Modular fuel cell unmanned aerial vehicle and fuel cell working method thereof

Abstract

The invention relates to a modular fuel cell unmanned aerial vehicle and a fuel cell working method thereof, the unmanned aerial vehicle comprises a fuselage, a plurality of power modules and a plurality of connecting shafts, and each power module is detachably connected with the fuselage through one connecting shaft; the loading area is used for placing goods needing to be transported; the power module comprises a fan and a small-sized air-cooled hydrogen fuel cell, and the fan is used for providing cathode gas for the small-sized air-cooled hydrogen fuel cell and is also used for cooling and heat dissipation of the small-sized air-cooled hydrogen fuel cell; the connecting shaft comprises an information transmission line, a circuit and a hydrogen supply pipeline; the power of the power module is selected according to the weight of goods needing to be transported. The multiple power modules are arranged to replace a traditional single power source, the detachable power modules are adopted, the proper power module is selected according to the weight of the unmanned aerial vehicle body, the working efficiency of the unmanned aerial vehicle is improved, the endurance time of the unmanned aerial vehicle is prolonged, and the application scenarios of the unmanned aerial vehicle are increased.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a modular fuel cell unmanned aerial vehicle and a fuel cell operating method thereof. Background Art

[0002] The emergence of drones has brought many conveniences to people's lives and has been widely used in all walks of life. At present, drones mainly rely on six types of power to complete complex tasks, including: lithium batteries, hydrogen fuel cells, laser transmitters, solar power generation, internal combustion engine power generation and wired cable power supply. Among them, hydrogen fuel cells are more popular due to their significant effects and high safety factor, and can also provide inspiration for the exploration of power sources for other aircraft in the future.

[0003] In the existing drone technology that uses hydrogen fuel cells as a power source, the fuselage usually carries an air-cooled hydrogen fuel cell, which requires an additional high-speed fan for cooling and gas supply. The use of a high-speed fan alone to supply cathode reaction gas not only reduces the system integration but also increases the cost of use. In addition, drones usually use a single power source. When the membrane electrode in the battery is damaged, the maintenance and repair costs are high. When a failure occurs during flight, it will directly cause serious consequences such as a crash. In addition, too many single cells in a single power source can easily cause uneven internal water vapor distribution, resulting in a decrease in the durability of the battery stack. In addition, a single power source cannot be adjusted according to the load-bearing capacity of the drone, and the energy utilization rate is low.

[0004] In existing drone technology that uses air-cooled hydrogen fuel cells as a power source, it is difficult to achieve cathode humidification, resulting in low overall performance of the fuel cell and only being able to operate in a low current density range; and air-cooled hydrogen fuel cells usually require an additional heat source when cold-starting, which increases system complexity and cost.

[0005] Therefore, it is urgent to design a modular fuel cell drone and a fuel cell working method thereof to solve the problems existing in the above-mentioned existing technologies. Summary of the invention

[0006] In view of this, the present invention provides a modular fuel cell UAV and a fuel cell working method thereof, the purpose of which is to replace the traditional single power source by setting multiple power modules, and adopting detachable power modules, selecting appropriate power modules according to the fuselage load, thereby improving the working efficiency and endurance time of the UAV and increasing the application scenarios of the UAV.

[0007] To achieve the above object, the present invention adopts the following technical solutions:

[0008] A modular fuel cell drone, comprising a fuselage, a plurality of power modules and a plurality of connecting shafts, wherein each power module is detachably connected to the fuselage via a connecting shaft;

[0009] The fuselage is provided with electrical equipment, a hydrogen source storage area and a cargo area. The hydrogen source storage area is used to store hydrogen bottle assemblies; the cargo area is used to place the cargo to be transported;

[0010] The power module includes a fan and a small air-cooled hydrogen fuel cell, wherein the fan is used to provide cathode gas for the small air-cooled hydrogen fuel cell and is also used for cooling and dissipating the heat of the small air-cooled hydrogen fuel cell;

[0011] The connecting shaft includes an information transmission line, an electric circuit and a hydrogen supply pipeline;

[0012] The power of the power module is selected according to the weight of the cargo that the drone needs to transport.

