Hydrogen fuel cell unmanned aerial vehicle with liquid cooling heat dissipation structure

Abstract

The application discloses a hydrogen fuel cell unmanned aerial vehicle with a liquid cooling heat dissipation structure, which comprises an unmanned aerial vehicle body, a hydrogen fuel cell system, heat dissipation arm of an internal cavity, a liquid distribution main pipe, a first water pump, a liquid guide forward flow pipe, a liquid guide backflow pipe, a propeller, a flow uniformizing mechanism and a liquid collecting main pipe. The cooling liquid after absorbing heat is evenly distributed to each liquid distribution branch pipe through the flow uniformizing mechanism via the liquid distribution main pipe, and then flows into the liquid guide forward flow pipe and the liquid guide backflow pipe in the heat dissipation arm to dissipate heat. The rotor wind of the propeller is fully utilized to dissipate heat by heat convection. Then, the cooling liquid is circulated into the hydrogen fuel cell system via the liquid collecting main pipe. The whole process adopts water cooling heat dissipation. The water cooling radiator is combined with the unmanned aerial vehicle rack, the arm of the unmanned aerial vehicle rack is used as a radiator, the additional radiator structure can be saved to reduce the weight, the rotor wind is fully utilized to dissipate heat by heat convection, the radiator fan components can be saved to reduce the weight, and thus the heat dissipation effect is ensured and the weight is reduced.

Description

Technical Field

[0001] This invention belongs to the field of hydrogen fuel cell drones, and specifically relates to a hydrogen fuel cell drone with a liquid cooling structure. 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 endurance. However, 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 also results in excessive size and weight of the drone, greatly affecting its endurance and fuel efficiency. Therefore, there is a need to propose a hydrogen fuel cell drone with a liquid-cooled heat dissipation structure. Summary of the Invention

[0003] The purpose of this invention is to solve the problems in the background art and provide a hydrogen fuel cell drone with a liquid cooling heat dissipation structure.

[0004] The above-mentioned technical objective of the present invention is achieved through the following technical solution: A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure includes a 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, a flow equalization mechanism, 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 an array along the circumferential direction 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. The pump outlet is connected to the main distribution pipe, which is equipped with a branch pipe that cooperates with the cooling arm. The branch pipe is connected to the inlet of 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 collection pipe. The outlet of the main collection pipe is connected to the input end of the hydrogen fuel cell system. The propeller is located above the cooling arm. Each branch pipe is equipped with the flow equalization mechanism. The propeller is rotatable. This is a mature technology in existing UAVs, so it will not be described in detail in this case.

[0005] This invention uses a main distribution pipe to evenly distribute the cooled liquid, after absorbing heat, to each branch pipe via a flow equalization mechanism. The liquid then flows into the liquid guide pipe and return pipe 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 distribution pipe. The entire process employs water cooling, which is highly effective. 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 the rotor airflow for thermal convection also eliminates the need for a cooling fan component, further reducing weight. Thus, while ensuring effective heat dissipation, weight is reduced.

[0006] Preferably, the flow equalization mechanism includes an inlet plate, a compression spring, a plug, and an inlet pipe. The inlet pipe is fixedly connected to the liquid distribution branch pipe. A fixing block is formed at the end of the inlet pipe. A guide groove communicating with the inside of the liquid distribution branch pipe is opened on the fixing block. The plug is inserted in the guide groove. The inlet plate is fixedly connected to the end of the inlet pipe. The compression spring is arranged between the plug and the inlet plate. The top of the inlet plate has three or more liquid guiding holes. The compression spring in the liquid distribution branch pipe closer to the first water pump exerts a greater force on the plug.

[0007] This invention uses a water inlet pipe and a distribution branch pipe to be fixedly connected. The position of the plug core in the guide groove is controlled by the force of the compression spring pressing the plug core, thereby controlling the amount of coolant passing through. The compression spring of each flow equalization structure has a different elastic force, so that coolant can be distributed in each distribution branch pipe, thereby uniformly distributing the coolant and improving the heat dissipation effect.

[0008] 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.

[0009] Preferably, the heat dissipation arm includes a tube 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 tube body. The tube 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 present invention enhances the heat dissipation effect through the heat dissipation fin structure.

