Liquid hydrogen fuel cell unmanned aerial vehicle thermal management system

Abstract

The invention discloses a liquid hydrogen fuel cell unmanned aerial vehicle thermal management system, relates to the technical field of unmanned aerial vehicles, and solves the problem of temperature management in the flight process of an unmanned aerial vehicle. The system comprises a liquid hydrogen storage tank, a heat exchanger II, a hydrogen pump, an air compressor, a fuel cell, a power management module, a lithium battery, a motor, a phase change heat reservoir and a cooling system, wherein the liquid hydrogen storage tank, a cold end of the heat exchanger II, the hydrogen pump and an anode of the fuel cell are sequentially communicated; the air compressor is communicated with the cathode of the fuel cell; the phase change heat reservoir and the liquid cooling heat management system are used for cooling the fuel cell; the fuel cell, the power management module and the motor are sequentially connected; the lithium battery is connected with the power management module; and the phase change heat reservoir absorbs heat generated by the motor and the lithium battery during working. Liquid hydrogen vaporization is assisted through heat generated by the fuel battery lithium battery and the motor, efficient recycling of energy is achieved, energy waste is reduced, the energy utilization efficiency of the whole system is improved, and the endurance time of the unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a liquid hydrogen fuel cell unmanned aerial vehicle thermal management system. Background Art

[0002] With the rapid development of UAV technology, UAVs have shown great application potential in many fields such as military reconnaissance, civil aerial photography, logistics and transportation. However, the endurance and flight stability of UAVs have always been the key technical bottlenecks restricting their further development. Traditional UAV power sources mainly include fuel and lithium batteries. Although fuel UAVs can provide relatively long flight time, the exhaust gas and noise they emit have a certain impact on the environment, and the maintenance cost is high. Although lithium battery UAVs have the advantages of zero emissions and low noise, their endurance time is relatively short, and they are prone to overheating problems under high-intensity flight, thus affecting flight stability.

[0003] As a new type of power source, liquid hydrogen fuel cells have become a research hotspot in the field of drones due to their significant advantages such as high energy density, long flight time and zero emissions. Liquid hydrogen fuel cells convert hydrogen and oxygen into electrical energy through electrochemical reactions. Not only are they highly efficient in energy conversion, but they also emit only water, making them environmentally friendly. However, liquid hydrogen fuel cells generate a lot of heat during operation. If this heat cannot be dissipated in time, it will cause the internal temperature of the fuel cell to rise, thereby affecting its performance and life. What's more serious is that excessive temperatures may also cause drone failures and even flight accidents. In order to fully utilize the advantages of liquid hydrogen fuel cells and solve their heat dissipation problems, researchers have begun to explore effective thermal management systems. It is worth noting that liquid hydrogen absorbs a lot of heat during the vaporization process, and this part of the heat can be used to dissipate heat in the fuel cell, thereby reducing the operating temperature of the battery and improving its stability and life.

[0004] Therefore, developing a thermal management system that can efficiently manage the heat generated by liquid hydrogen fuel cell drones during flight and make full use of the heat generated by liquid hydrogen vaporization is of great significance for improving the endurance and flight stability of drones. Summary of the invention

[0005] In order to solve the temperature management problem of the UAV mentioned above during flight, the present invention proposes a liquid hydrogen fuel cell UAV thermal management system. The present invention assists the vaporization of liquid hydrogen through the heat generated by fuel cells, lithium batteries and motors, thereby achieving efficient recycling of energy. This design not only reduces energy waste, but also improves the energy utilization efficiency of the entire system and prolongs the flight time of the UAV.

[0006] The present invention proposes a liquid hydrogen fuel cell UAV thermal management system, which specifically includes a liquid hydrogen storage tank, a second heat exchanger, a hydrogen pump, an air compressor, a fuel cell, a power management module, a motor, a phase change heat storage device and a cooling system. The liquid hydrogen storage tank, the cold end of the second heat exchanger, the hydrogen pump and the anode of the fuel cell are connected in sequence; the air compressor and the cathode of the fuel cell are connected; the fuel cell is respectively connected to the phase change heat storage device and the liquid cooling thermal management system to dissipate heat for the fuel cell; the fuel cell, the power management module and the motor are connected in sequence; one end of the phase change heat storage device is connected to the motor to absorb the heat generated by the motor, and the other end is connected to the hot end of the second heat exchanger.

