Hydrogen fuel hybrid power system for unmanned aerial vehicle and working method of hydrogen fuel hybrid power system

Abstract

The invention relates to a hydrogen fuel hybrid power system for an unmanned aerial vehicle and a working method of the hydrogen fuel hybrid power system, in the hybrid power system, a hydrogen fuel cell system and a hydrogen engine system are combined together, and an air filter of an oxygen supply subsystem in the hydrogen fuel cell system is sequentially connected with an air compressor and a first vortex tube; a hot flow outlet of the first vortex tube is connected with a hydrogen engine system through a pipeline; a cold flow outlet of the first vortex tube is sequentially connected with an atomizer and a cooling inlet of the galvanic pile through pipelines, a cooling outlet of the galvanic pile is connected with a cathode inlet of the galvanic pile through a pipeline, and a cathode outlet of the galvanic pile is connected with a hydrogen engine system through a pipeline. Two power systems are combined together to form a hydrogen fuel hybrid power system, strong flight power and long endurance time are provided for the unmanned aerial vehicle, meanwhile, electric energy is provided for electrical equipment in the unmanned aerial vehicle, normal operation of the electrical equipment is guaranteed, meanwhile, a lengthy energy conversion link is not needed, and the energy consumption of the unmanned aerial vehicle is reduced. And the energy utilization rate is effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of fuel cells, and particularly relates to a hydrogen fuel hybrid power system for an unmanned aerial vehicle and a working method thereof. Background Art

[0002] The engine power system is one of the most commonly used power systems for unmanned aerial vehicles. It mainly uses an internal combustion engine or a turbine engine as an energy source. And in order to make the electrical equipment in the unmanned aerial vehicle operate normally, generally, the chemical energy in the fuel needs to be converted into kinetic energy, and then the kinetic energy is converted into electrical energy and stored in a battery, and supplied to the electrical equipment in the form of electrical energy. This long energy conversion link represents a low energy conversion efficiency, and a separate water cooling or air cooling system needs to be set up to dissipate heat from the engine. At the same time, there are also disadvantages such as high noise and high maintenance cost.

[0003] The unmanned aerial vehicle can also use a battery power system, which mainly uses lithium batteries, nickel-metal hydride batteries, polymer batteries, etc. as energy sources, and directly drives the motor to propel the aircraft through power supply. It is widely used in small and light unmanned aerial vehicles, and has the advantages of light weight, low cost, low noise, and easy maintenance. However, its endurance ability is poor, and the power of the unmanned aerial vehicle is insufficient, the moving speed is slow, and the applicable range is relatively narrow.

[0004] The fuel cell power system is an efficient and clean power system for unmanned aerial vehicles. It mainly generates electrical energy through fuels such as hydrogen or methanol, and drives the motor to work, and has the advantages of zero emissions, low noise, low vibration, and long endurance ability.

[0005] Therefore, there is an urgent need to design a hydrogen fuel hybrid power system for an unmanned aerial vehicle and a working method thereof to solve the problems existing in the above-mentioned prior art. Summary of the Invention

[0006] In view of this, the present invention provides a hydrogen fuel hybrid power system for an unmanned aerial vehicle and a working method thereof, aiming to improve the energy utilization rate of the unmanned aerial vehicle through the hybrid power system on the premise of ensuring the speed and endurance ability of the unmanned aerial vehicle.

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

[0008] A hydrogen fuel hybrid power system for an unmanned aerial vehicle, the hybrid power system includes a hydrogen fuel cell system and a hydrogen engine system, and the hydrogen fuel cell system and the hydrogen engine system are combined together;

[0009] The hydrogen fuel cell system includes a hydrogen supply subsystem and an oxygen supply subsystem;

[0010] The oxygen supply subsystem includes an air filter, an air compressor, a first vortex tube, and an atomizer. The air filter is sequentially connected to the air compressor and the inlet of the first vortex tube. The hot flow outlet of the first vortex tube is connected to the hydrogen engine system through a pipeline. The cold flow outlet of the first vortex tube is sequentially connected to the atomizer and the cooling inlet of the fuel cell stack through pipelines. The cooling outlet of the fuel cell stack is connected to the cathode inlet of the fuel cell stack through a pipeline, and the cathode outlet of the fuel cell stack is connected to the hydrogen engine system through a pipeline.