[0010] Preferably, the heat sink structure is a strip-shaped heat sink arranged along the length of the tube body, and three or more strip-shaped heat sinks are arranged in an array along the circumferential direction of the tube body. The width of the strip-shaped heat sink located in the middle of the tube body and the strip-shaped heat sink located away from the middle of the tube body decreases sequentially.

[0011] This invention uses strip-shaped heat sinks, which are finned heat sinks, to increase the heat dissipation area and accelerate heat transfer.

[0012] Preferably, the heat sink structure is an arc-shaped heat sink arranged along the circumferential direction of the tube body, and a plurality of arc-shaped heat sinks are arranged in an array along the length direction of the tube body.

[0013] This invention uses arc-shaped heat sinks combined with the rotation of the top propeller. Compared with the setting of strip heat sinks, the airflow received between the heat sinks is not blocked, which expands the heat dissipation area, accelerates heat transfer, and improves the heat dissipation effect.

[0014] Preferably, a temperature sensor is also provided at the output end of the hydrogen fuel cell, and the arc-shaped heat sink is detachably connected to the tube body.

[0015] This invention uses a temperature sensor to detect temperature, allowing the number of heat sinks to be selected before shipment based on the different power levels of the hydrogen fuel cell, ensuring heat dissipation while minimizing weight.

[0016] Preferably, the bottom of the arc-shaped heat sink is provided with a retaining post, the side wall of the retaining post is provided with an annular retaining ring in the circumferential direction, and the tube body is provided with an annular groove that cooperates with the annular retaining ring.

[0017] This invention utilizes the engagement of a ring-shaped retaining ring and a ring-shaped groove to allow for detachable connection of the arc-shaped heat sink.

[0018] Preferably, thermally conductive silicone is also filled between the card post and the annular groove. The thermally conductive silicone strengthens the connection between the arc-shaped heat sink and the tube body, while also enhancing the heat conduction effect.

[0019] Preferably, both the distribution manifold and the collection manifold are made of thermally conductive materials to enhance the overall thermal conductivity.

[0020] In summary, the beneficial effects of this invention are as follows: 1. This invention uses a split-type main pipe to evenly distribute the cooled liquid after absorbing heat to each branch pipe through a flow equalization mechanism. The liquid then flows into the liquid guide pipe and liquid return pipe in the heat dissipation arm for heat dissipation, making full use of the rotor airflow of the propeller for thermal convection heat dissipation. Afterwards, it circulates to the hydrogen fuel cell system through the main 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. By making full use of the rotor airflow for thermal convection, the cooling fan component can be eliminated, reducing the weight. Thus, the heat dissipation effect is maintained while the weight is reduced. 2. The present invention uses a water inlet pipe and a distribution branch pipe to be fixedly connected. The position of the plug core in the guide groove is controlled by the force of the compression spring pressing the plug core, thereby controlling the amount of coolant passing through. The spring force of the compression spring of each flow equalization structure is different, so that coolant can be distributed in each distribution branch pipe, thereby uniformly distributing the coolant and improving the heat dissipation effect. 3. The present invention uses arc-shaped heat sinks in conjunction with the rotation of the top propeller. Compared with the setting of strip heat sinks, the airflow received between the heat sinks is not blocked, which expands the heat dissipation area, accelerates heat transfer, and improves the heat dissipation effect. 4. This invention uses a temperature sensor to detect temperature, allowing the number of heat sinks to be selected before shipment based on the different power levels of the hydrogen fuel cell, ensuring heat dissipation while minimizing weight. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the fuselage of the drone of the present invention; Figure 2 This is the present invention. Figure 1 An enlarged view of point B; Figure 3 This is a schematic diagram of the arc-shaped heat sink of the present invention; Figure 4 This is a schematic diagram of the flow equalization mechanism of the present invention; Figure 5 This is a schematic diagram showing the separation of the plug core and the guide groove in the flow equalization mechanism of the present invention; Figure 6 This is a cross-sectional schematic diagram of the arc-shaped heat sink and the tube body of the present invention; Figure 7 This is the present invention. Figure 6 An enlarged view of point C; Figure 8 This is an overall schematic diagram of the UAV of the present invention; Figure 9 This is a schematic diagram of the strip-shaped heat sink of the present invention; Figure 10 This is the present invention. Figure 9 An enlarged view of point A; Figure 11 This is a schematic diagram of the present invention without a plate heat exchanger. Detailed Implementation

[0022] The following specific embodiments are merely illustrative of the present invention and are not intended to limit the invention. 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 the present invention.

