Hydrogen fuel cell temperature control structure for unmanned aerial vehicle

Abstract

The invention relates to the technical field of hydrogen fuel cells, in particular to a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle, the hydrogen fuel cell temperature control structure comprises a heat dissipation mounting shell, a flow guide heat dissipation cavity and a storage cavity are arranged in the heat dissipation mounting shell, the storage cavity is used for limiting and mounting a hydrogen fuel cell, and a circulating temperature control device is mounted in the heat dissipation mounting shell. The circulating temperature control device comprises circulating pipelines evenly distributed in the heat dissipation mounting shell, the circulating pipelines are used for guiding cooling liquid, a circulating conveying device is mounted on the circulating pipelines, and an air guiding device is mounted at the top of the heat dissipation mounting shell and comprises a one-way air inlet shell mounted at the top of the heat dissipation mounting shell. The one-way air inlet shell is used for guiding airflow to the flow guide heat dissipation cavity, a transmission flow guide head is installed at the bottom of the one-way air inlet shell, a fan is installed on the transmission flow guide head, and the transmission flow guide head is in transmission connection with the circulating conveying device. According to the unmanned aerial vehicle, the heat dissipation efficiency can be effectively improved, meanwhile, extra power consumption is reduced, and the cruising ability of the unmanned aerial vehicle is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of hydrogen fuel cells, and more particularly to a temperature control structure for a hydrogen fuel cell used in an unmanned aerial vehicle (UAV). Background Art

[0002] The working principle of a hydrogen fuel cell is to convert its chemical energy into electrical energy through an electrochemical reaction of hydrogen and oxygen. In a UAV, this electrical energy is used to drive an electric motor, which in turn drives a propeller to rotate, enabling the UAV to fly.

[0003] Chinese Patent No. CN115425252A discloses a hydrogen-powered fuel cell structure for a UAV. The hydrogen-powered fuel cell structure includes a battery housing, a fuel cell stack, and an air driving member. There is an air passage groove in the battery housing, and the fuel cell stack is adapted to the air passage groove so that all the air flowing into the battery housing flows into the fuel cell stack through the air passage groove, improving the reaction efficiency of the fuel cell stack. The air driving member is installed on the battery housing, and the air driving member discharges the air after driving the reaction of the fuel cell stack out of the battery housing. After the reacted air is discharged, the air pressure in the battery housing drops, and the external air flows into the battery housing under the action of atmospheric pressure.

[0004] Although the above device can achieve heat dissipation protection through multiple air driving members, when the air driving members continuously drive for heat dissipation, it is necessary to continuously consume additional electrical energy, resulting in additional power consumption, which will affect the endurance. Moreover, the heat dissipation method of this device is relatively single, and it is difficult to achieve uniform and effective heat dissipation, resulting in poor heat dissipation effect. Summary of the Invention

[0005] In view of the above problems, a temperature control structure for a hydrogen fuel cell used in a UAV is provided. Through the temperature control structure, the heat dissipation efficiency can be effectively improved, while the additional power consumption is reduced, and the endurance of the UAV is improved.

[0006] To solve the problems of the prior art, the present invention provides a temperature control structure for a hydrogen fuel cell used in a UAV, which is installed on the outside of the hydrogen fuel cell. The temperature control structure includes a heat dissipation installation shell. Inside the heat dissipation installation shell, there are a diversion heat dissipation chamber and a storage chamber. The storage chamber is used for limiting and installing the hydrogen fuel cell. A circulation temperature control device is installed inside the heat dissipation installation shell. The circulation temperature control device includes circulation pipes evenly distributed inside the heat dissipation installation shell. The circulation pipes are used to guide the coolant. A circulation conveying device is installed on the circulation pipes. An air diversion device is installed on the top of the heat dissipation installation shell. The air diversion device includes a one-way intake housing installed on the top of the heat dissipation installation shell. The one-way intake housing is used to guide air flow into the diversion heat dissipation chamber. A transmission diversion head is installed at the bottom of the one-way intake housing. A fan is installed on the transmission diversion head. The transmission diversion head is in transmission connection with the circulation conveying device.

[0007] Preferably, a spiral diversion groove is provided inside the unidirectional air intake housing, and a plurality of air intake diversion holes are provided outside the unidirectional air intake housing. An air intake floating film is provided in each air intake diversion hole.

[0008] Preferably, the transmission diversion head includes a diversion sleeve installed at the air outlet end of the unidirectional air intake housing. A diffusion conical head is provided inside the diversion sleeve. A first rotating mounting shaft is rotatably mounted on the diffusion conical head. The first rotating mounting shaft is connected to the fan. A first telescopic rod is slidably mounted on the first rotating mounting shaft with a limit. A transmission docking head is mounted on the first telescopic rod. A first spring is mounted between the transmission docking head and the first rotating mounting shaft.

[0009] Preferably, the circulation pipeline includes an outer circulation pipe distributed outside the heat dissipation mounting shell. The circulation pipeline further includes an inner circulation pipe distributed inside the heat dissipation mounting shell. The outer circulation pipe and the inner circulation pipe are interconnected. The inner circulation pipe is connected to the circulation conveying device.

[0010] Preferably, the circulation conveying device includes a unidirectional compression assembly installed on the diversion heat dissipation chamber. The unidirectional compression assembly is connected to the inner circulation pipe. The unidirectional compression assembly is used to drive the coolant to flow. A kinetic energy conversion device is further installed on the unidirectional compression assembly. The kinetic energy conversion device is in transmission connection with the transmission diversion head.

[0011] Preferably, the unidirectional compression assembly includes a compression sleeve installed in the diversion heat dissipation chamber. A unidirectional liquid inlet valve and a unidirectional liquid outlet valve are provided on the compression sleeve. A unidirectional piston is slidably mounted inside the compression sleeve. A transmission telescopic rod is further mounted on the unidirectional piston. The end of the transmission telescopic rod away from the unidirectional piston is in transmission connection with the movable end of the kinetic energy conversion device.

