve 490 is described as being limited to the electronic control valve, but is not necessarily limited thereto.
  • the flow control valve 490 together with the opening and closing bar 336, has a meaning as an auxiliary means for controlling the flow of hydrogen gas.
  • the flow control valve 490 opens and closes the branch hole 458.
  • the opening and closing of the gas can be controlled auxiliaryly.
  • the primary opening / closing structure by the opening / closing bar 336 and the pressing part 460 and the two openings by the flow control valve 490 and the branch hole 458 are as described above.
  • the differential opening and closing structure enables more stable control of the gas supply.
  • the user opens the lid 204 of the case 200 and inserts the gas tank 300 in the inclined direction.
  • the manifold block 450 of the gas supply unit 430 is inclined upward by the elastic force of the tilting elastic body 471, so that the regulator valve 320 of the gas tank 300 is manifolded.
  • the insertion space 452 of the fold block 450 is fitted.
  • the gas tank 300 is tilted using the hinge portion 475 as the rotation axis. It is to be seated in the tank receiving portion (910).
  • the tank handle 301 is inserted into the grip portion 242 of the tank fixing bar 241, acts on the elastic force of the pressure elastic body 481, and the gas tank 300 is fixed by the tank fixing bar 241.
  • the opening and closing bar 336 is inserted into the pressing portion 460 Since it is pressed, the fuel tank may be supplied to the stack unit 410 before the gas tank 300 is seated on the tank accommodating part 910 of the module frame 900.
  • the flow control valve 490 is normally closed at all times in order to prevent the fuel gas from being supplied to the stack unit 410 at a point where the user does not want to open the flow path through which the fuel gas is supplied. It has been described above that the valve is of a normal close type.
  • the flow control valve 490 is opened when the user applies power, and when the user turns off the power to stop using the fuel cell power pack, the flow control valve 490 returns to the basic sealed state again. That is, it is opened and closed by the user's power operation.
  • the flow control valve 490 may be configured to automatically close when a failure or a dangerous situation of the fuel cell power pack occurs.
  • the flow control valve 490 is always in a closed state at all times, and controls opening and closing of the gas to the stack part 410 by operating the power supply.
  • the other end 336b of the opening and closing bar 336 is the pressing part 460. Pressed by the inner end of the, one end 336a of the opening and closing bar 336 is separated from the contact surface 331a of the opening and closing space 331, the gas flow path is opened.
  • the flow control valve 490 may be positioned in an open state so that all the flow paths through which the fuel gas flows are connected. This operation can be done later.
  • the gas discharged from the gas tank 300 is first decompressed by a predetermined pressure by the decompression unit 323 of the regulator valve 320 and then the internal flow path ( 332).
  • the gas Since the inner passage 332 and the dispersion passage 333 communicate with each other by the movement of the opening and closing bar 336, as shown in the enlarged view of FIG. 24, the gas is opened and closed in the inner passage 332. It is discharged through the distribution passage 333 via 331, and flows to the manifold passage (456).
  • the gas is supplied to each stack unit 410 by the gas supply pipe 440 connected to the manifold passage 456.
  • first and second seals 471 and 473 are disposed between an outer surface of the valve body 334, an outer surface of the valve protrusion 335, and an inner surface of the insertion space 452, thereby preventing external leakage of hydrogen gas. can do.
  • the operator may remove the valve body 334 of the regulator valve from the insertion space 452 of the manifold block 450.
  • the one end 336a of the opening / closing bar 336 is opened or closed. Is in close contact with the contact surface 331a.
  • the user can shut off the gas supply by closing the branch hole 458 by the flow control valve 490 by operating the controller. In this case, the user does not need to remove the gas tank 300 from the case 200.
  • the gas when the regulator valve 320 of the gas tank 300 is inserted into the manifold block 450, the opening and closing bar 336 is inserted and pressed into the pressing portion 460, the gas is still
  • the fuel gas may be supplied to the stack 410 before the tank 300 is seated on the tank accommodating part 910 of the module frame 900.
  • the flow control valve 490 may be provided to block supply of gas to the stack unit 410 at a time when the user does not want to.
  • FIG. 8 is a plan view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 9 is a side view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • Figure 10 is an internal structure of the fuel cell power pack integrated drone of the present invention.
  • 11 is a rear view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • FIG. 12 is a bottom view showing the internal structure of the fuel cell power pack integrated drone of the present invention
  • FIG. 13 is a fuel cell of the present invention.
  • FIG. 14 is a rear perspective view showing the internal structure of the power pack integrated drone
  • FIG. 14 is a front perspective view showing the interior of the fuel cell power pack integrated drone according to the present invention.
  • the module mounting structure of the fuel cell power pack integrated drone of the present invention is the module frame 900, tank receiving portion 910, stack receiving portion 920, manifold receiving portion 940 and It may be configured to include a control panel receiver 930.