[0011] The hydrogen supply subsystem includes a high-pressure hydrogen cylinder, a hydrogen valve, a second vortex tube, an ejector, and a water separator. A hydrogen valve is provided at the outlet of the high-pressure hydrogen cylinder to control whether the hydrogen in the high-pressure hydrogen cylinder flows out. The outlet of the hydrogen valve is connected to the inlet of the second vortex tube. The hot flow outlet of the second vortex tube is connected to the hydrogen engine system through a pipeline. The cold flow outlet of the second vortex tube is sequentially connected to the ejector and the anode inlet of the fuel cell stack through pipelines. The anode outlet of the fuel cell stack is connected to the water separator, and the gas outlet of the water separator is connected to the ejector through a pipeline.

[0012] Further, a water collector is also provided in the hydrogen engine system. A hydrophilic porous material is provided in the water collector. The hydrogen engine is connected to the water collector. The water collector is used to collect the liquid water generated after the fuel reaction in the hydrogen engine. The gas outlet of the water collector is connected to the outside through a pipeline to discharge the exhaust gas generated in the combustion chamber of the hydrogen engine.

[0013] Further, a water storage tank is also provided in the hydrogen fuel hybrid system. The water storage tank is used to store the liquid water generated during the reaction of the hydrogen fuel cell system and the hydrogen engine system. A pressure stabilizing hole is provided on the water storage tank to maintain the internal pressure of the water storage tank stable.

[0014] Further, the liquid outlet of the water separator is sequentially connected to a first water pump and the water storage tank. The first water pump is used to pump the liquid in the water separator into the water storage tank for storage. The liquid outlet of the water collector is sequentially connected to a second water pump and the water storage tank. The second water pump is used to pump the liquid in the water collector into the water storage tank for storage.

[0015] Further, the hot flow outlet of the first vortex tube is connected to the hydrogen engine through a pipeline to provide fuel for the hydrogen engine. The hot flow outlet of the second vortex tube is connected to the hydrogen engine through a pipeline to provide fuel for the hydrogen engine.

[0016] Further, the cathode outlet of the fuel cell stack is connected to the cooling inlet of the hydrogen engine through a pipeline. The cooling outlet of the hydrogen engine is connected to the outside through a pipeline, and the pipeline is arranged in parallel with the pipeline connected to the gas outlet of the water collector.

[0017] Further, the liquid outlet of the water storage tank is sequentially connected to a third water pump and the atomizer. The third water pump is used to pump the liquid in the water storage tank into the atomizer to provide a water source for the atomizer.

[0018] The present invention also provides a working method based on the above hydrogen fuel hybrid power system for drones, and the specific working method is as follows:

[0019] Open the hydrogen valve, and the hydrogen in the high-pressure hydrogen cylinder flows out of the second vortex tube, where it is separated into a cold stream and a hot stream. The high-temperature hydrogen as the hot stream part flows out of the hot stream outlet of the second vortex tube and enters the hydrogen engine as fuel; the low-temperature hydrogen as the cold stream part flows out of the cold stream outlet of the second vortex tube, enters the ejector, and then enters the stack through the anode inlet of the stack to participate in the reaction. The anode product enters the water separator, where gas-liquid separation is completed. The separated gas enters the ejector again, and the separated liquid is pumped into the water storage tank by the first water pump for storage;