[0012] Preferably, the kinetic energy conversion device includes a mounting sleeve installed on the top of the compression sleeve. An inclined circulation groove is provided on the inner wall of the mounting sleeve. A rotating block is further installed inside the mounting sleeve. A guiding ball is mounted on the rotating block. The guiding ball is slidably connected along the inclined circulation groove. A second telescopic rod is mounted on the rotating block. A second rotating mounting shaft is rotatably mounted on the mounting sleeve. The second rotating mounting shaft is in limit sliding connection with the second telescopic rod. A limit clamping joint is provided at the top of the second rotating mounting shaft.

[0013] Preferably, a plurality of outer wall heat dissipation fitting blocks are installed outside the heat dissipation mounting shell. A plurality of inner wall heat dissipation fitting blocks are installed inside the heat dissipation mounting shell. A detachable limit clamping ring is sleeved outside the outer wall heat dissipation fitting block. A rotating exhaust pipe is installed at the bottom of the heat dissipation mounting shell. Guide vanes are provided on the rotating exhaust pipe.

[0014] Preferably, an arc-shaped windward surface is provided outside the outer wall heat dissipation fitting block. A pipeline distribution groove for installing the circulation pipeline is provided on the arc-shaped windward surface. A limit clamping edge is provided at the top of the outer wall heat dissipation fitting block. A first heat conduction pad is provided on the side of the outer wall heat dissipation fitting block away from the arc-shaped windward surface.

[0015] Preferably, a wavy heat dissipation fin is provided on one side of the inner wall heat dissipation bonding block, a flow pipe installation interlayer is provided inside the inner wall heat dissipation bonding block, and a second thermal conductive pad is provided on the side of the inner wall heat dissipation bonding block away from the wavy heat dissipation fin.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention achieves an efficient and uniform heat dissipation effect. The evenly distributed circulation pipes in the circulating temperature control device guide the circulation of the coolant. During the flow, the coolant can effectively absorb the heat generated by the hydrogen fuel cell and evenly diffuse it to all parts of the heat dissipation mounting shell, thereby avoiding the occurrence of local overheating. At the same time, the air guide device guides the airflow into the guide and heat dissipation chamber to air-cool the interior of the heat dissipation mounting shell, which cooperates with the coolant heat dissipation to form a dual heat dissipation mechanism. This multi-mode combined heat dissipation method can significantly improve the heat dissipation efficiency and ensure that the hydrogen fuel cell operates stably within an appropriate temperature range, thereby improving the performance and service life of the battery.

[0017] 2. The present invention has an adaptive heat dissipation adjustment function, which can automatically adjust the heat dissipation intensity according to the temperature of the hydrogen fuel cell and the flight status of the UAV. Under normal working conditions, the airflow generated by the UAV during flight enters the transmission guide head through the air guide device, drives the fan to rotate, and then drives the circulation conveying device to move, so as to realize the circulation of the coolant without consuming additional electric energy. When the temperature of the hydrogen fuel cell is too high or the UAV is moving at a low speed, start the fan motor to accelerate the airflow and the flow of coolant inside the guide heat dissipation chamber, further improving the cooling effect. This adaptive heat dissipation adjustment method can not only meet the heat dissipation requirements under different working conditions, but also minimize the additional power consumption and improve the endurance of the UAV.

[0018] 3. The heat dissipation mounting shell and the air guide device of the present invention are detachably connected, and the installation and removal process is simple and convenient. When it is necessary to install or replace the hydrogen fuel cell, it is only necessary to remove the heat dissipation mounting shell from the air guide device, put in or take out the hydrogen fuel cell, and then install the heat dissipation mounting shell back to its original position. This design not only facilitates the installation and maintenance of the hydrogen fuel cell, but also improves the reliability and maintainability of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a three-dimensional schematic diagram of a temperature control structure of a hydrogen fuel cell for an unmanned aerial vehicle according to the present invention.

[0020] Figure 2 It is a three-dimensional schematic diagram of a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle of the present invention in a disassembled state.

[0021] Figure 3It is the front view of a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0022] Figure 4 Is Figure 3 The plane cross-sectional view at the A-A section in

[0023] Figure 5 It is the front view of an air guiding device in a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0024] Figure 6 Is Figure 5 The plane cross-sectional perspective view at the B-B section in

[0025] Figure 7 It is the front view of a heat dissipation mounting shell in a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0026] Figure 8 Is Figure 7 The plane cross-sectional perspective view at the C-C section in

[0027] Figure 9 Is Figure 8 The partial enlarged view at D in

[0028] Figure 10 Is Figure 8 The partial enlarged view at E in

[0029] Figure 11 It is the three-dimensional schematic diagram of the outer wall heat dissipation fitting block in a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0030] Figure 12 It is the three-dimensional schematic diagram of the inner wall heat dissipation fitting block in a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0031] Figure 13 It is the front view of a circulation conveying device in a temperature control structure for a hydrogen fuel cell used in a drone of the present invention.