  • the module frame 900 may be a frame of a relatively rigid material disposed inside the case 200 and on which components constituting the fuel cell are mounted.
  • the tank accommodating part 910 may be formed at a central portion of the module frame 900 and mounted to the gas tank 300.
  • the tank accommodating part 910 may be processed according to the outer shape of the gas tank 300, and in the present invention, the tank accommodating part 910 may have a groove shape rounded to a semicircular shape.
  • Elastic pads 911 may be disposed at both inner circumferences of the tank accommodation portion 910, and the accommodation pad 911 may be in close contact with the tank accommodation portion 910. And may be provided to absorb a shock that may be applied to the gas tank 300.
  • a tank handle 301 is disposed at a lower end of the gas tank 300, and a grip 242 having a tong shape into which the tank handle 301 of the gas tank 300 is inserted inside the rear part of the case 200. Is formed tank fixing bar 241 may be disposed.
  • the stack part accommodating part 920 may be formed at both sides of the module frame 900 and may be a part in which the stack part 410 is mounted.
  • the stack portion receiving portion 920 may be disposed at positions symmetrical with respect to both sides with respect to the tank receiving portion 910 so as to achieve a weight balance on the module frame 900.
  • the stack portion receiving portion 920 may include a first receiving surface 921 and a second receiving surface 923.
  • the first receiving surface 921 may be provided in a quadrangular shape, and a first fastening unit 922 may be disposed to fix one side of the stack 410.
  • the second receiving surface 923 is provided in a quadrangular shape, and is formed at a right angle with respect to the first receiving surface 921, and a second fastening unit 924 fixing the lower surface of the stack part 410 is provided. Can be arranged.
  • the stack 410 is fixed to the first and second fastening units 922 and 924 on the first and second receiving surfaces 921 and 923, respectively.
  • the first and second fastening units 922 and 924 may be fastening bolts / nuts.
  • the stack part accommodating part 920 may be disposed to be inclined at a predetermined angle ⁇ 1 on both sides of the module frame 900 based on the vertical line H1 of the case 200.
  • the first receiving surface 921 may be disposed to be inclined while looking outwardly downward of the module frame 900 based on the vertical line H1 of the case 200.
  • the second receiving surface 923 is connected to the first receiving surface 921 at a right angle, the second receiving surface 923 is based on the horizontal line H2 of the case 200. It may be disposed to be inclined while looking at the outer downward direction of the 900.
  • the inclination angle ⁇ 1 range of the stack receiving portion 920 may be about 5 ° ⁇ 15 °, preferably an inclination angle of about 5 ° may be adopted. have.
  • the fixing panel 713 of the present invention may be disposed on both sides of the case 200, the opening window 713a connected to one surface of the stack portion 410 may be formed.
  • the fixing panel 713 may be disposed at an inclination angle ⁇ 2 opposite to the stack 410 disposed on the first and second receiving surfaces 921 and 923.
  • the inclination angle of 5 ° to 15 ° may be formed in an upward direction based on the vertical direction H1 of the case 200. That is, in the embodiment of the present invention, the inclination angles ⁇ 1 and ⁇ 2 may be the same.
  • the sealing unit 714 is disposed along the circumference of the opening window 713a of the fixing panel 713, and is closely adhered along the circumference of the first receiving surface 921 of the stack 410.
  • the air passing through the 410 may be provided to flow into the sealed housing 720 without leakage.
  • the stack unit accommodating part 920 is disposed to be inclined at a predetermined angle ⁇ 1 as follows.
  • the fixing panel is disposed inside the case 200, and an elastic sealing unit 714 is surrounded by an opening 713a of the fixing panel 713 to prevent air leakage.
  • the stack portion receiving portion 920 is also formed vertically on the module frame 900 If the stack part 410 is mounted perpendicular to the stack part receiving part 920, when the module frame 900 is inserted into the case 200, the stack part 410 is inserted in the insertion process. If interference occurs between one surface of the sealing unit and the sealing unit 714, and is forcibly inserted to overcome such interference, friction between the one surface of the stack portion 410 made of metal and the surface of the sealing unit 714 made of elastic material. Damage may occur.
  • the stack part 410 is disposed at an inclination at a predetermined angle ⁇ 1 in the downward direction, and the fixing panel 713 and the sealing unit 714 are disposed at an inclination at an angle opposite to the upward direction.
  • one surface of the stack part 410 is smoothly seated on the surface of the sealing unit 714 and adheres to the sealing unit 714. ) To prevent surface damage.
  • arranging one surface of the stack 410 inclined downwards generally guides the flow of air downwards and finally contributes to the lift composition of the drone when discharged from the air outlet 230. There is also a purpose to do so.