[0020] After the air is filtered by the air filter to remove harmful gases and impurities, it enters the air compressor and is compressed, and then is separated into a cold stream and a hot stream in the first vortex tube. The high-temperature air as the hot stream part flows out of the hot stream outlet of the first vortex tube and enters the hydrogen engine as fuel to carry out a combustion reaction with the high-temperature hydrogen; the low-temperature air as the cold stream part enters the atomizer and is fully atomized so that the water mist is evenly distributed in the low-temperature air, and then enters the cooling flow channel inside the stack through the cooling inlet of the stack. The low-temperature air mixed with the water mist absorbs heat in the stack to dissipate heat and cool the stack; at the same time, the temperature of the low-temperature air in the cooling flow channel rises to the stack temperature to form a suitable temperature and high-humidity air, and then flows out of the cooling outlet of the stack, flows through the pipeline to the cathode inlet of the stack, and enters the stack to participate in the reaction; the cathode product is discharged from the cathode outlet of the stack, and the cathode product carrying part of the liquid water enters from the cooling inlet of the hydrogen engine to cool the hydrogen engine, and then is discharged from the cooling outlet of the hydrogen engine.

[0021] Further, the temperature of the waste gas generated after the high-temperature air and the high-temperature hydrogen work in the combustion chamber of the hydrogen engine drops rapidly, and the water vapor part of it condenses into liquid water, which is collected by the water collector. The waste gas is then discharged through the pipeline to drive the drone forward. The liquid water collected by the water collector enters the water storage tank under the action of the second water pump for storage.

[0022] Further, the third water pump pumps the liquid in the water storage tank into the atomizer to provide water source for the atomizer.

[0023] Compared with the prior art, the beneficial effects of the present invention are:

[0024] (1) By combining a hydrogen fuel cell and a hydrogen engine together to form a hydrogen fuel hybrid system, it provides strong flight power and a long endurance time for the drone, and at the same time provides electrical energy for the electrical equipment in the drone, ensuring the normal operation of the electrical equipment without going through a long energy conversion link, effectively improving the energy utilization rate.

[0025] (2) By respectively arranging vortex tubes in the hydrogen supply subsystem and the oxygen supply subsystem, using the vortex tubes to convert the potential energy of the compressed air generated by the air compressor and the potential energy of the compressed hydrogen in the high-pressure hydrogen cylinder into internal energy, and sending the high-temperature hydrogen and high-temperature air into the hydrogen engine for combustion reaction, fully utilizing the potential energy of the air compressor and the high-pressure hydrogen cylinder to assist the combustion reaction process, and finally converting it into kinetic energy, improving the energy conversion efficiency.

[0026] (3) By making the air flowing out from the cold end of the vortex tube in the oxygen supply subsystem first be used for the heat dissipation of the fuel cell stack and then for the cathode gas supply, canceling the cooling path subsystem in the traditional fuel cell, increasing the system integration degree and efficiency, and reducing the cost.

[0027] (4) By setting up a water storage device to collect the liquid water from the hydrogen engine and the anode of the fuel cell, and using the liquid water in the water storage device as the water source of the atomizer, atomizing the liquid water and spraying it into the air through the atomizer to enhance the heat dissipation ability of the air to the stack, and the air used for cooling will then enter the anode of the stack to participate in the reaction, that is, the self-humidification of the air is also completed at the same time.

[0028] (5) By discharging the waste gas generated at the cathode of the fuel cell into the cooling path of the hydrogen engine for cooling the hydrogen engine, canceling the traditional hydrogen engine cooling system, and further improving the system integration degree.

[0029] Other features and advantages of the present invention will be described in the subsequent specification, and part of them will be obvious from the specification or understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the structures pointed out in the specification and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0031] Figure 1 The structural schematic diagram of the embodiment of the present invention is shown.