[0032] Figure 14 Is Figure 13 The plane cross-sectional view at the F-F section in

[0033] The reference numerals in the figure are: 1. Hydrogen fuel cell; 2. Air diversion device; 21. Unidirectional intake housing; 211. Spiral diversion groove; 212. Intake diversion hole; 213. Intake floating membrane; 22. Transmission diversion head; 221. Diversion sleeve; 222. Diffusion conical head; 223. First rotation mounting shaft; 224. First telescopic rod; 2241. Transmission docking head; 225. First spring; 23. Fan; 3. Circulation temperature control device; 31. Flow-through pipe; 311. Outer flow-through pipe; 312. Inner flow-through pipe; 32. Circulation conveying device; 321. Unidirectional compression assembly; 3211. Compression sleeve; 3212. Unidirectional liquid inlet valve; 3213. Unidirectional liquid outlet valve; 3214. Unidirectional piston; 3215. Unidirectional flow hole; 3216. Sealing film; 3217. Transmission telescopic rod; 322. Kinetic energy conversion device; 3221. Mounting sleeve; 3222. Inclined circulation groove; 3223. Rotating block; 3224. Guide ball; 3225. Second rotation mounting shaft; 3226. Second telescopic rod; 3227. Limit clamping joint; 4. Heat dissipation mounting shell; 41. Rotating exhaust pipe; 421. Guide vane; 42. Limit clamping ring; 43. Limit clamping mechanism; 431. Movable clamping block; 432. Second spring; 44. Outer wall heat dissipation fitting block; 441. Arc-shaped windward surface; 442. Limit clamping edge; 443. Pipeline distribution groove; 45. Inner wall heat dissipation fitting block; 451. Wavy heat dissipation fin; 46. Third spring. Detailed implementation mode

[0034] To further understand the features, technical means, specific purposes, and functions achieved by the present invention, the present invention will be described in further detail below in conjunction with the accompanying drawings and specific implementation modes.

[0035] See Figures 1 to 14 As shown in the figure, a temperature control structure for a hydrogen fuel cell used in a drone is installed outside the hydrogen fuel cell 1, and includes a heat dissipation mounting shell 4. A diversion heat dissipation chamber and a storage chamber are provided inside the heat dissipation mounting shell 4. The storage chamber is used for limiting and mounting the hydrogen fuel cell 1. A circulation temperature control device 3 is installed inside the heat dissipation mounting shell 4. The circulation temperature control device 3 includes flow-through pipes 31 evenly distributed inside the heat dissipation mounting shell 4. The flow-through pipes 31 are used to guide the coolant. A circulation conveying device 32 is installed on the flow-through pipes 31. An air diversion device 2 is installed on the top of the heat dissipation mounting shell 4. The air diversion device 2 includes a unidirectional intake housing 21 installed on the top of the heat dissipation mounting shell 4. The unidirectional intake housing 21 is used to guide air flow into the diversion heat dissipation chamber. A transmission diversion head 22 is installed at the bottom of the unidirectional intake housing 21. A fan 23 is installed on the transmission diversion head 22. The transmission diversion head 22 is in transmission connection with the circulation conveying device 32.

[0036] The circulation pipe 31 is used to guide the coolant. A circulation conveying device 32 is installed on the circulation pipe 31. The circulation conveying device 32 drives the coolant in the circulation pipe 31 to circulate. During the flow of the coolant, it can effectively absorb the heat generated by the hydrogen fuel cell 1 absorbed by the heat dissipation mounting shell 4, and evenly diffuse the heat to all parts of the heat dissipation mounting shell 4, so as to achieve uniform and effective cooling and heat dissipation without consuming additional electric energy. The air guide device 2 includes a one-way air intake shell 21 installed on the top of the heat dissipation mounting shell 4, and the one-way air intake shell 21 is used to guide the airflow to the air guide heat dissipation chamber. A transmission guide head 22 is installed at the bottom of the one-way air intake shell 21, and a fan 23 is installed on the transmission guide head 22.

[0037] The air guide device 2 is fixedly mounted on the bottom of the drone, and the heat dissipation mounting shell 4 is detachably connected to the air guide device 2. When the hydrogen fuel cell 1 needs to be installed, the heat dissipation mounting shell 4 is removed from the air guide device 2, and after multiple groups of hydrogen fuel cells 1 are placed in the storage chamber, the heat dissipation mounting shell 4 is installed to the bottom of the air guide device 2 to achieve stable wrapping and fixing of the hydrogen fuel cell 1.

[0038] When the UAV is flying, the hydrogen fuel cell 1 generates heat energy and transfers it to the heat dissipation mounting shell 4. The outer side of the heat dissipation mounting shell 4 is in contact with the flowing airflow, so that the outer wall is air-cooled. At the same time, the air guide device 2 guides the airflow into the transmission guide head 22, and the transmission guide head 22 diffuses and guides the external air to the guide and heat dissipation chamber of the heat dissipation mounting shell 4. The airflow passes through the guide and heat dissipation chamber to air-cool the inside of the heat dissipation mounting shell 4. When the airflow enters the transmission guide head 22, it passes through the fan 23. At this time, the fan 23 is not started and rotates due to the airflow. The rotation of the fan 23 drives the transmission guide head 22 to rotate, and the rotation of the transmission guide head 22 drives the circulating conveying device 32 to move synchronously, thereby realizing the circulation of the coolant, improving the cooling effect and ensuring the uniformity of heat dissipation.

[0039] When the temperature of the hydrogen fuel cell 1 is too high or the UAV is moving at a low speed, the motor of the fan 23 is started. After the motor of the fan 23 is started, the airflow inside the heat dissipation chamber is accelerated, and the movement of the circulation conveying device 32 is accelerated to accelerate the flow of the coolant, further improve the cooling effect, and achieve the cooling protection effect of adaptive switching adjustment.

[0040] Through the above principle, the temperature control structure of the hydrogen fuel cell 1 can effectively solve the problems of single heat dissipation method, poor heat dissipation effect and extra power consumption affecting battery life of traditional devices, and realize uniform and effective heat dissipation protection for the hydrogen fuel cell 1.

[0041] See also Figures 1 to 6 As shown, a spiral guide groove 211 is provided inside the one-way air intake housing 21 , and a plurality of air intake guide holes 212 are provided outside the one-way air intake housing 21 . An air intake floating membrane 213 is provided in each air intake guide hole 212 .

