An aerodynamic-based unmanned aerial vehicle cooling system

Abstract

The application provides an unmanned aerial vehicle (UAV) heat dissipation system based on aerodynamics, and relates to the technical field of UAV heat dissipation.The system comprises a first battery air-cooled radiator and a second battery air-cooled radiator, which are arranged on the left side and the right side of the UAV respectively, and the first battery air-cooled radiator and the second battery air-cooled radiator are arranged on a first cooling loop in sequence and used for dissipating heat of fuel cells of the UAV; and an electric control system air-cooled radiator is arranged on the same side of the UAV and close to the second battery air-cooled radiator, and the electric control system air-cooled radiator is used for dissipating heat of an electric control system of the UAV; the problem that a heat management system in the prior art only considers the heat dissipation of fuel cells of the UAV and does not consider the influence of heat dissipation on aerodynamics of the UAV during the heat dissipation process is solved.

Description

Technical Field

[0001] This invention belongs to the field of drone heat dissipation technology, and more specifically, relates to an aerodynamic drone heat dissipation system. Background Technology

[0002] The development of new energy drones has entered a golden age. Currently, the biggest bottleneck limiting new energy drones is their flight time. Popular lithium-ion battery systems generally only allow for less than one hour of flight time within the weight limits of drones. Extending the flight time of new energy drones is a challenge that is being addressed both domestically and internationally.

[0003] Therefore, hydrogen fuel cell power is increasingly becoming a trend in the development of new energy drones. Compared to lithium batteries, hydrogen fuel cells have a longer lifespan, and hydrogen fuel has the advantages of abundant supply, high energy density, low price, and no pollution byproducts. Fuel cells can meet the long-term power needs of drones and reduce the weight of the power supply system. At the same time, fuel cells have some challenges in use. The system has strict requirements for operating temperature. Excessive or insufficient stack temperature will reduce the efficiency and lifespan of the fuel cell, and in severe cases, it may even fail. Therefore, the design of the heat dissipation system is challenging.

[0004] Current research on thermal management of traditional fuel cell systems mainly focuses on ground-level conditions at normal temperature and pressure, with limited research on the thinner air conditions at medium and high altitudes, and less research combining aerodynamics. Existing thermal management systems, including components such as water tanks, cooling water circulation pumps, and radiators, can achieve heat dissipation and cooling of the fuel cell stack. However, these systems only consider the heat dissipation of the fuel cell in UAVs, and do not take into account the aerodynamic impact of heat dissipation on the UAV during the cooling process. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies by providing an aerodynamic-based drone cooling system. This system solves the problem that existing thermal management systems only consider the cooling of the drone's fuel cell and do not take into account the aerodynamic impact of the cooling process on the drone.

[0006] To achieve the above objectives, the present invention provides an aerodynamic-based unmanned aerial vehicle (UAV) heat dissipation system, the system comprising:

[0007] The first battery air-cooled heat sink and the second battery air-cooled heat sink are respectively located on the left and right sides of the UAV. The first battery air-cooled heat sink and the second battery air-cooled heat sink are sequentially arranged on the first cooling circuit and are used to dissipate heat from the UAV's fuel cell.

[0008] The electronic control system air-cooled heat sink is located close to and on the same side of the UAV as the second battery air-cooled heat sink, and the electronic control system air-cooled heat sink is used to dissipate heat from the UAV's electronic control system.

[0009] Optionally, the heat dissipation of the first battery air-cooled radiator is equal to the sum of the heat dissipation of the second battery air-cooled radiator and the air-cooled radiator of the electronic control system.

[0010] Optionally, a first water pump is provided upstream of the first battery air-cooled radiator on the first cooling circuit, and a bypass pipe is connected to the first cooling circuit between the output end of the first water pump and the first battery air-cooled radiator. The bypass pipe is connected to the first cooling circuit downstream of the second battery air-cooled radiator, and a bypass control valve is provided on the bypass pipe.

[0011] Optionally, the first cooling circuit is connected to the fuel cell via a first branch and to the intercooler of the UAV via a second branch, and the first branch and the second branch are connected to the input end of the first water pump.

[0012] Optionally, a water temperature sensor is provided on the first branch downstream of the fuel cell.

[0013] Optionally, the electronic control system includes a compressor, a voltage converter, and a compressor controller.