[0013] Furthermore, the fan includes a motor, blades, an upper shell and a lower shell, the upper shell and the lower shell are both hollow structures, the upper shell and the lower shell are buckled together, the motor and the blades are both located in the upper shell and the lower shell, the motor is fixed on the inner side of the lower shell, the output end of the motor is connected to the rotating shaft of the blades, and the small air-cooled hydrogen fuel cell is fixed on the outer side of the upper shell.

[0014] Furthermore, the shape of the hollow structure on the lower shell matches the shape of the small air-cooled hydrogen fuel cell, the small air-cooled hydrogen fuel cell is fixedly mounted on the hollow structure of the lower shell, and the hollow structure of the outer lower shell of the small air-cooled hydrogen fuel cell fits tightly.

[0015] Furthermore, the direction of the cathode flow channel of the small air-cooled hydrogen fuel cell is parallel to the direction of the rotation axis of the fan blade.

[0016] Furthermore, the hydrogen supply subsystem of the small air-cooled hydrogen fuel cell includes a hydrogen bottle assembly, a vortex tube, a condenser, a first solenoid valve, a second solenoid valve, and a third solenoid valve. The hydrogen bottle assembly is connected to the inlet of the vortex tube, and the hot flow outlet of the vortex tube is connected to the anode inlet of the small air-cooled hydrogen fuel cell through a pipeline; the cold flow outlet of the vortex tube is connected to the inlet of the condenser, and the outlet of the condenser is connected to a T-shaped pipe, one branch of the T-shaped pipe is connected to the first solenoid valve and the anode inlet of the small air-cooled hydrogen fuel cell in sequence, and the other branch of the T-shaped pipe is provided with a second solenoid valve for controlling whether the gas at the cold flow outlet of the vortex tube is discharged outside the gas supply subsystem; a water collector is provided below the condenser; the anode outlet of the small air-cooled hydrogen fuel cell is connected to a pipeline, and the pipeline is provided with a third solenoid valve for controlling whether the exhaust gas and water generated by the anode of the small air-cooled hydrogen fuel cell are discharged outside the hydrogen supply subsystem.

[0017] Furthermore, the hydrogen supply subsystem of the small air-cooled hydrogen fuel cell also includes a water collector, an ultrasonic atomizer and a water pump. The water collector is arranged directly below the condenser and is used to collect liquid water condensed in the condenser. A liquid water outlet is arranged at the bottom of the water collector, and the liquid water outlet is connected to the ultrasonic atomizer through a pipe. A water pump is arranged on the connecting pipe between the liquid water outlet of the water collector and the ultrasonic atomizer. The water pump is used to pump out the liquid water collected by the water collector to provide a water source for the ultrasonic atomizer. The ultrasonic atomizer is arranged at the upper end of the power module and is used to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell.

[0018] Furthermore, the hydrogen supply subsystem of the small air-cooled hydrogen fuel cell also includes a first temperature sensor and a second temperature sensor. The first temperature sensor is arranged at the heat flow outlet of the vortex tube to measure the gas temperature at the heat flow outlet of the vortex tube; the second temperature sensor is arranged at the anode outlet of the small air-cooled hydrogen fuel cell to measure the gas temperature at the anode outlet of the small air-cooled hydrogen fuel cell.