[0042] Inside the unidirectional air intake housing 21, there is a spiral guide groove 211, and on the outside, there are multiple air intake guide holes 212, and an air intake floating membrane 213 is provided in each air intake guide hole 212. When the drone is flying, the external air flow will flow towards the air intake guide holes 212 of the unidirectional air intake housing 21. At this time, under the action of the air flow pressure, the air intake floating membrane 213 will open, enabling the air flow to enter the inside of the unidirectional air intake housing 21 through the air intake guide holes 212. And due to the unidirectional opening characteristic of the air intake floating membrane 213, the air flow can only enter unidirectionally and cannot flow out reversely from the air intake guide holes 212, thus ensuring the air flow pressure entering the unidirectional air intake housing 21.

[0043] The air flow entering the unidirectional air intake housing 21 will form a vortex flow under the guidance of the spiral guide groove 211. The spiral guide groove 211 can make the air flow flow along a specific vortex path, and this vortex flow mode can effectively ensure the stability of the air flow. At the same time, the stable vortex flow of the air flow can provide stable air flow power for the transmission guide head 22 installed at the bottom of the unidirectional air intake housing 21 and the fan 23 on the transmission guide head 22, ensuring the stability of the rotation of the fan 23, and further realizing the diffusion and guidance of the external air to the air guide and heat dissipation chamber of the heat dissipation installation housing 4 to perform air cooling and heat dissipation on the inside of the heat dissipation installation housing 4.

[0044] See Figures 1 to 6 As shown, the transmission guide head 22 includes a guide sleeve 221 installed at the air outlet end of the unidirectional air intake housing 21. Inside the guide sleeve 221, there is a diffusion conical head 222. A first rotating mounting shaft 223 is rotatably mounted on the diffusion conical head 222. The first rotating mounting shaft 223 is connected to the fan 23. A first telescopic rod 224 is installed on the first rotating mounting shaft 223 in a limited sliding manner. A transmission docking head 2241 is installed on the first telescopic rod 224. A first spring 225 is installed between the transmission docking head 2241 and the first rotating mounting shaft 223.

[0045] The inside of the first rotating mounting shaft 223 is provided with a limit sliding groove, and the outside of the first telescopic rod 224 is provided with a limit block. When the first telescopic rod 224 is connected to the first rotating mounting shaft 223, the limit block will be slidably connected to the limit sliding groove to achieve limited sliding connection.

[0046] The flow guiding sleeve 221 is fixedly installed at the air outlet end of the unidirectional air intake housing 21, and is responsible for guiding the vortex air flow formed inside the unidirectional air intake housing 21 into the flow guiding and heat dissipation chamber. Inside the flow guiding sleeve 221, there is a diffusing conical head 222. The top of the diffusing conical head 222 is an inclined surface. When the air flow passes through the unidirectional air intake housing 21 and enters the flow guiding sleeve 221, the flowing air flow will first contact the inclined surface at the top of the diffusing conical head 222. Guided by the inclined surface, the air flow will diffuse and flow. The diffused air flow will flow downward from the gap between the flow guiding sleeve 221 and the diffusing conical head 222, so that the air flow entering the flow guiding and heat dissipation chamber can diffuse and flow evenly. The diffused air flow helps the air flow to better contact the inner wall of the flow guiding and heat dissipation chamber, thereby improving the air-cooling heat dissipation efficiency. The diffusing conical head 222 effectively prevents the flowing air flow from directly flowing through the middle of the flow guiding and heat dissipation chamber, resulting in the air flow being unable to effectively contact the inner wall of the flow guiding and heat dissipation chamber.

[0047] A first telescopic rod 224 is installed on the first rotating mounting shaft 223 in a limited sliding manner, and a transmission docking head 2241 is further installed on the first telescopic rod 224. A first spring 225 is installed between the transmission docking head 2241 and the first rotating mounting shaft 223. The first spring 225 provides a pre-tightening force to ensure that the transmission docking head 2241 is in an appropriate position in the initial state and has the ability to adaptively contract.

[0048] When the heat dissipation mounting shell 4 is fixedly connected to the air guiding device 2, the transmission air guiding head 22 is automatically inserted into the flow guiding and heat dissipation chamber of the heat dissipation mounting shell 4. During this process, the transmission docking head 2241 will attempt to perform transmission docking with the circulating conveying device 32. The transmission docking head 2241 is a block-shaped hexagon.

[0049] The cooperative design of the first telescopic rod 224 and the first spring 225 enables the transmission docking head 2241 to perform a stable adaptive contraction movement. It avoids equipment damage caused by forced docking when the transmission docking head 2241 fails to accurately dock to the specified position.

[0050] When the fan 23 starts to rotate, the first rotating mounting shaft 223 rotates accordingly, and then drives the first telescopic rod 224 and the transmission docking head 2241 to rotate synchronously. When the transmission docking head 2241 rotates to the specified position of the circulating conveying device 32, the pre-tightening force of the first spring 225 pushes the transmission docking head 2241 downward to achieve accurate docking with the circulating conveying device 32. Once the docking is completed, the continuous rotation of the fan 23 will drive the circulating conveying device 32 to work through the transmission docking head 2241, thereby driving the coolant to circulate in the circulation pipeline 31 to achieve the cooling and heat dissipation function.

[0051] See Figures 7 to 12As shown, the circulation pipeline 31 includes an outer circulation pipe 311 distributed on the outside of the heat dissipation installation shell 4, and the circulation pipeline 31 also includes an inner circulation pipe 312 distributed inside the heat dissipation installation shell 4. The outer circulation pipe 311 and the inner circulation pipe 312 are connected to each other, and the inner circulation pipe 312 is connected to the circulation conveying device 32.

[0052] The circulation pipeline 31 is arranged as a whole inside and outside the heat dissipation installation shell 4, and is specifically composed of an outer circulation pipe 311 distributed on the outside of the heat dissipation installation shell 4 and an inner circulation pipe 312 distributed inside the heat dissipation installation shell 4. The two are interconnected, and the inner circulation pipe 312 is directly connected to the circulation conveying device 32 to form a complete coolant circulation loop.

