CN219215414U - Unmanned aerial vehicle cooling system based on aerodynamics - Google Patents
Unmanned aerial vehicle cooling system based on aerodynamics Download PDFInfo
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- CN219215414U CN219215414U CN202223601950.9U CN202223601950U CN219215414U CN 219215414 U CN219215414 U CN 219215414U CN 202223601950 U CN202223601950 U CN 202223601950U CN 219215414 U CN219215414 U CN 219215414U
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Abstract
The utility model provides an unmanned aerial vehicle heat dissipation system based on aerodynamics, which relates to the technical field of unmanned aerial vehicle heat dissipation, and comprises the following components: the first battery air-cooled radiator and the second battery air-cooled radiator are respectively arranged on the left side and the right side of the unmanned aerial vehicle, are sequentially arranged on the first cooling loop and are used for radiating heat of a fuel cell of the unmanned aerial vehicle; the electronic control system air-cooled radiator is close to the second battery air-cooled radiator and arranged on the same side of the unmanned aerial vehicle, and is used for radiating the electronic control system of the unmanned aerial vehicle; the heat management system solves the problems that only the heat dissipation of the fuel cell of the unmanned aerial vehicle is considered in the heat management system in the prior art, and the aerodynamic influence of the heat dissipation on the unmanned aerial vehicle is not considered in the heat dissipation process.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle heat dissipation, and particularly relates to an unmanned aerial vehicle heat dissipation system based on aerodynamics.
Background
In order to respond to energy conservation and emission reduction call, the aim of carbon neutralization is achieved early, and the development of the new energy unmanned aerial vehicle enters the golden period. The biggest limitation bottleneck of the new energy unmanned aerial vehicle at present is the duration, and the current popular lithium ion battery system can only last for 1 hour in the weight range allowed by the unmanned aerial vehicle, and how to prolong the duration of the new energy unmanned aerial vehicle is a breakthrough problem at home and abroad.
Therefore, hydrogen fuel cell power is increasingly becoming a trend for new energy unmanned aerial vehicles. Compared with a lithium battery, the hydrogen fuel battery has longer service life, and the hydrogen fuel has the characteristics of sufficient source, high energy density, low price, no pollution of products and the like, and the fuel battery can supply power for unmanned aerial vehicles to meet the long-time power requirement, thereby reducing the weight of a power supply system. Meanwhile, the fuel cell has some using difficulties, the system has strict requirements on the working temperature, the working efficiency and the service life of the fuel cell are reduced due to the too high or too low temperature of a galvanic pile, and even the fuel cell is invalid when serious, so that the design of a heat dissipation system is challenged.
At present, the traditional fuel cell system heat management research is mainly focused on the research of the middle-high altitude working environment with thinner air under the condition of normal temperature and normal pressure on the ground, and the research on the aspect of combining aerodynamics is less. The heat management system in the prior art comprises parts such as a water tank, a cooling water circulating pump, a radiator and the like, and can realize heat dissipation and cooling of the electric pile, but only heat dissipation of a fuel cell of the unmanned aerial vehicle is considered, and aerodynamic influence of heat dissipation on the unmanned aerial vehicle is not considered in the heat dissipation process.
Disclosure of Invention
The utility model aims to overcome the defects in the prior art, provides an unmanned aerial vehicle heat dissipation system based on aerodynamics, and solves the problems that a heat management system in the prior art only considers heat dissipation of a fuel cell of an unmanned aerial vehicle and the aerodynamic influence of heat dissipation on the unmanned aerial vehicle is not considered in the heat dissipation process.
In order to achieve the above object, the present utility model provides an aerodynamic unmanned aerial vehicle heat dissipation system, comprising:
the first battery air-cooled radiator and the second battery air-cooled radiator are respectively arranged on the left side and the right side of the unmanned aerial vehicle, and are sequentially arranged on the first cooling loop and used for radiating the fuel cell of the unmanned aerial vehicle;
the electronic control system air-cooled radiator is close to the second battery air-cooled radiator and arranged on the same side of the unmanned aerial vehicle, and the electronic control system air-cooled radiator is used for radiating heat of the electronic control system of the unmanned aerial vehicle.