[0019] The present invention also provides a working method of a small-scale air-cooled hydrogen fuel cell based on the modular fuel cell UAV, and the working method is specifically as follows:

[0020] The hydrogen in the hydrogen bottle assembly is separated into high-temperature low-pressure hydrogen and low-temperature low-pressure hydrogen under the action of the vortex tube. The high-temperature low-pressure hydrogen flows out from the hot flow outlet of the vortex tube; the low-temperature low-pressure hydrogen flows out from the cold flow part of the vortex tube and enters the condenser as a cold source, so that the water vapor in the air condenses in the condenser to form liquid water. The liquid water enters the water collector under the action of gravity. At the same time, the low-temperature low-pressure hydrogen absorbs heat and heats up. After merging with the high-temperature low-pressure hydrogen flowing out from the hot flow outlet, it enters the fuel cell stack through the anode inlet of the small air-cooled hydrogen fuel cell to participate in the reaction;

[0021] Under the action of the water pump, the water in the water collector is pumped out and enters the ultrasonic atomizer, where it is atomized and sprayed out through the nozzle of the ultrasonic atomizer to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell.

[0022] Furthermore, the working method also includes:

[0023] The anode of the small air-cooled hydrogen fuel cell adopts a dead-end mode, and the anode outlet is opened and closed by a third solenoid valve. Normally, the third solenoid valve is in a closed state. When water and exhaust gas in the stack accumulate to a certain level, the third solenoid valve is opened to purge the stack anode and discharge the water and exhaust gas through the pressure difference.

[0024] Furthermore, the working method also includes:

[0025] When the ambient temperature is lower than 0℃, a cold start needs to be performed when the small air-cooled hydrogen fuel cell is started. The heat flow temperature is increased by changing the opening of the hot flow outlet of the vortex tube. When the first temperature sensor arranged at the hot flow outlet of the vortex tube measures that the gas temperature at the hot flow outlet reaches the maximum hot pressure temperature of the membrane electrode, the gas flowing out of the hot flow outlet of the vortex tube is used to purge the small air-cooled hydrogen fuel cell. At this time, the second battery valve is opened and the first solenoid valve is closed, and the low-temperature hydrogen flowing out of the cold flow outlet of the vortex tube is directly discharged to the hydrogen supply subsystem; when the second temperature sensor arranged at the anode outlet of the small air-cooled hydrogen fuel cell measures that the temperature of the anode outlet reaches above 0℃, the cold start is completed; then the second solenoid valve is closed, the first solenoid valve is opened, the hot flow outlet of the vortex tube is adjusted to a normal opening, and normal operation begins.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] (1) By splitting a single power source into multiple power modules, the UAV can be prevented from crashing due to a single power source failure during flight. At the same time, after being split into multiple power modules, when a power module fails, it is also easy to repair and replace, effectively reducing maintenance costs. By separating the fuselage from the power source and selecting a power module with appropriate power according to the weight of the cargo that the fuselage needs to transport, simply replacing the power module can meet different load requirements. When the load is low, a power module with low power can be selected to reduce the energy waste caused by the weight of the battery stack itself. When the load is high, a power module with high power can be selected to prevent the problem of insufficient power of the battery stack and the fan when the load is high; at the same time, it can also avoid the low efficiency of the system caused by the weight of a single high-power air-cooled fuel cell, making the UAV's capacity utilization efficiency high and the application scenario more flexible. In addition, using multiple power modules as the power source of the UAV effectively reduces the number of single cells in each battery, makes the water vapor distribution inside the battery stack more uniform, increases the service life of the battery stack, and reduces the replacement cost when it is damaged.

[0028] (2) By using a fan to provide cathode gas for the small air-cooled hydrogen fuel cell and cool the small air-cooled hydrogen fuel cell, the endurance of the UAV is greatly improved, the overall complexity and weight of the UAV is reduced, and the cost of use is reduced.

[0029] (3) By using the low-temperature hydrogen separated by the vortex tube as the cold source of the condenser, the water vapor in the air is condensed in the condenser to form liquid water, and the liquid water is collected by the collector, thereby achieving humidification of the cathode gas entering the small air-cooled hydrogen fuel cell, increasing the performance and working efficiency of the fuel cell stack. By setting a small air-cooled hydrogen fuel cell cold start, the high-temperature hydrogen separated by the vortex tube is used to purge the small air-cooled hydrogen fuel cell, without the need for an additional heat source, so that the small air-cooled hydrogen fuel cell can be quickly cold-started, increasing the applicability of the drone in cold areas.

