Heat dissipation structure suitable for hydrogen fuel cell unmanned aerial vehicle

Abstract

The utility model discloses a heat dissipation structure suitable for a hydrogen fuel cell unmanned aerial vehicle. The heat dissipation structure comprises a hydrogen fuel cell unmanned aerial vehicle body, a hydrogen fuel cell system, a heat dissipation vehicle arm with an inner cavity, a liquid distribution header pipe, a first water pump, a liquid guide downstream pipe, a liquid guide backflow pipe, a propeller, a liquid collection header pipe and an adapter. Cooling liquid absorbing heat is distributed to each liquid distribution branch pipe and then flows into the liquid guide downstream pipe and the liquid guide backflow pipe in the heat dissipation machine arm for heat dissipation, rotor wing wind of a propeller is fully utilized for heat convection heat dissipation, then the cooling liquid circulates into a hydrogen fuel cell system through the liquid collection header pipe, water cooling heat dissipation is adopted in the whole process, and the heat dissipation efficiency is greatly improved. The unmanned aerial vehicle is simple in structure and remarkable in effect, meanwhile, the water-cooling radiator is combined with the unmanned aerial vehicle frame, the vehicle arms of the unmanned aerial vehicle frame serve as the radiator, an additional radiator structure can be omitted, the weight is reduced, rotor wing wind is fully utilized for heat convection, the weight is reduced, meanwhile, water pipes are convenient to assemble through adapters, and use is more convenient.

Description

Technical Field

[0001] This utility model belongs to the field of heat dissipation structure, specifically relating to a heat dissipation structure suitable for hydrogen fuel cell drones. Background Technology

[0002] As a product of the 21st century, drones play a crucial role in driving industrial production and military development. Currently, most drones on the market are powered by lithium batteries. To increase flight range, it is necessary to install larger or higher-capacity batteries. However, a larger battery proportion increases weight and flight energy consumption. Many existing drones use hydrogen fuel cells for range, but existing hydrogen fuel cells must solve the problem of heat dissipation. Current drone cooling systems are usually air-cooled. With air cooling, both the radiator and cooling fan need to be made of strong metal. At the same time, to achieve better heat dissipation and obtain a larger heat dissipation surface area, the size of the radiator and the blades of the cooling fan need to reach a certain scale, which will result in excessive size and weight of the drone, greatly affecting its range and fuel efficiency. Therefore, it is necessary to propose a heat dissipation structure suitable for hydrogen fuel cell drones. Utility Model Content

[0003] The purpose of this invention is to solve the problems in the background art and provide a heat dissipation structure suitable for hydrogen fuel cell drones.

[0004] The above-mentioned technical objective of this utility model is achieved through the following technical solution:

[0005] A heat dissipation structure suitable for a hydrogen fuel cell drone includes a hydrogen fuel cell drone fuselage, a hydrogen fuel cell system, heat dissipation arms with internal cavities, a liquid distribution manifold, a first water pump, a liquid guide pipe, a liquid return pipe, a propeller, and a liquid collection manifold. The hydrogen fuel cell system is located in the middle of the drone fuselage. The heat dissipation arms are evenly distributed in a circumferential array on the side walls of the drone fuselage. Each heat dissipation arm has a liquid guide pipe and a liquid return pipe along its length on its inner wall. The output end of the hydrogen fuel cell system is connected to the inlet of the first water pump, and the outlet of the first water pump is connected to the liquid distribution manifold. The main pipe is equipped with a liquid distribution branch pipe that cooperates with the heat dissipation arm. The liquid distribution branch pipe is connected to the inlet of the liquid guiding flow pipe. Both ends of the liquid distribution branch pipe are equipped with adapters. One adapter is fixed to the main liquid distribution pipe, and the other adapter is fixed to the liquid guiding flow pipe. The outlet of the liquid guiding flow pipe and the inlet of the liquid guiding return pipe are connected by a pipe. The outlet of the liquid guiding return pipe is connected to the inlet of the main liquid collection pipe. The outlet of the main liquid collection pipe is connected to the input end of the hydrogen fuel cell system. The propeller is located above the heat dissipation arm. The propeller can rotate. This is a mature technology of existing UAVs, so it will not be described in detail in this case.