Optionally, the heat dissipation capacity of the first battery air-cooled radiator is equal to the sum of the heat dissipation capacities of the second battery air-cooled radiator and the electric control system air-cooled radiator.
Optionally, a first water pump is arranged on the first cooling loop at the upstream of the first battery air-cooled radiator, a bypass pipeline is connected to the first cooling loop 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 loop at the downstream of the second battery air-cooled radiator, and a bypass control valve is arranged on the bypass pipeline.
Optionally, the first cooling circuit is connected with the fuel cell through a first branch and is connected with an intercooler of the unmanned aerial vehicle through a second branch, and the first branch and the second branch are connected with an input end of the first water pump.
Optionally, a water temperature sensor is disposed on the first branch downstream of the fuel cell.
Optionally, the electric control system comprises a compressor, a voltage converter and a compressor controller.
Optionally, the air cooling radiator of the electric control system is arranged on a second cooling loop, one end of the second cooling loop is connected with an outlet of the air cooling radiator of the electric control system, sequentially passes through the air compressor, the voltage converter, the air compressor controller and the second water pump, and is connected with an inlet of the air cooling radiator of the electric control system.
Optionally, the system further comprises a gas pipeline, wherein one end of the gas pipeline is connected with the gas compressor, sequentially passes through an intercooler and a humidifier of the unmanned aerial vehicle, and is connected with the fuel cell.
Optionally, a first exhaust valve is arranged between the first battery air-cooled radiator and the second battery air-cooled radiator on the first cooling loop, and a second exhaust valve is arranged between the electric control system air-cooled radiator and the air compressor on the second cooling loop.
Optionally, the cooling system further comprises a first expansion water tank and a second expansion water tank, wherein the first expansion water tank and the second expansion water tank are respectively connected with the first cooling loop and the second cooling loop.
The utility model provides an unmanned aerial vehicle heat dissipation system based on aerodynamics, which has the beneficial effects that: the system divides a battery air-cooled radiator for radiating the fuel battery into a first battery air-cooled radiator and a second battery air-cooled radiator, wherein the first battery air-cooled radiator and the second battery air-cooled radiator are respectively arranged on the left side and the right side of the unmanned aerial vehicle, an electric control system air-cooled radiator is arranged on the same side of the unmanned aerial vehicle, the electric control system air-cooled radiator and the second battery air-cooled radiator are close to each other, so that the heat dissipation capacity on the left side and the right side of the unmanned aerial vehicle is equal to each other as much as possible, the comprehensive heat dissipation of the fuel battery and the electric control system of the unmanned aerial vehicle is realized, the aerodynamic influence of the heat dissipation on the unmanned aerial vehicle is considered, the heat dissipation capacity on the left side and the right side of the unmanned aerial vehicle is balanced, and the air resistance on the left side and the right side of the aircraft is balanced.
Additional features and advantages of the utility model will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the utility model will be apparent from the following more particular descriptions of exemplary embodiments of the utility model as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the utility model.
Fig. 1 shows a schematic diagram of an aerodynamic based unmanned air vehicle heat dissipation system according to an embodiment of the utility model.
Reference numerals illustrate:
1. a first battery air-cooled radiator; 2. a second battery air-cooled radiator; 3. an air-cooled radiator of the electric control system; 4. a first cooling circuit; 5. a first water pump; 6. a bypass line; 7. a bypass control valve; 8. a first branch; 9. a second branch; 10. a fuel cell; 11. an intercooler; 12. a water temperature sensor; 13. a compressor; 14. a voltage converter; 15. a compressor controller; 16. a second cooling circuit; 17. a second water pump; 18. a gas line; 19. a first exhaust valve; 20. a second exhaust valve; 21. a first expansion tank; 22. a second expansion tank; 23. a first liquid injection valve; 24. a second liquid injection valve; 25. a humidifier.