[0053] The outer flow pipe 311 is arranged in close contact with the outer wall of the heat dissipation mounting shell 4, making full use of the characteristics of the external flow airflow when the drone is flying. When the circulation conveying device 32 is started and drives the coolant circulation, the coolant forms a continuous flow between the outer flow pipe 311 and the inner flow pipe 312 under the action of power. In this process, the heat generated by the operation of the hydrogen fuel cell 1 is transferred to the inner flow pipe 312 via the heat dissipation mounting shell 4, and then transferred to the coolant circulating inside, so that the temperature of the coolant increases. The heated coolant is transported to the outer flow pipe 311 through the inner flow pipe 312. Since the outer flow pipe 311 is directly exposed to the external flow airflow environment, the flowing air and the surface of the outer flow pipe 311 undergo forced convection heat exchange. Through the heat conduction and convection heat exchange mechanism, the flowing air effectively reduces the temperature of the coolant in the outer flow pipe 311.

[0054] The cooled coolant is re-entered into the inner flow tube 312 at the end of the outer flow tube 311 to form a complete circulating liquid cooling path. During the circulation process, the coolant continuously absorbs the heat generated by the hydrogen fuel cell 1 and transfers it to the external air flow environment, achieving heat dissipation through gas-liquid heat exchange.

[0055] See also Figures 4 to 13 As shown, the circulating conveying device 32 includes a one-way compression component 321 installed on the diversion and heat dissipation chamber, the one-way compression component 321 is connected to the internal flow pipe 312, the one-way compression component 321 is used to drive the flow of coolant, and a kinetic energy conversion device 322 is also installed on the one-way compression component 321, and the kinetic energy conversion device 322 is connected to the transmission guide head 22.

[0056] When the drone is in flight, external airflow enters the air guiding device 2 through the unidirectional intake housing 21, and axial thrust is generated when the airflow passes through the transmission guiding head 22. Under the driving action of the airflow, the transmission guiding head 22 and the fan cooperate to generate a rotational motion, and the rotational motion is synchronously transmitted to the kinetic energy conversion device 322 through mechanical transmission. The kinetic energy conversion device 322 drives the unidirectional compression assembly 321 to move. During this process, the unidirectional compression assembly 321 drives the directional delivery of the coolant, causing the coolant to form a continuous circulating flow between the inner flow pipe 312 and the outer flow pipe 311.

[0057] See Figures 8 to 14 As shown, the unidirectional compression assembly 321 includes a compression sleeve 3211 installed in the guiding and heat dissipating chamber. A unidirectional liquid inlet valve 3212 and a unidirectional liquid outlet valve 3213 are provided on the compression sleeve 3211. A unidirectional piston 3214 is slidably installed inside the compression sleeve 3211. A transmission telescopic rod 3217 is also installed on the unidirectional piston 3214. The end of the transmission telescopic rod 3217 away from the unidirectional piston 3214 is in transmission connection with the movable end of the kinetic energy conversion device 322.

[0058] A unidirectional flow hole 3215 is provided on the unidirectional piston 3214, and a sealing film 3216 is also installed on the unidirectional piston 3214.

[0059] The kinetic energy conversion device 322 converts the rotational motion of the transmission guiding head 22 into a linear reciprocating motion, and pushes the unidirectional piston 3214 to move downward in the compression sleeve 3211 through the transmission telescopic rod 3217. When the unidirectional piston 3214 moves downward, the internal sealing film 3216 closely adheres to the unidirectional flow hole 3215 under hydraulic pressure, forming a dynamic seal to block the coolant from passing through the unidirectional flow hole 3215. The unidirectional liquid outlet valve 3213 at the lower part of the compression sleeve 3211 is communicated with the inner flow pipe 312. The volume reduction generated by the downward movement of the piston forces the coolant to be directionally discharged through the unidirectional liquid outlet valve 3213, forming a high-pressure fluid output. The unidirectional liquid inlet valve 3212 at the upper part of the compression sleeve 3211 is communicated with the inner flow pipe 312. Under the negative pressure generated by the downward movement of the piston, the coolant enters the inside of the compression sleeve 3211 through the unidirectional liquid inlet valve 3212. At this time, the coolant entering the compression sleeve 3211 is above the unidirectional piston 3214. When the transmission telescopic rod 3217 drives the unidirectional piston 3214 to move upward, the unidirectional piston 3214 will squeeze the coolant above. The coolant above cannot flow out through the unidirectional liquid inlet valve 3212. Therefore, when the coolant is squeezed, it will exert pressure on the unidirectional flow hole 3215. The sealing film 3216 will move downward and separate from the unidirectional flow hole 3215 under the influence of hydraulic pressure, allowing the coolant to flow through the unidirectional flow hole 3215 into the lower part of the unidirectional piston 3214, providing medium supplement for the next compression and completing the cycle preparation.

[0060] See Figures 8 to 14As shown in the figure, the kinetic energy conversion device 322 includes a mounting sleeve 3221 installed on the top of the compression sleeve 3211. The inner wall of the mounting sleeve 3221 is provided with an inclined circulating groove 3222. A rotating block 3223 is also installed inside the mounting sleeve 3221. A guiding ball 3224 is installed on the rotating block 3223. The guiding ball 3224 is slidably connected along the inclined circulating groove 3222. A second telescopic rod 3226 is installed on the rotating block 3223. A second rotating mounting shaft 3225 is rotatably installed on the mounting sleeve 3221. The second rotating mounting shaft 3225 is in limit sliding connection with the second telescopic rod 3226. A limit clamping joint 3227 is provided at the top of the second rotating mounting shaft 3225.

[0061] The limit clamping joint 3227 is provided with a hexagonal groove, which is used to dock with the transmission docking head 2241 to ensure the stability of transmission.