[0006] This invention distributes the cooled liquid, after absorbing heat, to each branch pipe via a main manifold. The liquid then flows into the co-current and return pipes within the cooling arm for heat dissipation, fully utilizing the rotor airflow for thermal convection. The cooled liquid is then circulated back to the hydrogen fuel cell system through the main manifold. The entire process employs water cooling, resulting in significant effectiveness. Furthermore, by integrating the water-cooled radiator with the drone frame, using the drone frame's arm as a radiator, the need for an additional radiator structure is eliminated, reducing weight. Utilizing rotor airflow for thermal convection further reduces the need for cooling fan components, thus ensuring effective heat dissipation while minimizing weight. Additionally, the adapter facilitates assembly between water pipes, making it more convenient to use.

[0007] Preferably, the heat dissipation arm includes an arm body, and the liquid guiding convection pipe and the liquid guiding return pipe are located on the left and right sides of the inner cavity of the arm body. The arm body is provided with heat dissipation fin structures on the side walls of the liquid guiding convection pipe and the liquid guiding return pipe. The heat dissipation fin structures are strip-shaped heat dissipation fins arranged along the length direction of the arm body. Three or more strip-shaped heat dissipation fins are arranged in an array along the circumferential direction of the arm body. This utility model uses strip-shaped heat dissipation fins to expand the heat dissipation area and accelerate heat transfer.

[0008] Preferably, the width of the strip heat sink located in the middle of the arm body decreases sequentially from the strip heat sink located away from the middle of the arm body, thereby reducing the area while ensuring the heat dissipation effect.

[0009] Preferably, the adapter includes a hollow tube body, both ends of the tube are provided with insertion grooves to facilitate tube insertion, the outer wall of the tube body is provided with two symmetrical first semi-through grooves along the axial direction of the tube body, and the outer walls of both ends of the tube body are arrayed with several protruding retaining rings along the axial direction of the tube body, and the liquid distribution branch is a flexible tube.

[0010] This invention involves inserting the distribution branch pipe connected to the adapter into the insertion groove. The first semi-through groove allows the outer wall of the pipe to deform after the distribution branch pipe is inserted, facilitating the insertion of the distribution branch pipe and ensuring a tight fit between the adapter and the distribution branch pipe, thus achieving a quick connection between the adapter and the distribution branch pipe. Subsequently, the groove formed between the retaining rings allows the cable ties to be used to further connect the distribution branch pipe and prevent it from falling off.

[0011] Preferably, both the distribution manifold and the collection manifold are made of thermally conductive materials to enhance the overall thermal conductivity.

[0012] Preferably, the hydrogen fuel cell system includes a hydrogen fuel cell, a plate heat exchanger, and a second water pump. The output end of the hydrogen fuel cell is connected to the inlet of the second water pump, the outlet of the second water pump is connected to the heat medium inlet of the plate heat exchanger, the input end of the hydrogen fuel cell is connected to the heat medium outlet of the plate heat exchanger, the cold medium outlet of the plate heat exchanger is connected to the inlet of the first water pump, and the outlet of the manifold is connected to the cold medium inlet of the plate heat exchanger. Heat exchange is performed using a plate heat exchanger.

[0013] Preferably, fixing plates are fixed on both the left and right sides of the arm body, and the liquid guiding convection pipe and the liquid guiding return pipe are formed between the fixing plates and the inner cavity of the arm body, so that the liquid is closer to the heat sink and the heat conduction effect is enhanced.

[0014] Preferably, the cold source fluid channel in the plate heat exchanger of this utility model uses superconducting fluid. Superconducting fluid is a new technology for superconducting heat transfer and high-efficiency heat exchange. Under normal pressure, the main function of superconducting fluid is to conduct heat faster than water. It generally does not freeze at -40 degrees Celsius and has a higher boiling point than water. Now, many antifreeze is used instead, which is also cheaper. The heat source fluid channel in the plate heat exchanger uses deionized antifreeze, which is convenient for later maintenance.

[0015] Preferably, the hydrogen fuel cell system is a hydrogen fuel cell, the output end of the hydrogen fuel cell is connected to the inlet of the first water pump, and the outlet of the manifold is connected to the input end of the hydrogen fuel cell.