[0007] Furthermore, heat exchanger one is arranged between the liquid hydrogen storage tank and heat exchanger two, and the liquid hydrogen storage tank, the cold end of heat exchanger one and the cold end of heat exchanger two are connected in sequence; the hot end inlet of heat exchanger one is connected to the atmosphere, and the hot end outlet is connected to the inlet of the air compressor.

[0008] Furthermore, a gas-liquid separator is provided between the cold end of the second heat exchanger and the hydrogen pump, and the liquid outlet of the gas-liquid separator is connected to the cold end inlet of the first heat exchanger through the liquid hydrogen circulation pump; the gas outlet of the gas-liquid separator is connected to the hydrogen pump.

[0009] Furthermore, the liquid-cooled thermal management system includes a coolant storage tank, a radiator and a coolant pump, and the fuel cell is connected to the coolant storage tank and the phase change heat storage device through a main pipeline; the coolant storage tank, the radiator and the coolant pump are connected in sequence, and the coolant pump outlet is connected to the fuel cell.

[0010] Furthermore, a temperature sensor is arranged on the main pipe.

[0011] Furthermore, a second solenoid valve is provided between the coolant pump outlet and the fuel cell.

[0012] Furthermore, a solenoid valve 1 is provided between the hydrogen pump and the anode of the fuel cell.

[0013] Furthermore, a pressure sensor is provided between an outlet of the solenoid valve and an anode of the battery.

[0014] Furthermore, it also includes a controller, which is connected to the solenoid valve 1, the temperature sensor, the solenoid valve 2 and the pressure sensor respectively.

[0015] Furthermore, it also includes a lithium battery, which is connected to the power management module and the phase change heat storage device respectively.

[0016] The beneficial effects of the liquid hydrogen fuel cell UAV thermal management system described in the present invention are:

[0017] (1) The thermal management system for a liquid hydrogen fuel cell drone described in the present invention solves the problem of temperature management during drone flight, and utilizes the heat generated by the fuel cell, lithium battery, and motor to assist in the vaporization of liquid hydrogen, thereby achieving efficient recycling of energy. This design not only reduces energy waste, but also improves the energy utilization efficiency of the entire system and prolongs the flight time of the drone.

[0018] (2) In the thermal management system for a liquid hydrogen fuel cell UAV described in the present invention, the cathode air intake is pre-cooled with liquid hydrogen, and the air intake temperature is effectively reduced. This directly reduces the thermodynamic resistance that the air compressor needs to overcome when compressing the gas, thereby significantly reducing the operating power consumption of the compressor and optimizing the energy consumption performance of the equipment.

[0019] (3) The thermal management system for a liquid hydrogen fuel cell drone described in the present invention can automatically adjust the speed of the liquid hydrogen circulation pump, hydrogen pump, coolant pump and other equipment and the opening of the solenoid valve according to the heat generated by the fuel cell and the flight status of the drone through a built-in controller. This intelligent adjustment method ensures that the system can maintain stable operation under various working conditions, thereby improving the reliability and safety of the system.

[0020] (4) The liquid hydrogen fuel cell UAV thermal management system described in the present invention not only realizes the effective utilization and transfer of heat through the phase change heat storage device and the heat exchanger, but also sets up a liquid cooling thermal management system as a backup heat dissipation mechanism. When the temperature of the fuel cell reaches a higher alarm threshold, the controller will automatically control and open the solenoid valve 2, start the liquid cooling thermal management system, and ensure that the fuel cell remains within the optimal operating temperature range, thereby effectively preventing the occurrence of overheating failures and ensuring the safety of the system.