[0062] The limit sliding connection mode between the second rotating mounting shaft 3225 and the second telescopic rod 3226 is the same as the connection mode between the first rotating mounting shaft 223 and the first telescopic rod 224, so it will not be elaborated here. When the drone is in flight, the external air flow enters the air guiding device 2 through the one-way intake housing 21 and acts on the transmission guiding head 22 to generate a self-rotation motion. The rotational motion of the transmission guiding head 22 is transmitted to the second rotating mounting shaft 3225 in the kinetic energy conversion device 322.

[0063] The rotational motion of the second rotating mounting shaft 3225 drives the second telescopic rod 3226 to rotate synchronously. A rotating block 3223 is installed on the second telescopic rod 3226. A guiding ball 3224 is provided on the rotating block 3223. The guiding ball 3224 is in sliding fit with the inclined circulating groove 3222 on the inner wall of the mounting sleeve 3221. When the second telescopic rod 3226 rotates, the rotating block 3223 generates a lifting motion under the interaction between the guiding ball 3224 and the inclined circulating groove 3222. Specifically, the guiding ball 3224 moves along the trajectory of the inclined circulating groove 3222, causing the rotating block 3223 to achieve displacement in the up and down directions while rotating.

[0064] The rotating block 3223 is rotatably connected to the transmission telescopic rod 3217. The lifting motion of the rotating block 3223 is transmitted to the transmission telescopic rod 3217 through the second telescopic rod 3226. Since the second telescopic rod 3226 is mechanically connected to the rotating block 3223 and the transmission telescopic rod 3217, the up and down displacement of the rotating block 3223 directly drives the transmission telescopic rod 3217 to perform synchronous linear reciprocating motion. The linear reciprocating motion of the transmission telescopic rod 3217 further acts on the one-way piston 3214 in the one-way compression assembly 321. Through the above process, the kinetic energy conversion device 322 realizes the conversion of the rotational motion of the transmission guiding head 22 into a linear reciprocating motion and uses the reciprocating motion to drive the one-way compression assembly 321.

[0065] See Figures 7 to 10 As shown, a plurality of outer wall heat dissipation fitting blocks 44 are installed on the outer side of the heat dissipation installation shell 4, and a plurality of inner wall heat dissipation fitting blocks 45 are installed on the inner side of the heat dissipation installation shell 4. A detachable limit clamping ring 42 is sleeved on the outer side of the outer wall heat dissipation fitting block 44. A rotating exhaust pipe 41 is installed at the bottom of the heat dissipation installation shell 4, and guide vanes 421 are provided on the rotating exhaust pipe 41.

[0066] A plurality of limit clamping mechanisms 43 are installed on the outer side of the heat dissipation installation shell 4. The limit clamping mechanism 43 includes a plurality of movable clamping blocks 431 slidably installed on the heat dissipation installation shell 4. A second spring 432 is installed between each movable clamping block 431 and the heat dissipation installation shell 4. The second spring 432 is used to push the movable clamping block 431 so that the movable clamping block 431 can move elastically. The movable clamping block 431 is used to clamp and fix the limit clamping ring 42 to ensure the stability of the installation of the limit clamping ring 42.

[0067] The gap between the inner wall heat dissipation fitting block 45 and the outer wall heat dissipation fitting block 44 of the heat dissipation installation shell 4 forms a storage chamber. Both the inner wall heat dissipation fitting block 45 and the outer wall heat dissipation fitting block 44 are in direct contact with the outer wall of the hydrogen fuel cell 1 to realize the limitation and heat conduction of the hydrogen fuel cell 1. A third spring 46 is provided between the inner wall heat dissipation fitting block 45 and the heat dissipation installation shell 4.

[0068] When the hydrogen fuel cell 1 is in a working state, the generated heat is conducted to the inner wall heat dissipation fitting block 45 and the outer wall heat dissipation fitting block 44. During the flight of the drone, the outer wall heat dissipation fitting block 44 is directly exposed to the external air flow to realize natural convection heat dissipation. At the same time, the air guiding device 2 guides the air flow into the transmission guiding head 22 through the one-way intake housing 21. The air flow passes through the fan 23 and then enters the guiding heat dissipation chamber to perform air-cooled heat dissipation on the inner wall heat dissipation fitting block 45 inside the heat dissipation installation shell 4. Subsequently, the air flow passes through the guiding heat dissipation chamber and enters the rotating exhaust pipe 41. The rotating exhaust pipe 41 will discharge the air flow. The guide vanes 421 will be affected by the external air flow to automatically adjust the rotating exhaust to the downwind position, so that the air outlet of the rotating exhaust pipe 41 remains in the downwind state to avoid air flow backflow. During this process, the inner wall heat dissipation fitting block 45 and the outer wall heat dissipation fitting block 44 are continuously in contact with the external air flow, effectively increasing the heat dissipation area and improving the heat dissipation efficiency.

[0069] Both the outer wall heat dissipation fitting block 44 and the inner wall heat dissipation fitting block 45 are slidably connected to the heat dissipation installation shell 4.

[0070] When the heat dissipation mounting shell 4 is installed together with the air guiding device 2, the driving guiding head 22 of the air guiding device 2 will press against the inner wall heat dissipation fitting block 45, causing the inner wall heat dissipation fitting block 45 to remain in contact with the hydrogen fuel cell 1. At this time, the third spring 46 will be compressed. Meanwhile, through the installation of the limit retaining ring 42, the outer wall heat dissipation fitting block 44 remains in contact with the hydrogen fuel cell 1.