[0030] Other features and advantages of the present invention will be described in the following description, and partly become obvious from the description, or be understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 A schematic diagram of the structure of a modular fuel cell drone according to an embodiment of the present invention is shown;

[0033] Figure 2 A three-dimensional exploded view of a power module of a modular fuel cell drone according to an embodiment of the present invention is shown;

[0034] Figure 3 A schematic diagram of the structure of a hydrogen supply subsystem of an air-cooled hydrogen fuel cell according to an embodiment of the present invention is shown.

[0035] In the figure: 1. fuselage; 2. power module; 3. connecting shaft; 4. lower shell; 5. motor; 6. blades; 7. upper shell; 8. small air-cooled hydrogen fuel cell; 9. hydrogen bottle assembly; 10. gas bottle valve; 11. vortex tube; 12. first temperature sensor; 13. condenser; 14. water collector; 15. first solenoid valve; 16. second solenoid valve; 17. ultrasonic atomizer; 18. second temperature sensor; 19. third solenoid valve; 20. water pump. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] The embodiment of the present invention provides a modular fuel cell drone, as shown in the attached Figure 1-3 As shown, the UAV comprises a fuselage 1, a plurality of power modules 2 and a plurality of connecting shafts 3, and each power module 2 is detachably connected to the fuselage 2 via a connecting shaft 3;

[0038] The fuselage 1 is provided with electrical equipment, a hydrogen source storage area and a cargo area. The hydrogen source storage area is used to store the hydrogen bottle assembly 9; the cargo area is used to place the cargo to be transported;

[0039] The power module 2 includes a fan and a small air-cooled hydrogen fuel cell 8, wherein the fan is used to provide cathode gas for the small air-cooled hydrogen fuel cell 8 and is also used to cool and dissipate heat for the small air-cooled hydrogen fuel cell 8;

[0040] The connecting shaft 3 includes an information transmission line, an electric circuit and a hydrogen supply pipeline;

[0041] The power of the power module 2 is selected according to the weight of the cargo to be transported by the drone. When the weight of the cargo to be transported is large, a power module with larger power is selected for installation. When the weight of the cargo to be transported is small, a power module with smaller power is selected for installation.

[0042] The fan includes a motor 5, blades 6, an upper shell 7 and a lower shell 4. The upper shell 7 and the lower shell 4 are both hollow structures. The upper shell 7 and the lower shell 4 are buckled together. The motor and the blades are both located in the upper shell 7 and the lower shell 4. The motor 5 is fixed on the inner side of the lower shell 4. The output end of the motor 5 is connected to the rotating shaft of the blade 6. The small air-cooled hydrogen fuel cell 8 is fixed on the outer side of the upper shell 7.

[0043] The shape of the hollow structure on the lower shell 7 matches the shape of the small air-cooled hydrogen fuel cell 8. The small air-cooled hydrogen fuel cell 8 is fixedly mounted on the hollow structure of the lower shell 7, and the hollow structure of the lower shell 7 on the outer side of the small air-cooled hydrogen fuel cell 8 fits tightly, which can prevent the airflow from escaping from the gap, resulting in a decrease in air supply and heat dissipation efficiency.

[0044] The direction of the cathode flow channel of the small air-cooled hydrogen fuel cell 8 is parallel to the direction of the rotating shaft of the fan blade 6, so that the blade 6 can provide cathode gas to the small air-cooled fuel cell 8 when rotating, and can also cool and dissipate the heat of the small air-cooled fuel cell 8. By using the fan to provide cathode gas to the small air-cooled hydrogen fuel cell 8 and cool and dissipate the heat of the small air-cooled hydrogen fuel cell 8, the endurance of the drone is greatly improved, the overall complexity and weight of the drone are reduced, and the use cost is reduced.