[0014] Optionally, the air-cooled radiator of the electronic control system is installed on the second cooling circuit. One end of the second cooling circuit is connected to the outlet of the air-cooled radiator of the electronic control system, passes through the compressor, the voltage converter, the compressor controller and the second water pump in sequence, and is connected to the inlet of the air-cooled radiator of the electronic control system.

[0015] Optionally, it also includes a gas pipeline, one end of which is connected to the compressor, passes sequentially through the intercooler and humidifier of the UAV, and is connected to the fuel cell.

[0016] Optionally, a first exhaust valve is provided on the first cooling circuit between the first battery air-cooled radiator and the second battery air-cooled radiator, and a second exhaust valve is provided on the second cooling circuit between the electronic control system air-cooled radiator and the compressor.

[0017] Optionally, it also includes a first expansion tank and a second expansion tank, the first expansion tank and the second expansion tank being connected to the first cooling circuit and the second cooling circuit, respectively.

[0018] This invention provides an aerodynamic-based unmanned aerial vehicle (UAV) cooling system. Its advantages lie in the following: the system divides the battery air-cooled radiator used for cooling the fuel cell into a first battery air-cooled radiator and a second battery air-cooled radiator, which are respectively located on the left and right sides of the UAV. An electronic control system air-cooled radiator is also provided, positioned close to and on the same side of the UAV as the second battery air-cooled radiator, ensuring that the heat dissipation on the left and right sides of the UAV is as equal as possible. This not only provides comprehensive cooling for the UAV's fuel cell and electronic control system but also, based on aerodynamics, considers the impact of heat dissipation on the UAV's aerodynamics, balancing the heat dissipation on the left and right sides of the UAV, thereby balancing the air resistance on the left and right sides of the aircraft.

[0019] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0020] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0021] Figure 1 A schematic diagram of an aerodynamic-based unmanned aerial vehicle (UAV) cooling system according to an embodiment of the present invention is shown.

[0022] Explanation of reference numerals in the attached figures:

[0023] 1. First battery air-cooled radiator; 2. Second battery air-cooled radiator; 3. Electronic control system air-cooled radiator; 4. First cooling circuit; 5. First water pump; 6. Bypass pipeline; 7. Bypass control valve; 8. First branch; 9. Second branch; 10. Fuel cell; 11. Intercooler; 12. Water temperature sensor; 13. Compressor; 14. Voltage converter; 15. Compressor controller; 16. Second cooling circuit; 17. Second water pump; 18. Gas pipeline; 19. First exhaust valve; 20. Second exhaust valve; 21. First expansion tank; 22. Second expansion tank; 23. First injection valve; 24. Second injection valve; 25. Humidifier. Detailed Implementation

[0024] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0025] like Figure 1As shown, the present invention provides an aerodynamic-based unmanned aerial vehicle (UAV) heat dissipation system, the system comprising:

[0026] The first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 are respectively located on the left and right sides of the UAV. The first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 are sequentially arranged on the first cooling circuit 4 and used to dissipate heat from the UAV's fuel cell 10.

[0027] The electronic control system air-cooled radiator 3 is located close to and on the same side of the drone as the second battery air-cooled radiator 2. The electronic control system air-cooled radiator 3 is used to dissipate heat from the drone's electronic control system.

[0028] Specifically, to address the problem that existing thermal management systems only consider heat dissipation for the UAV's fuel cell 10 and do not consider the aerodynamic impact of heat dissipation on the UAV, the aerodynamic-based UAV heat dissipation system provided by this invention divides the battery air-cooled radiator used for heat dissipation of the fuel cell 10 into a first battery air-cooled radiator 1 and a second battery air-cooled radiator 2, which are respectively located on the left and right sides of the UAV. An electronic control system air-cooled radiator 3 is also provided, positioned close to and on the same side of the UAV as close as possible to the second battery air-cooled radiator 2, so that the heat dissipation on the left and right sides of the UAV is as equal as possible. This not only provides comprehensive heat dissipation for the UAV's fuel cell 10 and electronic control system, but also, based on aerodynamics, considers the aerodynamic impact of heat dissipation on the UAV, balancing the heat dissipation on the left and right sides of the UAV, thereby balancing the air resistance on the left and right sides of the aircraft.

[0029] Optionally, the heat dissipation of the first battery air-cooled radiator 1 is equal to the sum of the heat dissipation of the second battery air-cooled radiator 2 and the air-cooled radiator 3 of the electronic control system.