[0032] In the figure: 1. Air filter; 2. Air compressor; 3. First vortex tube; 4. Hydrogen engine; 5. Water collector; 6. Second vortex tube; 7. Hydrogen valve; 8. High-pressure hydrogen cylinder; 9. Ejector; 10. Stack; 11. Water separator; 12. First water pump; 13. Second water pump; 14. Water storage tank; 15. Atomizer; 16. Third water pump. Detailed implementation mode

[0033] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0034] An embodiment of the present invention provides a hydrogen fuel hybrid power system for an unmanned aerial vehicle. As shown in the attached Figure 1 figure, the hybrid power system includes a hydrogen fuel cell system and a hydrogen engine system, and the hydrogen fuel cell system and the hydrogen engine system are combined together;

[0035] The hydrogen fuel cell system includes a hydrogen supply subsystem and an oxygen supply subsystem;

[0036] The oxygen supply subsystem includes an air filter 1, an air compressor 2, a first vortex tube 3, and an atomizer 15. The air filter 1 is sequentially connected to the air compressor 2 and the inlet of the first vortex tube 3. The hot flow outlet of the first vortex tube 3 is connected to the hydrogen engine system through a pipeline; the cold flow outlet of the first vortex tube 3 is sequentially connected to the atomizer 15 and the cooling inlet of the stack 10 through a pipeline. The cooling outlet of the stack 10 is connected to the cathode inlet of the stack 10 through a pipeline, and the cathode outlet of the stack 10 is connected to the hydrogen engine system through a pipeline;

[0037] The hydrogen supply subsystem includes a high-pressure hydrogen cylinder 8, a hydrogen valve 7, a second vortex tube 6, an ejector 9, and a water separator 11. A hydrogen valve 7 is provided at the outlet of the high-pressure hydrogen cylinder 8 to control whether the hydrogen in the high-pressure hydrogen cylinder 8 flows out. The outlet of the hydrogen valve 7 is connected to the inlet of the second vortex tube 6. The hot flow outlet of the second vortex tube 6 is connected to the hydrogen engine system through a pipeline; the cold flow outlet of the second vortex tube 6 is sequentially connected to the ejector 9 and the anode inlet of the stack 10 through a pipeline; the anode outlet of the stack 10 is connected to the water separator 11, and the gas outlet of the water separator 11 is connected to the ejector 9 through a pipeline.

[0038] The hot flow outlet of the first vortex tube 3 is connected to the hydrogen engine 4 through a pipeline to provide fuel for the hydrogen engine 4; the hot flow outlet of the second vortex tube 6 is connected to the hydrogen engine 4 through a pipeline to provide fuel for the hydrogen engine 4.

[0039] The hydrogen engine system is further provided with a water collector 5. A hydrophilic porous material is arranged inside the water collector 5, which adsorbs liquid water while avoiding flow resistance to the air flow and causing power loss. The hydrogen engine 4 is connected to the water collector 5. The water collector 5 is used to collect the liquid water generated after the fuel reaction in the hydrogen engine 4. The gas outlet of the water collector 5 is communicated with the outside through a pipeline, and is used to discharge the waste gas generated in the combustion chamber of the hydrogen engine 4.

[0040] The hydrogen fuel hybrid system is further provided with a water storage tank 14. The water storage tank 14 is used to store the liquid water generated during the reaction of the hydrogen fuel cell system and the hydrogen engine system. A pressure stabilizing hole is opened on the water storage tank 14, which is used to maintain the internal pressure of the water storage tank 14 stable.

[0041] The liquid outlet of the water separator 11 is sequentially connected to the first water pump 12 and the water storage tank 14. The first water pump 12 is used to pump the liquid in the water separator 11 into the water storage tank 14 for storage.

[0042] The liquid outlet of the water collector 5 is sequentially connected to the second water pump 13 and the water storage tank 14. The second water pump 13 is used to pump the liquid in the water collector 5 into the water storage tank 14 for storage.

[0043] The liquid outlet of the water storage tank 14 is sequentially connected to the third water pump 16 and the atomizer 15. The third water pump 16 is used to pump the liquid in the water storage tank 14 into the atomizer 15 to provide a water source for the atomizer 15.

[0044] The cathode outlet of the fuel cell stack 10 is connected to the cooling inlet of the hydrogen engine 4 through a pipeline. The cooling outlet of the hydrogen engine 4 is communicated with the outside through a pipeline, and the pipeline is arranged in parallel with the pipeline connected to the gas outlet of the water collector 5. By arranging the pipeline of the hydrogen engine cooling outlet in parallel with the main power gas discharge pipeline of the hydrogen engine, the kinetic energy can be further recovered to assist the propulsion of the drone.