Detailed Description
Preferred embodiments of the present utility model will be described in more detail below. While the preferred embodiments of the present utility model are described below, it should be understood that the present utility model may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the utility model to those skilled in the art.
As shown in fig. 1, the present utility model provides an aerodynamic unmanned aerial vehicle heat dissipation system, comprising:
the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 are respectively arranged on the left side and the right side of the unmanned aerial vehicle, and the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 are sequentially arranged on the first cooling loop 4 and are used for radiating the fuel cell 10 of the unmanned aerial vehicle;
the electric control system air-cooled radiator 3 is close to the second battery air-cooled radiator 2 and arranged on the same side of the unmanned aerial vehicle, and the electric control system air-cooled radiator 3 is used for radiating heat of the electric control system of the unmanned aerial vehicle.
Specifically, in order to solve the problem that the heat management system in the prior art only considers the heat dissipation of the fuel cell 10 of the unmanned aerial vehicle, and does not consider the aerodynamic influence of the heat dissipation on the unmanned aerial vehicle in the heat dissipation process; the unmanned aerial vehicle cooling system based on aerodynamics provided by the utility model divides a battery air-cooled radiator for cooling a fuel battery 10 into a first battery air-cooled radiator 1 and a second battery air-cooled radiator 2 which are respectively arranged on the left side and the right side of the unmanned aerial vehicle, and an electric control system air-cooled radiator 3 is arranged, the electric control system air-cooled radiator 3 and the second battery air-cooled radiator 2 are close to each other and are arranged on the same side of the unmanned aerial vehicle, so that the cooling capacity on the left side and the right side of the unmanned aerial vehicle is equal as much as possible, the unmanned aerial vehicle cooling system not only has the overall cooling of the fuel battery 10 and the electric control system of the unmanned aerial vehicle, but also balances the cooling capacity on the left side and the right side of the unmanned aerial vehicle based on aerodynamics, and further balances the air resistance on the left side and the right side of an aircraft in consideration of the aerodynamic effect of the cooling on the unmanned aerial vehicle.
Optionally, the heat dissipation capacity of the first battery air-cooled radiator 1 is equal to the sum of the heat dissipation capacities of the second battery air-cooled radiator 2 and the electric control system air-cooled radiator 3.
Specifically, the heat dissipation capacity of the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 and the electric control system air-cooled radiator 3 can be controlled by controlling the flow of the cooling liquid flowing through the three, so that the heat dissipation capacity of the first battery air-cooled radiator 1 is equal to the sum of the heat dissipation capacities of the second battery air-cooled radiator 2 and the electric control system air-cooled radiator 3, and the effect of balancing the heat dissipation capacities of the left side and the right side of the unmanned aerial vehicle is achieved.
In this embodiment, the left and right sides of the unmanned aerial vehicle refer to the left and right wings of the unmanned aerial vehicle, respectively.
In one example, according to the calculation of the heat dissipation capacity of each component of the unmanned aerial vehicle, the heat dissipation capacity of the air-cooled battery radiator is obviously higher than that of the air-cooled battery radiator 3 of the electronic control system due to the large heat generation capacity of the fuel cell 10, and even more than five times of the heat dissipation capacity of the air-cooled battery radiator under the partial selection working condition, so that the temperature of the outside ambient air after flowing through the air-cooled battery radiator is obviously higher; according to the physical characteristics of the air, the higher the temperature is, the higher the air viscosity is, and the air resistance is increased by the increase of the air viscosity, so that the problem that the flight resistances on the left side and the right side of the unmanned aerial vehicle are different greatly is caused. Therefore, the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 are arranged, the second battery air-cooled radiator 2 and the electric control system air-cooled radiator 3 are arranged close to each other on the same side of the unmanned aerial vehicle, and the heat loads of the first battery air-cooled radiator 1 and the combined radiator are basically the same under various conventional working conditions by the travel combined radiator, and the first battery air-cooled radiator and the combined radiator are respectively arranged on the left side and the right side of the unmanned aerial vehicle, so that the effect of balancing air resistance on the left side and the right side of a flight is achieved.