[0045] By splitting a single power source into multiple power modules, the UAV can be prevented from crashing due to a single power source failure during flight. At the same time, after being split into multiple power modules, when a power module fails, it is also easy to repair and replace, effectively reducing maintenance costs. By separating the fuselage from the power source and selecting a power module with appropriate power according to the weight of the goods that the fuselage needs to transport, simply replacing the power module can meet different load requirements. When the load is low, a power module with low power can be selected to reduce the energy waste caused by the weight of the battery stack itself. When the load is high, a power module with high power can be selected to prevent the problem of insufficient power of the battery stack and the fan when the load is high; at the same time, it can also avoid the low efficiency of the system caused by the weight of a single high-power air-cooled fuel cell, making the UAV's capacity utilization efficiency high and the application scenario more flexible. In addition, using multiple power modules as the power source of the UAV effectively reduces the number of single cells in each battery, makes the water vapor distribution inside the battery stack more uniform, increases the service life of the battery stack, and reduces the replacement cost when it is damaged.

[0046] The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell 8 includes a hydrogen bottle assembly 9, a vortex tube 11, a condenser 13, a first solenoid valve 15, a second solenoid valve 16, and a third solenoid valve 19. The hydrogen bottle assembly 9 is connected to the inlet of the vortex tube 11, and the hot flow outlet of the vortex tube 11 is connected to the anode inlet of the small air-cooled hydrogen fuel cell 8 through a pipeline; the cold flow outlet of the vortex tube 11 is connected to the inlet of the condenser 13, and the outlet of the condenser 13 is connected to a T-shaped pipe, one branch of the T-shaped pipe is connected to the first solenoid valve 15 and the anode inlet of the small air-cooled hydrogen fuel cell 8 in sequence, and the other branch of the T-shaped pipe is provided with a second solenoid valve 16 for controlling whether the gas at the cold flow outlet of the vortex tube 11 is discharged outside the gas supply subsystem; a water collector 14 is provided below the condenser 13; the anode outlet of the small air-cooled hydrogen fuel cell 8 is connected to a pipeline, and the third solenoid valve 19 is provided on the pipeline for controlling whether the exhaust gas and water generated by the anode of the small air-cooled hydrogen fuel cell 8 are discharged outside the hydrogen supply subsystem.

[0047] The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell 8 also includes a water collector 14, an ultrasonic atomizer 17 and a water pump 20. The water collector 14 is arranged directly below the condenser 13, and is used to collect liquid water condensed in the condenser 13. A liquid water outlet is arranged at the bottom of the water collector 14, and the liquid water outlet is connected to the ultrasonic atomizer 17 through a pipeline. A water pump 20 is arranged on the connecting pipeline between the liquid water outlet of the water collector 14 and the ultrasonic atomizer 17. The water pump 20 is used to pump out the liquid water collected by the water collector 14 to provide a water source for the ultrasonic atomizer 17. The ultrasonic atomizer 17 is arranged at the upper end of the power module, and is used to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell 8.

[0048] The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell 8 also includes a first temperature sensor 12 and a second temperature sensor 18. The first temperature sensor 12 is arranged at the hot flow outlet of the vortex tube 11, and is used to measure the gas temperature at the hot flow outlet of the vortex tube 11; the second temperature sensor 18 is arranged at the anode outlet of the small air-cooled hydrogen fuel cell 8, and is used to measure the gas temperature at the anode outlet of the small air-cooled hydrogen fuel cell 8.

[0049] The hydrogen bottle assembly 9 includes a plurality of hydrogen bottles, each of which has a bottle valve 10 at its outlet, and the plurality of hydrogen bottles are connected in series to the inlet of the vortex tube 11 .