[0045] An embodiment of the present invention also proposes a working method based on the above hydrogen fuel hybrid system for drones, and the working method is specifically as follows:

[0046] Open the hydrogen valve 7, and the hydrogen in the high-pressure hydrogen cylinder 8 flows out of the second vortex tube 6. In the second vortex tube 6, it is separated into a cold stream and a hot stream. The high-temperature hydrogen as the hot stream part flows out of the hot stream outlet of the second vortex tube 6 and enters the hydrogen engine 4 as fuel. The high-temperature hydrogen helps combustion to generate thrust, improving the utilization rate of hydrogen potential energy; the low-temperature hydrogen as the cold stream part flows out of the cold stream outlet of the second vortex tube 6, enters the ejector 9, and then enters the stack 10 through the anode inlet of the stack 10 to participate in the reaction. The anode product enters the water separator 11, where gas-liquid separation is completed. The separated gas enters the ejector 9 again, and the separated liquid is pumped into the water storage tank 14 by the first water pump 12 for storage;

[0047] After the air filters out harmful gases and impurities through the air filter 1, it enters the air compressor 2 and is compressed. Then, in the first vortex tube 3, it is separated into a cold stream and a hot stream. The high-temperature air as the hot stream part flows out of the hot stream outlet of the first vortex tube 3 and enters the hydrogen engine 4 as fuel to carry out a combustion reaction with the high-temperature hydrogen; the low-temperature air as the cold stream part enters the atomizer 15 and is fully atomized so that the water mist is evenly distributed in the low-temperature air. Then, it enters the cooling flow channel inside the stack through the cooling inlet of the stack 10. The low-temperature air mixed with the water mist absorbs heat in the stack to dissipate heat and cool down the stack; at the same time, the temperature of the low-temperature air in the cooling flow channel rises to the stack temperature, forming a suitable-temperature and high-humidity air. Then, it flows out of the cooling outlet of the stack 10, flows through the pipeline to the cathode inlet of the stack 10, and enters the stack 10 to participate in the reaction. The suitable-temperature and high-humidity air with a temperature close to the stack temperature will not cause uneven performance of single cells due to a large temperature difference in the stack; the cathode product is discharged from the cathode outlet of the stack 10. The temperature of the cathode product remains basically unchanged, while the humidity further increases, even carrying some liquid water. The cathode product carrying some liquid water enters from the cooling inlet of the hydrogen engine 4 to cool the hydrogen engine 4, and then is discharged from the cooling outlet of the hydrogen engine 4. The liquid water in the anode product undergoes a phase change during the cooling process, further enhancing its heat dissipation ability.

[0048] By discharging the waste gas generated at the cathode of the fuel cell into the cooling circuit of the hydrogen engine to dissipate heat for the hydrogen engine, the traditional heat dissipation system of the hydrogen engine is cancelled, further improving the system integration degree.

[0049] After the waste gas generated by the combustion of high-temperature air and high-temperature hydrogen in the combustion chamber of the hydrogen engine 4 works, its temperature drops rapidly. Part of the water vapor in it condenses into liquid water, which is collected by the water collector 5, and the waste gas is discharged through the pipeline to push the UAV forward. The liquid water collected by the water collector 5 enters the water storage tank 14 for storage under the action of the second water pump 13.

[0050] The third water pump 16 pumps the liquid in the water storage device 14 into the atomizer 15 to provide a water source for the atomizer 15. The liquid water generated in the hydrogen fuel hybrid system is fully recycled to achieve self-humidification of the system.

[0051] In this application, a hydrogen fuel hybrid system is formed by combining a hydrogen fuel cell and a hydrogen engine, which not only provides strong flight power and a long endurance time for the drone, but also provides electrical energy for the electrical equipment in the drone. While ensuring the normal operation of the electrical equipment, there is no need for a long energy conversion link, effectively improving the energy utilization rate.