Optionally, a first water pump 5 is arranged on the first cooling loop 4 at the upstream of the first battery air-cooled radiator 1, a bypass pipeline 6 is connected on the first cooling loop 4 between the output end of the first water pump 5 and the first battery air-cooled radiator 1, the bypass pipeline 6 is connected with the first cooling loop 4 at the downstream of the second battery air-cooled radiator 2, and a bypass control valve 7 is arranged on the bypass pipeline 6.
Specifically, the first water pump 5 provides power for circulation of the cooling liquid in the first cooling loop 4, and the bypass pipeline 6 and the bypass control valve 7 are used for regulating and controlling the flow of the cooling liquid in the first cooling loop 4 and the bypass pipeline 6, so that the heat dissipation capacity of the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2 can be controlled.
Alternatively, the first cooling circuit 4 is connected to the fuel cell 10 via a first branch 8 and to the intercooler 11 of the unmanned aerial vehicle via a second branch 9, the first branch 8 and the second branch 9 being connected to the input of the first water pump 5.
Specifically, when the fuel cell 10 starts to supply power, the rotation speed of the first water pump 5 and the opening of the bypass control valve 7 in the first cooling loop 4 can be adjusted, part of the cooling liquid flows through the first battery air-cooled radiator 1 and the second battery air-cooled radiator 2, the rest of the cooling liquid directly flows through the bypass pipeline 6, and the two paths of cooling liquid are converged after the second battery air-cooled radiator 2; the merged part of the cooling liquid flows into the fuel cell 10 through the first branch 8, the rest flows into the intercooler 11 through the second branch 9, and the two cooling liquids are merged again before the first water pump 5 and flow into the first water pump 5.
Optionally, a water temperature sensor 12 is provided on the first branch 8 downstream of the fuel cell 10.
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 the cooling effect of the coolant on the fuel cell 10.
Optionally, the electrical control system comprises a compressor 13, a voltage converter 14, a compressor controller 15.
Specifically, the air-cooled radiator 3 of the electric control system is used for radiating electric control components such as the air compressor 13, the voltage converter 14, the air compressor controller 15 and the like, and can be connected with other electric control components as required.
Optionally, the electric control system air-cooled radiator 3 is disposed on the second cooling circuit 16, one end of the second cooling circuit 16 is connected to an outlet of the electric control system air-cooled radiator 3, sequentially passes through the compressor 13, the voltage converter 14, the compressor controller 15 and the second water pump 17, and is connected to an inlet of the electric control system air-cooled radiator 3.
Specifically, the cooling liquid in the second cooling circuit 16 is pumped out from the second water pump 17 and flows through the second battery air-cooled radiator 2, then flows through the compressor 13, the voltage converter 14 and the compressor controller 15 in sequence, dissipates heat of the three electric control components and flows back to the second water pump 17 to form a circuit.
Optionally, a gas pipeline 18 is further included, one end of the gas pipeline 18 is connected with the gas compressor 13, sequentially passes through the intercooler 11 and the humidifier 25 of the unmanned aerial vehicle, and is connected with the fuel cell 10.
Specifically, the ambient air is compressed by the compressor 13 to become high-temperature and high-pressure air, and then passes through the intercooler 11 and the humidifier 25 to become medium-temperature and high-pressure humid air, and then enters the fuel cell 10 to react.
Optionally, a first exhaust valve 19 is disposed 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 disposed on the second cooling circuit 16 between the electric control system air-cooled radiator 3 and the compressor 13.
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, so as to ensure the cooling efficiency of the cooling liquid.