[0016] In summary, the beneficial effects of this utility model are as follows:

[0017] 1. This utility model distributes the cooled liquid, after absorbing heat, to each branch pipe through the main distribution pipe. The liquid then flows into the liquid guide pipe and the liquid return pipe in the cooling arm for heat dissipation, making full use of the rotor airflow for thermal convection. Afterward, it circulates to the hydrogen fuel cell system through the main distribution pipe. The entire process uses water cooling, which is very effective. At the same time, the water-cooled radiator is combined with the drone frame, and the drone frame arm is used as a radiator. This can reduce the weight by eliminating the need for an additional radiator structure. Making full use of the rotor airflow for thermal convection can eliminate the need for a cooling fan component, thus reducing weight. This ensures heat dissipation while reducing weight. In addition, the adapter facilitates the assembly of water pipes, making it more convenient to use.

[0018] 2. This utility model inserts the liquid distribution branch pipe connected to the adapter into the insertion groove. The first semi-through groove allows the outer wall of the pipe to deform after the liquid distribution branch pipe is inserted, which facilitates the insertion of the liquid distribution branch pipe and allows the adapter to fit tightly with the liquid distribution branch pipe, thus completing the quick connection between the adapter and the liquid distribution branch pipe. Then, the groove formed between the retaining rings can be used to fix the cable ties to further connect the liquid distribution branch pipe and prevent it from falling off.

[0019] 3. This utility model uses strip-shaped heat sinks, which are finned heat sinks, to expand the heat dissipation area and accelerate heat transfer. Attached Figure Description

[0020] Figure 1 This is an overall schematic diagram of the UAV of this utility model;

[0021] Figure 2 This is a schematic diagram of the strip-shaped heat sink of this utility model;

[0022] Figure 3 This is a utility model Figure 3 An enlarged schematic diagram of point A.

[0023] Figure 4 This is a schematic diagram of the fuselage of the unmanned aerial vehicle (UAV) of this utility model;

[0024] Figure 5 This is a utility model Figure 4 An enlarged view of point B;

[0025] Figure 6 This is a schematic diagram of the adapter of this utility model;

[0026] Figure 7 This is a schematic diagram of the heat dissipation of this utility model;

[0027] Figure 8 This is a schematic diagram of the present invention without a plate heat exchanger; Detailed Implementation

[0028] The following specific embodiments are merely explanations of this utility model and are not intended to limit it. After reading this specification, those skilled in the art can make modifications to these embodiments without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this utility model.

[0029] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0030] Example 1

[0031] like Figure 1 , 4 As shown in Figure 7, a heat dissipation structure suitable for a hydrogen fuel cell drone includes a hydrogen fuel cell drone fuselage 1, a hydrogen fuel cell system 2, a heat dissipation arm 3 with an internal cavity, a liquid distribution manifold 4, a first water pump 5, a liquid guide pipe 6, a liquid guide return pipe 7, a propeller 8, and a liquid collection manifold 40. The hydrogen fuel cell system 2 is located in the middle of the drone fuselage 1. The heat dissipation arms 3 are evenly distributed in an array along the circumferential direction on the side walls of the drone fuselage 1. Each heat dissipation arm 3 has a liquid guide pipe 6 and a liquid guide return pipe 7 along its length on its inner wall. The output end of the hydrogen fuel cell system 2 is connected to the inlet of the first water pump 5, and the outlet of the first water pump 5 is connected to the liquid distribution manifold 4. The liquid distribution manifold 4 has a liquid distribution branch pipe 401 that cooperates with the heat dissipation arms 3. The liquid distribution branch pipe 401 is connected to the inlet of the liquid guide pipe 6. Both ends of the liquid distribution branch pipe 401 are provided with adapters 60, one of which is fixed to... On the main distribution pipe 4, another adapter 60 is fixed to the liquid guiding pipe 6. The outlet of the liquid guiding pipe 6 and the inlet of the liquid guiding return pipe 7 are connected by a pipe. The outlet of the liquid guiding return pipe 7 is connected to the inlet of the main collection pipe 40. The outlet of the main collection pipe 40 is connected to the input end of the hydrogen fuel cell system 2. The propeller 8 is located above the heat dissipation arm 3. Both the main distribution pipe 4 and the main collection pipe 40 are made of thermally conductive materials. The hydrogen fuel cell system 2 includes a hydrogen fuel cell 21, a plate heat exchanger 22, and a second water pump 23. The output end of the hydrogen fuel cell 21 is connected to the inlet of the second water pump 23. The outlet of the second water pump 23 is connected to the hot medium inlet of the plate heat exchanger 22. The input end of the hydrogen fuel cell is connected to the hot medium outlet of the plate heat exchanger 22. The cold medium outlet of the plate heat exchanger is connected to the inlet of the first water pump 5. The outlet of the main collection pipe 40 is connected to the cold medium inlet of the plate heat exchanger 22.