[0052] By respectively arranging vortex tubes in the hydrogen supply subsystem and the oxygen supply subsystem, the potential energy generated by the compressed air of the air compressor and the potential energy of the compressed hydrogen in the high-pressure hydrogen cylinder are converted into internal energy by the vortex tubes. The high-temperature hydrogen and high-temperature air are sent into the hydrogen engine for combustion reaction, making full use of the potential energy of the air compressor and the high-pressure hydrogen cylinder to assist the combustion reaction process, and finally converted into kinetic energy, improving the energy conversion efficiency.

[0053] By making the air flowing out from the cold end of the vortex tube in the oxygen supply subsystem first be used for heat dissipation of the fuel cell stack and then for cathode gas supply, the cooling path subsystem in the traditional fuel cell is cancelled, increasing the system integration degree and efficiency and reducing the cost.

[0054] By setting a water storage device to collect the liquid water from the hydrogen engine and the anode of the fuel cell, and using the liquid water in the water storage device as the water source of the atomizer, the liquid water is atomized and sprayed into the air by the atomizer to enhance the heat dissipation capacity of the air to the stack, and the air used for cooling will then enter the anode of the stack to participate in the reaction, that is, the self-humidification of the air is also completed at the same time.

[0055] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements 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 hydrogen fuel hybrid system for an unmanned aerial vehicle, characterized in that, The hybrid power system includes a hydrogen fuel cell system and a hydrogen engine system, and the hydrogen fuel cell system and the hydrogen engine system are combined together; The hydrogen fuel cell system includes a hydrogen supply subsystem and an oxygen supply subsystem; The oxygen supply subsystem includes an air filter, an air compressor, a first vortex tube, and an atomizer. The air filter is sequentially connected to the air compressor and the inlet of the first vortex tube. The hot flow outlet of the first vortex tube is connected to the hydrogen engine system through a pipeline; the cold flow outlet of the first vortex tube is sequentially connected to the atomizer and the cooling inlet of the fuel cell stack through a pipeline. The cooling outlet of the fuel cell stack is connected to the cathode inlet of the fuel cell stack through a pipeline, and the cathode outlet of the fuel cell stack is connected to the hydrogen engine system through a pipeline; The hydrogen supply subsystem includes a high-pressure hydrogen cylinder, a hydrogen valve, a second vortex tube, an ejector, and a water separator. A hydrogen valve is provided at the outlet of the high-pressure hydrogen cylinder to control whether the hydrogen in the high-pressure hydrogen cylinder flows out. The outlet of the hydrogen valve is connected to the inlet of the second vortex tube. The hot flow outlet of the second vortex tube is connected to the hydrogen engine system through a pipeline; the cold flow outlet of the second vortex tube is sequentially connected to the ejector and the anode inlet of the fuel cell stack through a pipeline; the anode outlet of the fuel cell stack is connected to the water separator, and the gas outlet of the water separator is connected to the ejector through a pipeline.

2. The hydrogen fuel hybrid system for an unmanned aerial vehicle according to claim 1, characterized in that, The hydrogen engine system is further provided with a water collector. A hydrophilic porous material is provided in the water collector. The hydrogen engine is connected to the water collector. The water collector is used to collect the liquid water generated after the fuel reaction in the hydrogen engine. The gas outlet of the water collector is communicated with the outside through a pipeline to discharge the waste gas generated in the combustion chamber of the hydrogen engine.

3. The hydrogen fuel hybrid system for an unmanned aerial vehicle according to claim 2, characterized in that, The hydrogen fuel hybrid power system is further provided with a water storage tank. The water storage tank is used to store the liquid water generated during the reaction of the hydrogen fuel cell system and the hydrogen engine system. A pressure stabilizing hole is provided on the water storage tank to maintain the internal pressure of the water storage tank stable.