  • the airtight housing 710 in which the recirculation flow path 720 and the recirculation control mechanism 722 are disposed is connected to the opening window 713a of the fixed panel 713, and the airtight housing 710 A duct 760 having a plurality of blinds 740 may be disposed between the air outlets 230. Since it is disposed to look downward generally, the air flowing in the stack portion 410 toward the air outlet 230 is naturally guided downward.
  • the manifold receiving portion 940 is formed on the front surface of the module frame 900, the manifold portion for connecting the regulator valve 320 and the stack portion 410 mounted on the gas tank 300 It may be a portion in which 420 is disposed.
  • the manifold receiving portion 940 may be configured to include a first bracket plate 941 and the second bracket plate 942.
  • the first bracket plate 941 may be disposed to protrude toward the front portion of the module frame 900, and the second bracket may be spaced apart from the first bracket plate 941 at a predetermined interval. It may be disposed to protrude in the front direction of the 900.
  • the tilting unit 470 and the pressing unit 480 may be connected and disposed between the first and second bracket plates 941 and 942.
  • the base bar 473 of the tilting unit 470 is connected to and disposed between the first and second bracket plates 941 and 942.
  • the tilting elastic body 471 has rings formed at both ends thereof, and a pair of rings are respectively formed. It is connected to the center side of the base bar 473 and the center side of the support plate 485.
  • the support plate 485 is connected to the gas supply unit 430 so that the support plate 485 is pulled toward the base bar 473 by the elastic force of the tilting elastic body 471. Accordingly, the gas supply unit 430 connected to the support plate 485 is inclined upwardly before mounting the regulator valve 320 of the gas tank 300.
  • the hinge part 475 is rotatably connected to the housing block 482 with respect to the module frame 900 by the hinge pin 475a and the hinge bush 475b.
  • the housing block 482, the support plate 485, and the gas supply unit 430 are inclined upwardly integrally on the module frame 900 by the elastic force of 471.
  • the housing block 482 of the pressing unit 480 is hinged between the first bracket plate 941 and the second bracket plate 942 formed to protrude from the front surface of the module frame 900. It is connected to the branch 475 and is rotatably arranged.
  • protrusions 482e are formed at both sides of the housing block 482, and the protrusions 482e are connected to the first and second bracket plates 941 and 942 by hinge pins 475a, respectively.
  • the hinge bush 475b may be disposed at a connection portion of the first and second bracket plates 941 and 942 to smoothly rotate the hinge pin 475a.
  • the tilting unit 470 and the pressurizing unit 480 are disposed between the first and second bracket plates 941 and 942 so that the regulator valve 320 of the gas tank 300 is inserted into and connected to the manifold block 450.
  • the gas tank 300 is applied to the module by applying a pressing force. It is to be firmly fixed on the tank receiving portion 910 of the frame 900.
  • the control panel accommodating part 930 is formed at a lower side of the manifold accommodating part 940 at the front part of the module frame 900, and controls the regulator valve and the stack part 410 of the gas tank 300.
  • the control panel can be arranged.
  • control panel accommodating part 930 may be inclined to correspond to the inclined arrangement of the front window 221.
  • control panel 830 mounted to the control panel accommodating part 930 is naturally cooled by the air introduced from the front window 221.
  • the auxiliary power brackets 510 may be disposed at both sides of the front part of the case 200 in symmetrical positions. As described above, the auxiliary power bracket 510 may be disposed at the center line P of the first direction V1 of the case 200. It is disposed in consideration of maintaining the weight balance of the auxiliary power source 500 on the basis of.
  • the present invention relates to a module mounting structure of a fuel cell power pack integrated drone, and has industrial applicability.

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Abstract

La présente invention concerne une structure de montage de module d'un drone à bloc d'alimentation de pile à combustible intégré. Selon la présente invention: de l'énergie est fournie à partir d'une pile à combustible, de façon à réduire le poids d'un drone et permettre un fonctionnement de longue durée du drone; le drone comporte une structure de circulation d'air améliorée, de façon à maintenir une température d'environnement de fonctionnement stable d'un empilement et contribuer à la génération de la portance du drone; et un réservoir de gaz peut être facilement monté sur le drone ou démonté de celui-ci par l'intermédiaire d'une structure de montage/démontage basculante, de façon à améliorer la praticité pour l'utilisateur. En particulier, la présente invention met en oeuvre une structure de montage équilibrée d'un module de pile à combustible, de façon à obtenir l'équilibre du poids général du drone, et permet un fonctionnement stable du drone.
PCT/KR2019/011077 2018-08-31 2019-08-29 Structure de montage de module pour un drone à bloc d'alimentation de pile à combustible intégré WO2020046011A1 (fr)

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KR1020180103818A KR102224303B1 (ko) 2018-08-31 2018-08-31 연료전지 파워팩 일체형 드론의 모듈 탑재 구조
KR10-2018-0103818 2018-08-31

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