[0032] like Figure 2-3As shown, the heat dissipation arm 3 includes an arm body 31. The liquid guiding pipe 6 and the liquid guiding return pipe 7 are located on the left and right sides of the inner cavity of the arm body 31. The arm body 31 is provided with heat dissipation fin structures 90 on the side walls of the liquid guiding pipe 6 and the liquid guiding return pipe 7. The heat dissipation fin structure 90 is a strip-shaped heat dissipation fin 901 arranged along the length direction of the arm body 31. Three or more strip-shaped heat dissipation fins 901 are arranged in an array along the circumferential direction of the arm body 31. The width of the strip-shaped heat dissipation fin 901 located in the middle of the arm body 31 to the strip-shaped heat dissipation fin 901 away from the middle of the arm body 31 decreases sequentially.

[0033] like Figure 6 As shown, the adapter 60 includes a hollow tube 601. Both ends of the tube 601 are provided with insertion grooves 602 to facilitate pipe insertion. The outer wall of the tube 601 has two symmetrical first semi-through grooves 603 along the axial direction of the tube 601. The outer walls of both ends of the tube 601 are arrayed with several protruding retaining rings 604 along the axial direction of the tube 601. The liquid distribution branch pipe 401 is a flexible tube.

[0034] like Figure 3 As shown, fixing plates 310 are fixed on both the left and right sides of the arm body 31, and the liquid guiding flow pipe 6 and the liquid guiding return pipe 7 are formed between the fixing plates 310 and the inner cavity of the arm body 31.

[0035] Working principle: such as Figure 1-7 As shown, during use, the plate heat exchanger transfers the cooled liquid after heat absorption through the main distribution pipe 4, then distributes it to each branch pipe 401, and then flows into the liquid guide pipe 6 and liquid guide return pipe 7 in the heat dissipation arm 3 for heat dissipation. The heat dissipation area is expanded by the heat dissipation fin structure 90, accelerating heat transfer and making full use of the rotor airflow of the propeller 8 for thermal convection heat dissipation. Then, it is circulated to the hydrogen fuel cell system 2 through the main distribution pipe 40. The entire process uses water cooling, which is very effective. At the same time, the water cooling radiator is combined with the drone frame, and the drone frame arm is used as a radiator. This can reduce the weight by eliminating the need for an additional radiator structure. Making full use of the rotor airflow for thermal convection can eliminate the need for a cooling fan component, thus reducing weight. This ensures heat dissipation effect while reducing weight.

[0036] Example 2

[0037] like Figure 8As shown, unlike Example 1, the hydrogen fuel cell system (2) is a hydrogen fuel cell (21). The output end of the hydrogen fuel cell (21) is connected to the inlet of the first water pump (5), and the outlet of the manifold (40) is connected to the input end of the hydrogen fuel cell (21). Deionized antifreeze is used as the coolant throughout the process. Plate heat exchangers are not used, which can reduce weight, but will increase the maintenance cost of the coolant.