[0071] The heat dissipation mounting shell 4 is detachably connected to the air guiding device 2, facilitating the installation and replacement of the hydrogen fuel cell 1. When replacing the hydrogen fuel cell 1, the heat dissipation mounting shell 4 and the air guiding device 2 are disassembled and separated. Then the third spring 46 will release pressure, and the third spring 46 pushes the inner wall heat dissipation fitting block 45 to reset, releasing the contact with the hydrogen fuel cell 1. Subsequently, the limit retaining ring 42 is removed. At this time, the outer wall heat dissipation fitting block 44 can be adjusted and detached from the hydrogen fuel cell 1. Thus, the hydrogen fuel cell 1 can be removed.

[0072] See Figures 7 to 11 As shown, an arc-shaped windward surface 441 is provided on the outer side of the outer wall heat dissipation fitting block 44. A pipe distribution groove 443 for installing the flow-through pipe 31 is provided on the arc-shaped windward surface 441. A limit retaining edge 442 is provided at the top of the outer wall heat dissipation fitting block 44. A first heat conducting pad is provided on the side of the outer wall heat dissipation fitting block 44 away from the arc-shaped windward surface 441.

[0073] The pipe distribution groove 443 on the arc-shaped windward surface 441 is used to install the outer flow-through pipe 311 of the flow-through pipe 31.

[0074] The outer wall heat dissipation fitting block 44 is in direct contact with the outer wall of the hydrogen fuel cell 1. The heat conducting effect is enhanced through the first heat conducting pad, and the heat generated during the operation of the hydrogen fuel cell 1 is conducted to itself.

[0075] The outer wall heat dissipation fitting block 44 is provided with an arc-shaped windward surface 441, which can effectively ensure the contact area with the flowing air and maintain the smooth fluidity of the air flow. During the flight of the drone, the outer wall heat dissipation fitting block 44 is directly exposed to the external air flow. The arc-shaped windward surface 441 contacts the air flow to achieve natural convection heat dissipation, and the heat conducted to itself is dissipated to the external environment.

[0076] A limit retaining edge 442 is provided at the top of the outer wall heat dissipation fitting block 44. The limit retaining ring 42 can be sleeved on the limit retaining edge 442. By sleeving the limit retaining ring 42, the positions of multiple outer wall heat dissipation fitting blocks 44 can be effectively limited. The stability of the installation of the limit retaining ring 42 is ensured through the limit clamping mechanism 43, thereby guaranteeing the stability of the installation of the outer wall heat dissipation fitting block 44 on the heat dissipation mounting shell 4. When disassembling the hydrogen fuel cell 1, the position of the outer wall heat dissipation fitting block 44 needs to be adjusted. At this time, the limit retaining ring 42 is removed from the limit retaining edge 442 to adjust the position of the outer wall heat dissipation fitting block 44. See Figures 7 to 12As shown, a wave heat dissipation fin 451 is provided on one side of the inner wall heat dissipation bonding block 45, an installation interlayer for installing the flow pipe 31 is provided inside the inner wall heat dissipation bonding block 45, and a second thermal conductive pad is provided on the side of the inner wall heat dissipation bonding block 45 away from the wave heat dissipation fin 451.

[0077] The inner wall heat dissipation bonding block 45 is in direct contact with the outer wall of the hydrogen fuel cell 1 through the second thermal pad. The second thermal pad is made of a material with high thermal conductivity, which can quickly and stably transfer the heat generated during the operation of the hydrogen fuel cell 1 to the inner wall heat dissipation bonding block 45 body. A wave heat dissipation fin 451 is provided on one side of the inner wall heat dissipation bonding block 45. When the hydrogen fuel cell 1 is in operation, the air guide device 2 guides the airflow into the transmission guide head 22 through the one-way air intake shell 21, and the airflow passes through the fan 23 and enters the diversion and heat dissipation chamber. In the diversion and heat dissipation chamber, the airflow is in full contact with the wave heat dissipation fin 451. The wave heat dissipation fin 451 increases the contact area with the airflow, destroys the airflow boundary layer, and promotes the transfer of heat, thereby realizing effective air cooling and heat dissipation of the inner wall heat dissipation bonding block 45. An installation interlayer is provided inside the inner wall heat dissipation bonding block 45, and the installation interlayer is used to install the inner flow pipe 312 of the flow pipe 31. The inner circulation tube 312 can circulate cooling medium. When the cooling medium flows in the inner circulation tube 312, it absorbs the heat of the inner wall heat dissipation bonding block 45, further enhancing the heat dissipation capacity of the inner wall heat dissipation bonding block 45, and realizing internal circulation heat dissipation.

[0078] Specific working principle: The circulation pipe 31 is used to guide the coolant. A circulation conveying device 32 is installed on the circulation pipe 31. The circulation conveying device 32 drives the coolant in the circulation pipe 31 to circulate. During the flow of the coolant, it can effectively absorb the heat generated by the hydrogen fuel cell 1 absorbed by the heat dissipation mounting shell 4, and evenly diffuse the heat to all parts of the heat dissipation mounting shell 4, so as to achieve uniform and effective cooling and heat dissipation without consuming additional electric energy. The air guide device 2 includes a one-way air intake shell 21 installed on the top of the heat dissipation mounting shell 4, and the one-way air intake shell 21 is used to guide the airflow to the air guide heat dissipation chamber. A transmission guide head 22 is installed at the bottom of the one-way air intake shell 21, and a fan 23 is installed on the transmission guide head 22.

[0079] The air guide device 2 is fixedly mounted on the bottom of the drone, and the heat dissipation mounting shell 4 is detachably connected to the air guide device 2. When the hydrogen fuel cell 1 needs to be installed, the heat dissipation mounting shell 4 is removed from the air guide device 2, and after multiple groups of hydrogen fuel cells 1 are placed in the storage chamber, the heat dissipation mounting shell 4 is installed to the bottom of the air guide device 2 to achieve stable wrapping and fixing of the hydrogen fuel cell 1.