[0050] The vortex tube 11, the first temperature sensor 12, the condenser 13, the water collector 14, the first solenoid valve 15, the second solenoid valve 16 and the water pump 20 of the hydrogen supply subsystem of the small air-cooled hydrogen fuel cell 8 are all arranged on the fuselage; the second temperature sensor 18 and the third solenoid valve 19 are arranged on the power module 2; the ultrasonic atomizer 17 is arranged on the connecting shaft.

[0051] The present invention also provides a method for operating a small-scale air-cooled hydrogen fuel cell in a modular fuel cell drone, which is as follows:

[0052] The hydrogen in the hydrogen bottle assembly 9 is separated into high-temperature low-pressure hydrogen and low-temperature low-pressure hydrogen under the action of the vortex tube 11. The high-temperature low-pressure hydrogen flows out from the hot flow outlet of the vortex tube 11; the low-temperature low-pressure hydrogen flows out from the cold flow part of the vortex tube 11 and enters the condenser 13 as a cold source, so that the water vapor in the air is condensed in the condenser 13 to form liquid water, and the liquid water enters the water collector 14 under the action of gravity. At the same time, the low-temperature low-pressure hydrogen absorbs heat and heats up. After merging with the high-temperature low-pressure hydrogen flowing out from the hot flow outlet, it enters the fuel cell stack through the anode inlet of the small air-cooled hydrogen fuel cell 8 to participate in the reaction;

[0053] Under the action of the water pump 20, the water in the water collector 14 is pumped out and enters the ultrasonic atomizer 17, where it is atomized and sprayed out through the nozzle of the ultrasonic atomizer 17 to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell 8.

[0054] The working method of the small air-cooled hydrogen fuel cell in the modular fuel cell drone also includes:

[0055] The anode of the small air-cooled hydrogen fuel cell 8 adopts a dead-end mode, and the anode outlet is opened and closed by a third solenoid valve 19. Normally, the third solenoid valve 19 is in a closed state. When the water and exhaust gas in the stack accumulate to a certain level, the third solenoid valve 19 is opened to purge the stack anode and discharge the water and exhaust gas through the pressure difference.

[0056] The working method of the small air-cooled hydrogen fuel cell in the modular fuel cell drone also includes:

[0057] When the ambient temperature is lower than 0°C, the small air-cooled hydrogen fuel cell 8 needs to perform a cold start when it starts. By changing the opening of the hot flow outlet of the vortex tube 11, the heat flow temperature is increased. When the first temperature sensor 12 arranged at the hot flow outlet of the vortex tube 11 measures that the gas temperature at the hot flow outlet reaches the maximum hot pressing temperature of the membrane electrode, the gas flowing out of the hot flow outlet of the vortex tube 11 is used to purge the small air-cooled hydrogen fuel cell 8. At this time, the second battery valve 16 is opened and the first solenoid valve 15 is closed, and the low-temperature hydrogen flowing out of the cold flow outlet of the vortex tube 11 is directly discharged to the hydrogen supply subsystem; when the second temperature sensor arranged at the anode outlet of the small air-cooled hydrogen fuel cell 8 measures that the temperature of the anode outlet reaches above 0°C, the cold start is completed; then the second solenoid valve 16 is closed, the first solenoid valve 15 is opened, the hot flow outlet of the vortex tube 11 is adjusted to a normal opening, and normal operation begins.

[0058] By using the low-temperature hydrogen separated by the vortex tube as the cold source of the condenser, the water vapor in the air is condensed in the condenser to form liquid water, and the liquid water is collected by the collector, thereby realizing the humidification of the cathode gas entering the small air-cooled hydrogen fuel cell, and increasing the performance and working efficiency of the fuel cell stack. By setting a small air-cooled hydrogen fuel cell cold start, the high-temperature hydrogen separated by the vortex tube is used to purge the small air-cooled hydrogen fuel cell, without the need for an additional heat source, so that the small air-cooled hydrogen fuel cell can be cold-started quickly, increasing the applicability of drones in cold areas.