[0030] Specifically, the heat dissipation of the three components can be controlled by adjusting the flow rate of the coolant flowing through the first battery air-cooled radiator 1, the second battery air-cooled radiator 2, and the electronic control system air-cooled radiator 3. This ensures that the heat dissipation of the first battery air-cooled radiator 1 is equal to the sum of the heat dissipation of the second battery air-cooled radiator 2 and the electronic control system air-cooled radiator 3, thus achieving a balance in heat dissipation between the left and right sides of the drone.

[0031] In this embodiment, the left and right sides of the drone refer to the left wing and right wing of the drone, respectively.

[0032] In one example, based on the heat dissipation calculations of various components of the drone, the heat dissipation of the battery air-cooled radiator is significantly higher than that of the electronic control system air-cooled radiator 3 due to the large heat generation of the fuel cell 10. In some selected operating conditions, the difference is even more than five times. Therefore, the temperature of the ambient air flowing through the battery air-cooled radiator is significantly higher. According to the physical properties of air, the higher the temperature, the greater the air viscosity. The increase in air viscosity will increase air resistance, thus causing a large difference in flight resistance between the left and right sides of the drone. Therefore, this invention sets up a first battery air-cooled radiator 1 and a second battery air-cooled radiator 2. The second battery air-cooled radiator 2 and the electronic control system air-cooled radiator 3 are set close to each other on the same side of the drone, forming a combined radiator. This ensures that the heat load of the first battery air-cooled radiator 1 and the combined radiator are basically the same under various conventional operating conditions. Furthermore, they are placed on the left and right sides of the drone respectively, thereby achieving the effect of balancing the air resistance on the left and right sides of the flight.

[0033] Optionally, a first water pump 5 is provided upstream of the first battery air-cooled radiator 1 on the first cooling circuit 4. A bypass pipe 6 is connected to the first cooling circuit 4 between the output end of the first water pump 5 and the first battery air-cooled radiator 1. The bypass pipe 6 is connected to the first cooling circuit 4 downstream of the second battery air-cooled radiator 2. A bypass control valve 7 is provided on the bypass pipe 6.

[0034] Specifically, the first water pump 5 provides power for the circulation of coolant in the first cooling circuit 4. The bypass pipe 6 and bypass control valve 7 are set to regulate the flow rate of coolant in the first cooling circuit 4 and the bypass pipe 6, thereby controlling the heat dissipation of the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2.

[0035] Optionally, the first cooling circuit 4 is connected to the fuel cell 10 via the first branch 8 and to the intercooler 11 of the UAV via the second branch 9. The first branch 8 and the second branch 9 are connected to the input end of the first water pump 5.

[0036] Specifically, when the fuel cell 10 starts to supply power, the speed of the first water pump 5 and the opening of the bypass control valve 7 in the first cooling circuit 4 can be adjusted. Part of the coolant flows through the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2, while the rest of the coolant flows directly through the bypass pipe 6. The two coolants merge after the second battery air-cooled radiator 2. After merging, part of the coolant flows into the fuel cell 10 through the first branch 8, and the rest flows into the intercooler 11 through the second branch 9. The two coolants merge again before the first water pump 5 and flow into the first water pump 5.

[0037] Optionally, a water temperature sensor 12 is provided downstream of the fuel cell 10 on the first branch 8.

[0038] Specifically, the water temperature sensor 12 is used to monitor the temperature of the coolant flowing through the fuel cell 10, so as to monitor its cooling effect on the fuel cell 10.

[0039] Optionally, the electronic control system includes a compressor 13, a voltage converter 14, and a compressor controller 15.

[0040] Specifically, the air-cooled heat sink 3 of the electronic control system is used to dissipate heat from electronic control components such as compressor 13, voltage converter 14, and compressor controller 15, and can also be connected to other electronic control components as needed.

[0041] Optionally, the air-cooled radiator 3 of the electronic control system is installed on the second cooling circuit 16. One end of the second cooling circuit 16 is connected to the outlet of the air-cooled radiator 3 of the electronic control system, passes through the compressor 13, voltage converter 14, compressor controller 15 and second water pump 17 in sequence, and is connected to the inlet of the air-cooled radiator 3 of the electronic control system.

[0042] Specifically, in the second cooling circuit 16, the coolant is pumped out from the second water pump 17 and flows through the second battery air-cooled radiator 2, and then flows through the compressor 13, voltage converter 14 and compressor controller 15 in sequence. After cooling the above three electronic control components, it flows back to the second water pump 17 to form a circuit.