Optionally, a first expansion tank 21 and a second expansion tank 22 are also included, the first expansion tank 21 and the second expansion tank 22 being connected to the first cooling circuit 4 and the second cooling circuit 16, respectively.
Specifically, the first expansion tank 21 and the second expansion tank 22 respectively supply the first cooling circuit 4 and the second cooling circuit 16 with cooling liquid, and the first expansion tank 21 and the second expansion tank 22 are respectively provided with a first injection valve 23 and a second injection valve 24 on the connecting lines, and the first injection valve 23 and the second injection valve 24 can be used for injection and drainage control.
The foregoing description of embodiments of the utility model has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (10)
1. An aerodynamic unmanned aerial vehicle heat dissipation system, comprising:
the first battery air-cooled radiator and the second battery air-cooled radiator are respectively arranged on the left side and the right side of the unmanned aerial vehicle, and are sequentially arranged on the first cooling loop and used for radiating the fuel cell of the unmanned aerial vehicle;
the electronic control system air-cooled radiator is close to the second battery air-cooled radiator and arranged on the same side of the unmanned aerial vehicle, and the electronic control system air-cooled radiator is used for radiating heat of the electronic control system of the unmanned aerial vehicle.
2. The aerodynamic unmanned aerial vehicle heat dissipation system of claim 1, wherein the heat dissipation capacity of the first battery air-cooled heat sink is equal to the sum of the heat dissipation capacities of the second battery air-cooled heat sink and the electronic control system air-cooled heat sink.
3. The unmanned aerial vehicle heat dissipation system based on aerodynamics according to claim 1, wherein a first water pump is provided on the first cooling circuit upstream of the first battery air-cooled radiator, a bypass line is connected on the first cooling circuit between the output of the first water pump and the first battery air-cooled radiator, the bypass line is connected with the first cooling circuit downstream of the second battery air-cooled radiator, and a bypass control valve is provided on the bypass line.
4. The unmanned aerial vehicle cooling system of claim 3, wherein the first cooling circuit is connected to the fuel cell via a first branch and to an intercooler of the unmanned aerial vehicle via a second branch, the first branch and the second branch being connected to an input of the first water pump.
5. The aerodynamic unmanned aerial vehicle heat dissipation system of claim 4, wherein the first leg is provided with a water temperature sensor downstream of the fuel cell.
6. The unmanned aerial vehicle based on aerodynamics heat dissipation system according to claim 1, wherein the electronic control system comprises a compressor, a voltage converter, a compressor controller.
7. The unmanned aerial vehicle cooling system of claim 6, wherein the electric control system air-cooled radiator is disposed on a second cooling circuit, one end of the second cooling circuit is connected to an 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 an inlet of the electric control system air-cooled radiator.
8. The unmanned aerial vehicle heat dissipating system of claim 7, further comprising a gas line having one end connected to the compressor, passing in sequence through an intercooler, humidifier of the unmanned aerial vehicle, and connected to the fuel cell.
9. The aerodynamic unmanned aerial vehicle heat dissipation system of claim 7, wherein a first exhaust valve is disposed on the first cooling circuit between the first battery air-cooled heat sink and the second battery air-cooled heat sink, and a second exhaust valve is disposed on the second cooling circuit between the electronic control system air-cooled heat sink and the compressor.
10. The aerodynamic unmanned aerial vehicle heat dissipation system of claim 7, further comprising 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223601950.9U CN219215414U (en) | 2022-12-30 | 2022-12-30 | Unmanned aerial vehicle cooling system based on aerodynamics |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223601950.9U CN219215414U (en) | 2022-12-30 | 2022-12-30 | Unmanned aerial vehicle cooling system based on aerodynamics |
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| CN219215414U true CN219215414U (en) | 2023-06-20 |
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| CN202223601950.9U Active CN219215414U (en) | 2022-12-30 | 2022-12-30 | Unmanned aerial vehicle cooling system based on aerodynamics |
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- 2022-12-30 CN CN202223601950.9U patent/CN219215414U/en active Active
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