[0021] (5) The thermal management system of a liquid hydrogen fuel cell drone described in the present invention can intelligently and accurately distribute the power requirements of each component of the drone through the power management module to ensure that the power generated by the fuel cell is efficiently used. When the fuel cell power is insufficient, it automatically switches to the lithium battery as an auxiliary power source to provide stable power for the drone. In addition, the power management module can also monitor the battery status, prevent failures, and reduce maintenance costs. This design improves the flexibility of the system and adapts to a variety of flight missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0023] In the attached picture:

[0024] Figure 1 It is a three-dimensional structural schematic diagram of a liquid hydrogen fuel cell UAV thermal management system according to the present invention;

[0025] Among them: 1-liquid hydrogen storage tank; 2-heat exchanger one; 3-heat exchanger two; 4-gas-liquid separator; 5-liquid hydrogen circulation pump; 6-hydrogen pump; 7-solenoid valve one, 8-air compressor; 9-fuel cell; 10-power management module; 11-lithium battery; 12-motor; 13-phase change heat storage; 14-temperature sensor; 15-coolant storage tank; 16-radiator; 17-coolant pump; 18-solenoid valve two; 19-controller; 20-pressure sensor. DETAILED DESCRIPTION

[0026] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. 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.

[0027] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0028] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0029] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0030] Specific implementation method 1: See Figure 1The present embodiment is described in detail. A liquid hydrogen fuel cell drone thermal management system described in the present embodiment specifically includes a liquid hydrogen storage tank 1, a heat exchanger 23, a hydrogen pump 6, an air compressor 8, a fuel cell 9, a power management module 10, a motor 12, a phase change heat storage device 13 and a cooling system. The liquid hydrogen storage tank 1, the cold end of the heat exchanger 23, the hydrogen pump 6 and the anode of the fuel cell 9 are connected in sequence; the air compressor 8 and the cathode of the fuel cell 9 are connected; the fuel cell 9 is respectively connected to the phase change heat storage device 13 and the liquid cooling thermal management system to dissipate heat for the fuel cell 9; the fuel cell 9, the power management module 10 and the motor 12 are connected in sequence; one end of the phase change heat storage device 13 is connected to the motor 12 to absorb the heat generated by the motor 12, and the other end is connected to the hot end of the heat exchanger 23. The phase change heat storage device 13 is filled with a phase change heat storage material with high specific heat capacity and high melting point.

[0031] A heat exchanger 1 is provided between the liquid hydrogen storage tank 1 and the heat exchanger 2 3. The cold ends of the liquid hydrogen storage tank 1, the heat exchanger 1 2 and the cold end of the heat exchanger 2 3 are connected in sequence; the hot end inlet of the heat exchanger 2 is connected to the atmosphere, and the hot end outlet is connected to the inlet of the air compressor 8. A gas-liquid separator 4 is provided between the cold end of the heat exchanger 2 3 and the hydrogen pump 6. The liquid outlet of the gas-liquid separator 4 is connected to the cold end inlet of the heat exchanger 2 through the liquid hydrogen circulation pump 5; the gas outlet of the gas-liquid separator 4 is connected to the hydrogen pump 6. After the air exchanges heat with the liquid hydrogen through the heat exchanger 1 2, it is compressed by the air compressor 8 and enters the cathode of the fuel cell 9. The cooled air can produce a cooling effect on the inside of the fuel cell 9; the liquid hydrogen vaporized by the initial heat exchange enters the heat exchanger 2 3 and exchanges heat with the phase change heat storage 13. The vaporized hydrogen is sent to the anode of the fuel cell 9 through the hydrogen pump, and the unvaporized liquid hydrogen is circulated back to the heat exchanger 1 2 through the liquid hydrogen circulation pump 5 to continue vaporization.

[0032] The liquid-cooled thermal management system includes a coolant storage tank 15, a radiator 16 and a coolant pump 17. The fuel cell 9 is connected to the coolant storage tank 15 and the phase change heat storage device 13 through a main pipeline; the coolant storage tank 15, the radiator 16 and the coolant pump 17 are connected in sequence, and the outlet of the coolant pump 17 is connected to the fuel cell 9.