[0059] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A modular fuel cell drone, characterized in that: The drone comprises a fuselage (1), a plurality of power modules (2) and a plurality of connecting shafts (3), wherein each power module (2) is detachably connected to the fuselage (2) via a connecting shaft (3); The fuselage (1) is provided with electrical equipment, a hydrogen source storage area and a cargo area, wherein the hydrogen source storage area is used to store hydrogen bottle assemblies (9); and the cargo area is used to place cargo to be transported; The power module (2) comprises a fan and a small air-cooled hydrogen fuel cell (8), wherein the fan is used to provide cathode gas for the small air-cooled hydrogen fuel cell (8) and is also used to cool and dissipate heat for the small air-cooled hydrogen fuel cell (8); The connecting shaft (3) includes an information transmission line, an electric circuit and a hydrogen supply pipeline; The power of the power module (2) is selected according to the weight of the cargo that the drone needs to transport.

2. The modular fuel cell drone according to claim 1, characterized in that: The fan comprises a motor (5), blades (6), an upper shell (7) and a lower shell (4); the upper shell (7) and the lower shell (4) are both hollow structures; the upper shell (7) and the lower shell (4) are buckled together; the motor and the blades are both located inside the upper shell (7) and the lower shell (4); the motor (5) is fixed on the inner side of the lower shell (4); the output end of the motor (5) is connected to the rotating shaft of the blade (6); and the small air-cooled hydrogen fuel cell (8) is fixed on the outer side of the upper shell (7).

3. The modular fuel cell drone according to claim 2, characterized in that: The shape of the hollow structure on the lower shell (7) matches the shape of the small air-cooled hydrogen fuel cell (8); the small air-cooled hydrogen fuel cell (8) is fixedly mounted on the hollow structure of the lower shell (7), and the hollow structure of the lower shell (7) on the outside of the small air-cooled hydrogen fuel cell (8) fits tightly.

4. The modular fuel cell drone according to claim 2, characterized in that: The direction of the cathode flow channel of the small air-cooled hydrogen fuel cell (8) is parallel to the direction of the rotation axis of the fan blade (6).

5. The modular fuel cell drone according to claim 2, characterized in that: The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell (8) comprises a hydrogen bottle assembly (9), a vortex tube (11), a condenser (13), a first solenoid valve (15), a second solenoid valve (16), and a third solenoid valve (19); the hydrogen bottle assembly (9) is connected to the inlet of the vortex tube (11); the hot flow outlet of the vortex tube (11) is connected to the anode inlet of the small air-cooled hydrogen fuel cell (8) through a pipeline; the cold flow outlet of the vortex tube (11) is connected to the inlet of the condenser (13); the outlet of the condenser (13) is connected to a T-shaped pipe, and one of the T-shaped pipes is connected to the inlet of the condenser (13); The branches are connected in sequence to the first solenoid valve (15) and the anode inlet of the small air-cooled hydrogen fuel cell (8); a second solenoid valve (16) is provided on the other branch of the T-shaped pipe to control whether the gas at the cold flow outlet of the vortex tube (11) is discharged outside the gas supply subsystem; a water collector (14) is provided below the condenser (13); the anode outlet of the small air-cooled hydrogen fuel cell (8) is connected to a pipeline, and a third solenoid valve (19) is provided on the pipeline to control whether the waste gas and water generated by the anode of the small air-cooled hydrogen fuel cell (8) are discharged outside the hydrogen supply subsystem.

6. The modular fuel cell drone according to claim 5, characterized in that: The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell (8) further comprises a water collector (14), an ultrasonic atomizer (17) and a water pump (20). The water collector (14) is arranged directly below the condenser (13) and is used to collect liquid water condensed in the condenser (13). A liquid water outlet is arranged at the bottom of the water collector (14), and the liquid water outlet is connected to the ultrasonic atomizer (17) through a pipeline. A water pump (20) is arranged on the connecting pipeline between the liquid water outlet of the water collector (14) and the ultrasonic atomizer (17). The water pump (20) is used to pump out the liquid water collected by the water collector (14) to provide a water source for the ultrasonic atomizer (17). The ultrasonic atomizer (17) is arranged at the upper end of the power module and is used to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell (8).