[0043] Optionally, it also includes a gas pipeline 18, one end of which is connected to the compressor 13, passes through the intercooler 11 and humidifier 25 of the UAV in sequence, and is connected to the fuel cell 10.

[0044] Specifically, ambient air is compressed by compressor 13 into high-temperature and high-pressure air, and then becomes medium-temperature and high-pressure humid air after passing through intercooler 11 and humidifier 25, before entering fuel cell 10 for reaction.

[0045] Optionally, a first exhaust valve 19 is provided on the first cooling circuit 4 between the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2, and a second exhaust valve 20 is provided on the second cooling circuit 16 between the electronic control system air-cooled radiator 3 and the compressor 13.

[0046] Specifically, the first exhaust valve 19 and the second exhaust valve 20 are used for exhausting the first cooling circuit 4 and the second cooling circuit 16, respectively, to ensure the cooling efficiency of the coolant.

[0047] Optionally, it also includes a first expansion tank 21 and a second expansion tank 22, which are respectively connected to the first cooling circuit 4 and the second cooling circuit 16.

[0048] Specifically, the first expansion tank 21 and the second expansion tank 22 provide coolant to the first cooling circuit 4 and the second cooling circuit 16, respectively. The connecting pipes of the first expansion tank 21 and the second expansion tank 22 are respectively equipped with a first injection valve 23 and a second injection valve 24. Both the first injection valve 23 and the second injection valve 24 can be used for injection and drainage control.

[0049] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. An aerodynamic based unmanned aerial vehicle cooling system, comprising: The system comprises: A first battery air-cooled radiator and a second battery air-cooled radiator are arranged on the left and right sides of the unmanned aerial vehicle respectively, and are arranged on the first cooling circuit in sequence and used for radiating the fuel cell of the unmanned aerial vehicle; An electric control system air-cooled radiator is arranged on the same side of the unmanned aerial vehicle close to the second battery air-cooled radiator, and is used for radiating the electric control system of the unmanned aerial vehicle; A first water pump is arranged on the first cooling circuit upstream of the first battery air-cooled radiator, and a bypass pipeline is connected to the first cooling circuit between the output end of the first water pump and the first battery air-cooled radiator, the bypass pipeline is connected to the first cooling circuit downstream of the second battery air-cooled radiator, and a bypass control valve is arranged on the bypass pipeline.

2. The aerodynamic-based drone heat dissipation system of claim 1, wherein, The heat dissipation amount of the first battery air-cooled radiator is equal to the sum of the heat dissipation amounts of the second battery air-cooled radiator and the electric control system air-cooled radiator.

3. The aerodynamic-based drone heat dissipation system of claim 1, wherein, The first cooling circuit is connected to the fuel cell through a first branch and connected to the intercooler of the unmanned aerial vehicle through a second branch, and the first branch and the second branch are connected to the input end of the first water pump.

4. The aerodynamic-based drone heat dissipation system of claim 3, wherein, A water temperature sensor is arranged on the first branch downstream of the fuel cell.

5. The aerodynamic-based drone heat dissipation system of claim 1, wherein, The electric control system comprises a compressor, a voltage converter and a compressor controller.

6. The aerodynamic-based drone heat dissipation system of claim 5, wherein, The electric control system air-cooled radiator is arranged on the second cooling circuit, one end of the second cooling circuit is connected to the outlet of the electric control system air-cooled radiator, sequentially passes through the compressor, the voltage converter, the compressor controller and a second water pump, and is connected to the inlet of the electric control system air-cooled radiator.

7. The aerodynamic-based drone heat dissipation system of claim 6, wherein, A gas pipeline is further included, one end of the gas pipeline is connected to the compressor, sequentially passes through the intercooler and the humidifier of the unmanned aerial vehicle, and is connected to the fuel cell.

8. The aerodynamic-based drone heat dissipation system of claim 6, wherein, A first exhaust valve is arranged on the first cooling circuit between the first battery air-cooled radiator and the second battery air-cooled radiator, and a second exhaust valve is arranged on the second cooling circuit between the electric control system air-cooled radiator and the compressor.

9. The aerodynamic-based drone heat dissipation system of claim 6, wherein, First and second expansion water tanks are further included, and the first and second expansion water tanks are connected to the first and second cooling circuits respectively.

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