[0023] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] Example 1

[0025] like Figure 1-2 As shown, a hydrogen fuel cell drone with a liquid-cooled heat dissipation structure includes a drone fuselage 1, a hydrogen fuel cell system 2, heat dissipation arms 3 with internal cavities, a liquid distribution manifold 4, a first water pump 5, a liquid guide pipe 6, a liquid return pipe 7, a propeller 8, a flow equalization mechanism 9, 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 1 has a liquid guide pipe 6 and a liquid 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, and the outlet of the liquid guide pipe 6 and the inlet of the liquid return pipe 7 are connected by a pipe. The outlet of pipe 7 is connected to the inlet of the main liquid distribution pipe 40, and the outlet of the main liquid distribution 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, and each liquid distribution branch pipe 401 is equipped with the flow equalization mechanism 9. 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, and the outlet of the main liquid distribution pipe 40 is connected to the cold medium inlet of the plate heat exchanger 22. Both the main liquid distribution pipe 4 and the main liquid distribution pipe 40 are made of thermally conductive materials. The cold source fluid channel in the plate heat exchanger uses superconducting fluid, which is a new technology for superconducting heat transfer and high-efficiency heat exchange. The main function of superconducting fluid under normal pressure is to conduct electricity faster than water. It generally does not freeze at -40 degrees Celsius and has a higher boiling point than water. Nowadays, many people use antifreeze instead, which is also cheaper. In plate heat exchangers, deionized antifreeze is used in the heat source fluid channel for easy maintenance.

[0026] In order to reduce weight, plate heat exchangers can be omitted in hydrogen fuel cell system 2. The output end of hydrogen fuel cell 2 is directly connected to the liquid distribution manifold 4, and the coolant introduced is deionized antifreeze, which can also achieve the effect of heat dissipation.

[0027] like Figure 4-5As shown, the flow equalization mechanism 9 includes a water inlet plate 91, a compression spring 92, a plug core 93, and a water inlet pipe 94. The water inlet pipe 94 is fixedly connected to the liquid distribution branch pipe 401. A fixing block 941 is formed at the end of the water inlet pipe 94. A guide groove 942 communicating with the inside of the liquid distribution branch pipe 401 is opened on the fixing block 941. The plug core 93 is inserted in the guide groove 942. The water inlet plate 91 is fixedly connected to the end of the water inlet pipe 414. The compression spring 92 is spring-loaded between the plug core 453 and the water inlet plate 91. The top of the water inlet plate 91 has three or more liquid guiding holes 95. The closer the compression spring 92 is to the liquid distribution branch pipe 401 of the first water pump 5, the greater the force with which it presses against the plug core 93.

[0028] like Figure 3 As shown, the heat dissipation arm 3 includes a tube 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 tube body 31. The tube 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 an arc-shaped heat dissipation fin 902 arranged along the circumferential direction of the tube body 31. Several arc-shaped heat dissipation fins 902 are arranged in an array along the length direction of the tube body 31.

[0029] like Figure 2 As shown, a temperature sensor 211 is also provided on the output end of the hydrogen fuel cell 21, and the arc-shaped heat sink 902 is detachably connected to the tube body 31.

[0030] like Figure 6-7 As shown, the bottom of the arc-shaped heat sink 902 is provided with a retaining post 903, and the side wall of the retaining post 903 is provided with an annular retaining ring 904 in the circumferential direction. The tube body 31 is provided with an annular groove 905 that cooperates with the annular retaining ring 904. Thermally conductive silicone 906 is also filled between the retaining post 903 and the annular groove 905.

[0031] Working principle: such as Figure 1-10As shown, during use, the plate heat exchanger transfers the heat-absorbing coolant through the main distribution pipe 4 via heat exchange. The cooled coolant, after absorbing heat, is then evenly distributed to each branch pipe 401 via the flow equalization mechanism 9. It then flows into the liquid guide pipe 6 and the liquid return pipe 7 within the heat dissipation arm 3 for heat dissipation. The heat dissipation area is expanded through the heat sink structure 90, accelerating heat transfer. The rotor airflow from the propeller 8 is fully utilized for thermal convection cooling. The coolant is then circulated back to the hydrogen fuel cell system 2 through the main distribution pipe 40. The entire process uses water cooling, which is highly effective. Furthermore, by combining the water-cooled radiator with the drone frame, using the drone frame's arm as a radiator, the need for an additional radiator structure can be eliminated, reducing weight. Utilizing the rotor airflow for thermal convection also eliminates the need for a cooling fan component, further reducing weight. This ensures effective heat dissipation while reducing weight.