[0033] The main pipe is provided with a temperature sensor 14 to monitor the temperature of the coolant so as to obtain the temperature inside the fuel cell 9 .

[0034] A second solenoid valve 18 is provided between the outlet of the coolant pump 17 and the fuel cell 9, and the solenoid valve 18 is used to control the start-up of the liquid cooling thermal management system and the supply speed of the coolant.

[0035] A solenoid valve 7 is provided between the hydrogen pump 6 and the anode of the fuel cell 9, and the supply speed of hydrogen is adjusted by controlling the opening of the solenoid valve 7.

[0036] A pressure sensor 20 is provided between the outlet of the solenoid valve 7 and the anode of the fuel cell 9. The pressure sensor 20 monitors the hydrogen pressure in real time. After receiving the data, the controller 19 adjusts the opening of the solenoid valve 7 according to the hydrogen pressure required by the fuel cell 9 to ensure the stability and safety of the hydrogen supply.

[0037] It also includes a controller 19, which is connected to the solenoid valve 17, the temperature sensor 14, the solenoid valve 218 and the pressure sensor 20 respectively; the controller 19 automatically adjusts the rotation speed of the liquid hydrogen circulation pump 5, the hydrogen pump 6, the coolant pump 17 and the opening of the solenoid valve 17 and the solenoid valve 218 according to the heat generated by the fuel cell 9 and the flight status of the UAV, so as to achieve effective management and regulation of heat; when the temperature in the fuel cell 9 reaches a higher temperature alarm threshold, the controller 19 controls to open the solenoid valve 218 and start the liquid cooling thermal management system to keep the fuel cell 9 within the optimal operating temperature range.

[0038] It also includes a lithium battery 11. The power management module 10 is connected to the fuel cell 9, the lithium battery 11 and the motor 12 respectively. The lithium battery 11 and the motor 12 are both connected to the phase change heat storage 13. The heat generated by the lithium battery 11 and the motor 12 is absorbed by the phase change heat storage 13 for liquid hydrogen vaporization. The lithium battery 11 is used as an auxiliary power source to provide power for the drone when the power generated by the fuel cell 9 is insufficient.

[0039] The specific working process of the thermal management system of a liquid hydrogen fuel cell drone described in the present invention is as follows:

[0040] The liquid hydrogen in the liquid hydrogen storage tank 1 enters the heat exchanger 1 2 and the heat exchanger 2 3 in turn to absorb heat, and then part of the liquid hydrogen is vaporized, and the mixture of hydrogen and liquid hydrogen formed enters the gas-liquid separator 4. The gas-liquid separator 4 separates hydrogen from liquid hydrogen, and the hydrogen is pressurized by the hydrogen pump 6 and enters the anode inlet of the fuel cell 9 through the solenoid valve 1 7. The liquid hydrogen returns to the liquid hydrogen circulation pump 5 and enters the heat exchanger 1 2 and the heat exchanger 2 3 again for circulation heat exchange. The air in the atmosphere enters the air compressor 8 after being precooled by liquid hydrogen in the heat exchanger 1 2, and then the air compressor 8 compresses the air and sends it to the cathode inlet of the fuel cell 9. Hydrogen and oxygen undergo electrochemical reactions in the fuel cell 9 to generate heat, and then the heat generated by the fuel cell 9 is transferred to the phase change heat storage 13. The heat generated by the lithium battery 11 and the heat generated by the motor 12 are transferred to the phase change heat storage 13. The phase change heat storage 13 is filled with a phase change heat storage material with a high specific heat capacity and a high melting point, which can efficiently absorb and store the heat generated by the fuel cell. Subsequently, the heat in the phase change heat storage device 13 is used to assist the vaporization of liquid hydrogen through the heat exchanger 2 3, thereby realizing efficient recycling of energy, improving the energy utilization efficiency of the system and extending the flight time of the drone.