4. The hydrogen fuel hybrid system for an unmanned aerial vehicle according to claim 3, wherein, The liquid outlet of the water separator is sequentially connected to a first water pump and the water storage tank. The first water pump is used to pump the liquid in the water separator into the water storage tank for storage; the liquid outlet of the water collector is sequentially connected to a second water pump and the water storage tank. The second water pump is used to pump the liquid in the water collector into the water storage tank for storage.

5. The hydrogen fuel hybrid system for a drone according to claim 1, wherein The hot flow outlet of the first vortex tube is connected to the hydrogen engine through a pipeline to provide fuel for the hydrogen engine; the hot flow outlet of the second vortex tube is connected to the hydrogen engine through a pipeline to provide fuel for the hydrogen engine.

6. The hydrogen fuel hybrid system for an unmanned aerial vehicle according to claim 5, wherein, The cathode outlet of the fuel cell stack is connected to the cooling inlet of the hydrogen engine through a pipeline. The cooling outlet of the hydrogen engine is communicated with the outside through a pipeline, and the pipeline is arranged in parallel with the pipeline connected to the gas outlet of the water collector.

7. The hydrogen fuel hybrid system for an unmanned aerial vehicle according to claim 3, characterized in that, The liquid outlet of the water storage tank is sequentially connected to a third water pump and the atomizer. The third water pump is used to pump the liquid in the water storage tank into the atomizer to provide a water source for the atomizer.

8. A working method of the hydrogen fuel hybrid power system for an unmanned aerial vehicle according to any one of claims 1-7, characterized in that, The specific working method is as follows: Open the hydrogen valve, and the hydrogen in the high-pressure hydrogen cylinder flows out of the second vortex tube. In the second vortex tube, it is separated into a cold stream and a hot stream. The high-temperature hydrogen as the hot stream part flows out of the hot stream outlet of the second vortex tube and enters the hydrogen engine as fuel; the low-temperature hydrogen as the cold stream part flows out of the cold stream outlet of the second vortex tube, enters the ejector, and then enters the stack through the anode inlet of the stack to participate in the reaction. The anode product enters the water separator, and gas-liquid separation is completed in the water separator. The separated gas enters the ejector again, and the separated liquid is pumped into the water storage tank by the first water pump for storage; After the air is filtered by the air filter to remove harmful gases and impurities, it enters the air compressor and is compressed. Then it is separated into a cold stream and a hot stream in the first vortex tube. The high-temperature air as the hot stream part flows out of the hot stream outlet of the first vortex tube and enters the hydrogen engine as fuel to carry out a combustion reaction with the high-temperature hydrogen; The low-temperature air as the cold stream part enters the atomizer and is fully atomized so that the water mist is evenly distributed in the low-temperature air. Then it enters the cooling flow channel inside the stack through the cooling inlet of the stack. The low-temperature air mixed with the water mist absorbs heat in the stack to dissipate heat and cool down the stack; at the same time, the temperature of the low-temperature air in the cooling flow channel rises to the stack temperature to form a suitable-temperature and high-humidity air, and then it flows out of the cooling outlet of the stack, flows through the pipeline to the cathode inlet of the stack, and enters the stack to participate in the reaction; The cathode product is discharged from the cathode outlet of the stack. The cathode product carrying part of the liquid water enters from the cooling inlet of the hydrogen engine to cool the hydrogen engine, and then is discharged from the cooling outlet of the hydrogen engine.

9. The working method of the human-machine hydrogen fuel hybrid power system according to claim 8, characterized in that, The temperature of the exhaust gas generated after the high-temperature air and high-temperature hydrogen do work in the combustion chamber of the hydrogen engine drops rapidly. The water vapor part of it condenses into liquid water, which is collected by the water collector. The exhaust gas is then discharged through the pipeline to push the drone forward. The liquid water collected by the water collector enters the water storage tank for storage under the action of the second water pump.

10. The working method of the human-machine hydrogen fuel hybrid power system according to claim 8, characterized in that, The third water pump pumps the liquid in the water storage tank into the atomizer to provide water source for the atomizer.

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