7. The modular fuel cell drone according to claim 1, characterized in that: The hydrogen supply subsystem of the small air-cooled hydrogen fuel cell (8) further comprises a first temperature sensor (12) and a second temperature sensor (18), wherein the first temperature sensor (12) is arranged at the heat flow outlet of the vortex tube (11) and is used to measure the gas temperature at the heat flow outlet of the vortex tube (11); and the second temperature sensor (18) is arranged at the anode outlet of the small air-cooled hydrogen fuel cell (8) and is used to measure the gas temperature at the anode outlet of the small air-cooled hydrogen fuel cell (8).

8. A method for operating a small-scale air-cooled hydrogen fuel cell for a modular fuel cell drone according to any one of claims 1 to 7, characterized in that: The working method is specifically as follows: The hydrogen in the hydrogen bottle assembly (9) is separated into high-temperature low-pressure hydrogen and low-temperature low-pressure hydrogen under the action of the vortex tube (11). The high-temperature low-pressure hydrogen flows out from the hot flow outlet of the vortex tube (11); the low-temperature low-pressure hydrogen flows out from the cold flow part of the vortex tube (11) and enters the condenser (13) as a cold source, so that water vapor in the air is condensed in the condenser (13) to form liquid water. The liquid water enters the water collector (14) under the action of gravity. At the same time, the low-temperature low-pressure hydrogen absorbs heat to increase its temperature, and after merging with the high-temperature low-pressure hydrogen flowing out from the hot flow outlet, it enters the fuel cell stack through the anode inlet of the small air-cooled hydrogen fuel cell (8) to participate in the reaction; Under the action of the water pump (20), the water in the water collector (14) is pumped out and enters the ultrasonic atomizer (17), where it is atomized and sprayed out through the nozzle of the ultrasonic atomizer (17) to humidify the cathode inlet gas of the small air-cooled hydrogen fuel cell (8).

9. The operating method of a small air-cooled hydrogen fuel cell according to claim 8, characterized in that: The working method also includes: The anode of the small air-cooled hydrogen fuel cell (8) adopts a dead-end mode, and the anode outlet is opened and closed by a third solenoid valve (19). Under normal circumstances, the third solenoid valve (19) is in a closed state. When water and exhaust gas in the fuel cell stack accumulate to a certain level, the third solenoid valve (19) is opened to achieve stack anode purge, and the water and exhaust gas are discharged through the pressure difference.

10. The operating method of a small air-cooled hydrogen fuel cell according to claim 9, characterized in that: The working method also includes: When the ambient temperature is lower than 0°C, a cold start needs to be performed when the small air-cooled hydrogen fuel cell (8) is started. The heat flow temperature is increased by changing the opening of the heat flow outlet of the vortex tube (11). When the first temperature sensor (12) disposed at the heat flow outlet of the vortex tube (11) measures that the gas temperature at the heat flow outlet reaches the maximum hot pressing temperature of the membrane electrode, the gas flowing out of the heat flow outlet of the vortex tube (11) is used to purge the small air-cooled hydrogen fuel cell (8). At this time, the second battery valve (16) is opened and the first solenoid valve (15) is closed, and the low-temperature hydrogen flowing out of the cold flow outlet of the vortex tube (11) is directly discharged from the hydrogen supply subsystem; when the second temperature sensor disposed at the anode outlet of the small air-cooled hydrogen fuel cell (8) measures that the temperature of the anode outlet reaches above 0°C, the cold start is completed; then the second solenoid valve (16) is closed, the first solenoid valve (15) is opened, and the heat flow outlet of the vortex tube (11) is adjusted to a normal opening, and normal operation begins.

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