Claims

1. A heat dissipation structure suitable for a hydrogen fuel cell drone, characterized by, The unmanned aerial vehicle body (1), the hydrogen fuel cell system (2), the heat dissipation arm (3) with an internal cavity, the liquid distribution main pipe (4), the first water pump (5), the liquid guide forward flow pipe (6), the liquid guide backflow pipe (7), the propeller (8), and the liquid collection main pipe (40) are included. The hydrogen fuel cell system (2) is arranged in the middle of the unmanned aerial vehicle body (1). The heat dissipation arms (3) are evenly distributed along the circumferential direction on the side wall of the unmanned aerial vehicle body (1). The inner wall of each heat dissipation arm (3) is provided with the liquid guide forward flow pipe (6) and the liquid guide backflow pipe (7) along the length direction. The output end of the hydrogen fuel cell system (2) is connected with the inlet of the first water pump (5). The outlet of the first water pump (5) is connected with the liquid distribution main pipe (4). The liquid distribution main pipe (4) is provided with a liquid distribution branch pipe (401) matched with the heat dissipation arm (3). The liquid distribution branch pipe (401) is connected with the inlet of the liquid guide forward flow pipe (6). The two ends of the liquid distribution branch pipe (401) are provided with an adapter (60). One of the adapters (60) is fixed on the liquid distribution main pipe (4), and the other adapter (60) is fixed on the liquid guide forward flow pipe (6). The outlet of the liquid guide forward flow pipe (6) and the inlet of the liquid guide backflow pipe (7) are connected through a pipeline. The outlet of the liquid guide backflow pipe (7) and the inlet of the liquid collection main pipe (40) are connected. The outlet of the liquid collection main pipe (40) is connected with the input end of the hydrogen fuel cell system (2). The propeller (8) is arranged above the heat dissipation arm (3).

2. The heat dissipation structure for a hydrogen fuel cell unmanned aerial vehicle according to claim 1, wherein The heat dissipation arm (3) includes an arm body (31). The liquid guide forward flow pipe (6) and the liquid guide backflow pipe (7) are arranged on the left and right sides of the inner cavity of the arm body (31). The arm body (31) is provided with a heat dissipation fin structure (90) on the side wall of the liquid guide forward flow pipe (6) and the liquid guide backflow pipe (7).

3. The heat dissipation structure for a hydrogen fuel cell drone according to claim 2, wherein The heat dissipation fin structure (90) is a strip-shaped heat dissipation fin (901) arranged along the length direction of the arm body (31). The strip-shaped heat dissipation fin (901) is arranged in an array of more than three pieces along the circumferential direction of the arm body (31).

4. The heat dissipation structure for a hydrogen fuel cell drone according to claim 3, wherein The width of the strip-shaped heat dissipation fin (901) located in the middle of the arm body (31) gradually decreases to the strip-shaped heat dissipation fin (901) away from the middle of the arm body (31).

5. The heat dissipation structure for a hydrogen fuel cell drone according to claim 1, wherein The adapter (60) includes a hollow pipe body (601). The two ends of the pipe body (601) are provided with plug-in grooves (602) for facilitating the insertion of a pipeline. The outer wall of the pipe body (601) is provided with two symmetrical first half grooves (603) along the axial direction of the pipe body (601). The outer wall of the two ends of the pipe body (601) is arrayed with a plurality of protruding clamping rings (604) along the axial direction of the pipe body (601).

6. The heat dissipation structure for a hydrogen fuel cell drone according to claim 5, wherein The liquid distribution branch pipe (401) is a flexible pipe.

7. The heat dissipation structure for a hydrogen fuel cell drone according to claim 1, wherein The liquid distribution main pipe (4) and the liquid collection main pipe (40) are made of a heat-conducting material.

8. The heat dissipation structure for a hydrogen fuel cell drone of claim 1, wherein, The hydrogen fuel cell system (2) comprises a hydrogen fuel cell (21), a plate heat exchanger (22) and a second water pump (23), the output end of the hydrogen fuel cell (21) is connected with the inlet of the second water pump (23), the outlet of the second water pump (23) is connected with the hot medium inlet of the plate heat exchanger (22), the input end of the hydrogen fuel cell is connected with the hot medium outlet of the plate heat exchanger (22), the cold medium outlet of the plate heat exchanger is connected with the inlet of the first water pump (5), and the outlet of the liquid collecting header (40) is connected with the cold medium inlet of the plate heat exchanger (22).

9. The heat dissipation structure for a hydrogen fuel cell drone of claim 2, wherein, The left and right sides of the arm body (31) are fixed with fixed plates (310), and the fixed plates (310) and the inner cavities of the arm bodies (31) form the liquid guiding forward flow pipes (6) and the liquid guiding backflow pipes (7).

10. The heat dissipation structure for a hydrogen fuel cell drone of claim 1, wherein, The hydrogen fuel cell system (2) is a hydrogen fuel cell (21), the output end of the hydrogen fuel cell (21) is connected with the inlet of the first water pump (5), and the outlet of the liquid collecting header (40) is connected with the input end of the hydrogen fuel cell (21).

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