[0032] Example 2

[0033] Unlike Example 1, as Figure 9-10 As shown, the heat sink structure 90 is a strip heat sink 901 arranged along the length direction of the tube body 31. Three or more strip heat sinks 901 are arranged in an array along the circumferential direction of the tube body 31. The width of the strip heat sink 901 located in the middle of the tube body 31 to the strip heat sink 901 located away from the middle of the tube body 31 decreases sequentially.

[0034] Example 3

[0035] like Figure 11 As shown, unlike Embodiment 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, and a plate heat exchanger is not used, which can reduce weight, but will increase the maintenance cost of the coolant.

Claims

1. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure, characterized in that, The system includes a 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), a flow equalization mechanism (9), 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 wall of the drone fuselage (1). The inner wall of each heat dissipation arm (1) is provided with a liquid guide pipe (6) and a liquid guide return pipe (7) along the length direction. The output end of the hydrogen fuel cell system (2) is connected to the inlet of the first water pump (5). The outlet of the first water pump (5) is connected to the main distribution pipe (4). The main distribution pipe (4) is provided with a distribution branch pipe (401) that cooperates with the heat dissipation arm (3). The distribution branch pipe (401) is connected to the inlet of 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 liquid collection pipe (40). The outlet of the liquid 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). Each distribution branch pipe (401) is provided with the flow equalization mechanism (9).

2. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 1, characterized in that, The flow equalization mechanism (9) includes an inlet plate (91), a compression spring (92), a plug core (93), and an inlet pipe (94). The inlet pipe (94) is fixedly connected to the liquid distribution branch pipe (401). A fixing block (941) is formed at the end of the inlet pipe (94). A guide groove (942) communicating with the inside of the liquid distribution branch pipe (401) is opened on the fixing block (941). The plug core (93) is inserted in the guide groove (942). The inlet plate (91) is fixedly connected to the end of the inlet pipe (414). The compression spring (92) is spring-loaded between the plug core (453) and the inlet plate (91). The top of the inlet plate (91) has three or more liquid guiding holes (95). The compression spring (92) in the liquid distribution branch pipe (401) closer to the first water pump (5) exerts a greater force on the plug core (93).

3. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 1, characterized in that, 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), and the outlet of the manifold (40) is connected to the cold medium inlet of the plate heat exchanger (22).

4. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 1, characterized in that, The heat dissipation arm (3) includes a tube 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 tube body (31), and the tube body (31) is provided with heat dissipation fin structure (90) on the side wall of the liquid guiding pipe (6) and the liquid guiding return pipe (7).

5. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 4, characterized in that, The heat sink structure (90) is a strip heat sink (901) arranged along the length of the tube body (31). There are three or more strip heat sinks (901) arranged in an array along the circumferential direction of the tube body (31). The width of the strip heat sink (901) located in the middle of the tube body (31) and the strip heat sink (901) located away from the middle of the tube body (31) decreases sequentially.

6. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 5, characterized in that, The heat sink structure (90) is an arc-shaped heat sink (902) arranged along the circumferential direction of the tube body (31), and several arc-shaped heat sinks (902) are arranged in an array along the length direction of the tube body (31).

7. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 6, characterized in that, A temperature sensor (211) is also provided on the output end of the hydrogen fuel cell (21), and the arc-shaped heat sink (902) is detachably connected to the tube (31).

8. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 7, characterized in that, The bottom of the arc-shaped heat sink (902) is provided with a retaining post (903), and the side wall of the retaining post (903) is provided with an annular retaining ring (904) in the circumferential direction. The tube body (31) is provided with an annular groove (905) that cooperates with the annular retaining ring (904).

9. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 8, characterized in that, Thermally conductive silicone (906) is also filled between the pin (903) and the annular groove (905).

10. A hydrogen fuel cell drone with a liquid-cooled heat dissipation structure according to claim 1, characterized in that, Both the main distribution pipe (4) and the main collection pipe (40) are made of thermally conductive materials.

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