[0041] The controller 19 automatically adjusts the rotational speeds of the liquid hydrogen circulation pump 5, the hydrogen pump 6, and the coolant pump 17, as well as the opening degrees of the solenoid valve 1 7 and the solenoid valve 2 18 according to the heat generation of the fuel cell 9 and the flight state of the drone, ensuring stable operation of the system under various working conditions. Effective utilization and transfer of heat are achieved through the phase change heat storage device 13 and the heat exchanger, and a liquid cooling thermal management system is also provided as a backup heat dissipation mechanism. When the temperature inside the fuel cell 9 reaches the high-temperature alarm threshold, the controller 19 will control the opening of the solenoid valve 2 18 to start the liquid cooling thermal management system. The coolant in the coolant storage tank 15 enters the radiator 16 through the outlet. After heat dissipation, the temperature of the coolant decreases, and then after being pressurized by the coolant pump 17, it circulates back into the system for cooling, ensuring that the fuel cell 9 is maintained within the optimal operating temperature range. This effectively prevents the occurrence of overheating faults and ensures the safety of the system.

[0042] The power management module 10 can intelligently and precisely distribute the electrical energy according to the electrical energy requirements of each component of the drone, ensuring the efficient utilization of the electrical energy generated by the fuel cell 9. When the electrical energy of the fuel cell 9 is insufficient, it automatically switches to the lithium battery 11 as an auxiliary power source to provide stable electrical energy for the drone. The pressure sensor 20 continuously monitors the hydrogen pressure at the anode inlet and sends the data to the controller 19. The controller 19 adjusts the opening degree of the solenoid valve 1 7 according to the hydrogen pressure required by the fuel cell 9 to ensure the stability and safety of hydrogen supply.

[0043] Summarizing the above implementation cases, a liquid hydrogen fuel cell drone thermal management system described in the present invention solves the problem of temperature management during the flight of the drone. It utilizes the heat generation of the fuel cell 9, the heat generation of the lithium battery 11, and the heat generation of the motor 12 to assist in the vaporization of liquid hydrogen, achieving efficient cyclic utilization of energy. This design not only reduces energy waste but also improves the energy utilization efficiency of the entire system and extends the endurance time of the drone.

[0044] In a liquid hydrogen fuel cell drone thermal management system described in the present invention, the cathode intake air undergoes liquid hydrogen precooling treatment, effectively reducing the intake air temperature. This directly reduces the thermodynamic resistance that the air compressor 8 needs to overcome when compressing the gas, thereby significantly reducing the operating power consumption of the compressor and optimizing the energy consumption performance of the equipment.

[0045] In a liquid hydrogen fuel cell drone thermal management system described in the present invention, through the built-in controller 19, the present invention can automatically adjust the rotational speeds of devices such as the liquid hydrogen circulation pump 5, the hydrogen pump 6, and the coolant pump 17, as well as the opening degrees of the solenoid valves according to the heat generation of the fuel cell 9 and the flight state of the drone. This intelligent adjustment method ensures stable operation of the system under various working conditions and improves the reliability and safety of the system.

[0046] The liquid hydrogen fuel cell UAV thermal management system described in the present invention not only realizes the effective utilization and transfer of heat through the phase change heat storage device 13 and the heat exchanger, but also sets up a liquid cooling thermal management system as a backup heat dissipation mechanism. When the temperature of the fuel cell 9 reaches a higher alarm threshold, the controller 19 will automatically control and open the solenoid valve 2 18, start the liquid cooling thermal management system, and ensure that the fuel cell 9 remains within the optimal operating temperature range, thereby effectively preventing the occurrence of overheating failures and ensuring the safety of the system.

[0047] The thermal management system of a liquid hydrogen fuel cell drone described in the present invention can intelligently and accurately distribute the power requirements of each component of the drone through the power management module 10 to ensure that the power generated by the fuel cell 9 is efficiently used. When the power of the fuel cell 9 is insufficient, it automatically switches to the lithium battery 11 as an auxiliary power source to provide stable power for the drone. In addition, the power management module 10 can also monitor the battery status, prevent failures, and reduce maintenance costs. This design improves the flexibility of the system and adapts to a variety of flight missions.

[0048] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the invention. It can also be a reasonable combination of the features recorded in the above implementation methods. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A liquid hydrogen fuel cell UAV thermal management system, characterized by: The invention comprises a liquid hydrogen storage tank (1), a heat exchanger 2 (3), a hydrogen pump (6), an air compressor (8), a fuel cell (9), a power management module (10), a motor (12), a phase change heat storage device (13) and a cooling system. The liquid hydrogen storage tank (1), the cold end of the heat exchanger 2 (3), the hydrogen pump (6) and the anode of the fuel cell (9) are connected in sequence; the air compressor (8) and the cathode of the fuel cell (9) are connected; the fuel cell (9) is respectively connected to the phase change heat storage device (13) and the liquid cooling thermal management system to dissipate heat for the fuel cell (9); the fuel cell (9), the power management module (10) and the motor (12) are connected in sequence; one end of the phase change heat storage device (13) is connected to the motor (12) to absorb the heat generated by the motor (12) during operation, and the other end is connected to the hot end of the heat exchanger 2 (3).

2. The liquid hydrogen fuel cell UAV thermal management system according to claim 1 is characterized by: A heat exchanger 1 (2) is arranged between the liquid hydrogen storage tank (1) and the heat exchanger 2 (3); the liquid hydrogen storage tank (1), the cold end of the heat exchanger 1 (2) and the cold end of the heat exchanger 2 (3) are connected in sequence; the hot end inlet of the heat exchanger 1 (2) is connected to the atmosphere, and the hot end outlet is connected to the inlet of the air compressor (8).

3. The liquid hydrogen fuel cell UAV thermal management system according to claim 2 is characterized by: A gas-liquid separator (4) is provided between the cold end of the second heat exchanger (3) and the hydrogen pump (6); the liquid outlet of the gas-liquid separator (4) is connected to the cold end inlet of the first heat exchanger (2) through the liquid hydrogen circulation pump (5); and the gas outlet of the gas-liquid separator (4) is connected to the hydrogen pump (6).

4. The liquid hydrogen fuel cell UAV thermal management system according to claim 1, characterized in that: The liquid cooling thermal management system comprises a coolant storage tank (15), a radiator (16) and a coolant pump (17); the fuel cell (9) is respectively connected to the coolant storage tank (15) and the phase change heat storage device (13) through a main pipeline; the coolant storage tank (15), the radiator (16) and the coolant pump (17) are connected in sequence, and the outlet of the coolant pump (17) is connected to the fuel cell (9).

5. The liquid hydrogen fuel cell UAV thermal management system according to claim 4 is characterized in that: A temperature sensor (14) is arranged on the main pipe.

6. The liquid hydrogen fuel cell UAV thermal management system according to claim 5, characterized in that: A second solenoid valve (18) is provided between the outlet of the coolant pump (17) and the fuel cell (9).

7. The liquid hydrogen fuel cell UAV thermal management system according to claim 6, characterized in that: A solenoid valve (7) is provided between the hydrogen pump (6) and the anode of the fuel cell (9).

8. The liquid hydrogen fuel cell UAV thermal management system according to claim 7, characterized in that: A pressure sensor (20) is provided between the outlet of the solenoid valve 1 (7) and the anode of the battery (9).

9. The liquid hydrogen fuel cell UAV thermal management system according to claim 8, characterized in that: The invention also comprises a controller (19), which is respectively connected to the first solenoid valve (7), the temperature sensor (14), the second solenoid valve (18) and the pressure sensor (20).

10. The liquid hydrogen fuel cell UAV thermal management system according to claim 1, characterized in that: It also includes a lithium battery (11), which is connected to the power management module (10) and the phase change heat storage device (13) respectively.

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