[0080] When the drone is flying, the hydrogen fuel cell 1 generates heat energy and transfers it to the heat dissipation mounting shell 4. The outer side of the heat dissipation mounting shell 4 is in contact with the flowing air current to achieve air cooling of the outer wall. At the same time, the air guiding device 2 guides the air current into the transmission guiding head 22, and the transmission guiding head 22 diffuses and guides the external air to the guiding heat dissipation chamber of the heat dissipation mounting shell 4. The air current passes through the guiding heat dissipation chamber to conduct air cooling inside the heat dissipation mounting shell 4. When the air current enters the transmission guiding head 22, it will pass through the fan 23. At this time, the fan 23 is not started and rotates automatically under the influence of the air current. The self-rotation of the fan 23 drives the transmission guiding head 22 to rotate, and the rotation of the transmission guiding head 22 drives the circulating conveying device 32 to move synchronously, thereby realizing the circulating flow of the coolant, improving the cooling effect and ensuring the uniformity of heat dissipation.

[0081] When the temperature of the hydrogen fuel cell 1 is too high or the moving flight speed of the drone is relatively low, the motor of the fan 23 is started. After the motor of the fan 23 is started, it accelerates the air current inside the guiding heat dissipation chamber and at the same time accelerates the movement of the circulating conveying device 32, so that the coolant flows faster, further improving the cooling effect and realizing the cooling protection effect of adaptive switching regulation.

[0082] Through the above principle, the temperature control structure of the hydrogen fuel cell 1 can effectively solve the problems of single heat dissipation method, poor heat dissipation effect and additional power consumption affecting endurance of the traditional device, and realize uniform and effective heat dissipation protection for the hydrogen fuel cell 1.

[0083] The above embodiments only represent one or several implementation manners of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the protection scope of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. A hydrogen fuel cell temperature control structure for an unmanned aerial vehicle, installed on the outside of a hydrogen fuel cell (1), characterized in that: The heat dissipation installation shell (4) is provided with a heat dissipation chamber and a storage chamber inside the heat dissipation installation shell (4), the storage chamber is used for limiting the installation of a hydrogen fuel cell (1), a circulating temperature control device (3) is installed inside the heat dissipation installation shell (4), the circulating temperature control device (3) comprises a circulation pipeline (31) evenly distributed inside the heat dissipation installation shell (4), the circulation pipeline (31) is used to guide a coolant, a circulating conveying device (32) is installed on the circulation pipeline (31), an air guide device (2) is installed on the top of the heat dissipation installation shell (4), the air guide device (2) comprises a one-way air inlet shell (21) installed on the top of the heat dissipation installation shell (4), the one-way air inlet shell (21) is used to guide airflow to the heat dissipation chamber, a transmission guide head (22) is installed at the bottom of the one-way air inlet shell (21), a fan (23) is installed on the transmission guide head (22), and the transmission guide head (22) is connected to the circulating conveying device (32) in a transmission manner; The circulation conveying device (32) comprises a one-way compression component (321) installed in the diversion and heat dissipation chamber, the one-way compression component (321) is connected to the circulation pipeline (31), the one-way compression component (321) is used to drive the flow of coolant, and a kinetic energy conversion device (322) is also installed on the one-way compression component (321), and the kinetic energy conversion device (322) is in transmission connection with the transmission diversion head (22).

2. The hydrogen fuel cell temperature control structure for drone according to claim 1, characterized in that: A spiral guide groove (211) is provided inside the one-way air intake housing (21), a plurality of air intake guide holes (212) are provided outside the one-way air intake housing (21), and an air intake floating membrane (213) is provided in each air intake guide hole (212).

3. The hydrogen fuel cell temperature control structure for drone according to claim 2, characterized in that: The transmission guide head (22) comprises a guide sleeve (221) mounted at the air outlet end of the one-way air inlet housing (21); a diffusion cone head (222) is provided inside the guide sleeve (221); a first rotation installation shaft (223) is rotatably mounted on the diffusion cone head (222); the first rotation installation shaft (223) is connected to the fan (23); a first telescopic rod (224) is slidably mounted on the upper limit position of the first rotation installation shaft (223); a transmission butt joint (2241) is mounted on the first telescopic rod (224); and a first spring (225) is mounted between the transmission butt joint (2241) and the first rotation installation shaft (223).

4. The hydrogen fuel cell temperature control structure for drone according to claim 1, characterized in that: The circulation pipeline (31) comprises an outer circulation pipe (311) distributed outside the heat dissipation installation shell (4), and the circulation pipeline (31) further comprises an inner circulation pipe (312) distributed inside the heat dissipation installation shell (4), the outer circulation pipe (311) and the inner circulation pipe (312) are connected to each other, and the inner circulation pipe (312) is connected to the circulation conveying device (32).

5. The hydrogen fuel cell temperature control structure for drone according to claim 1, characterized in that: The one-way compression assembly (321) comprises a compression sleeve (3211) installed in the diversion and heat dissipation chamber, the compression sleeve (3211) is provided with a one-way liquid inlet valve (3212) and a one-way liquid outlet valve (3213), a one-way piston (3214) is slidably installed inside the compression sleeve (3211), a transmission telescopic rod (3217) is also installed on the one-way piston (3214), and one end of the transmission telescopic rod (3217) away from the one-way piston (3214) is transmission-connected to the movable end of the kinetic energy conversion device (322).

6. The hydrogen fuel cell temperature control structure for drone according to claim 5, characterized in that: The kinetic energy conversion device (322) comprises a mounting sleeve (3221) mounted on the top of the compression sleeve (3211); the inner wall of the mounting sleeve (3221) is provided with an inclined circulation groove (3222); a rotating block (3223) is also mounted inside the mounting sleeve (3221); a guide ball (3224) is mounted on the rotating block (3223); the guide ball (3224) is slidably connected along the inclined circulation groove (3222); a second telescopic rod (3226) is mounted on the rotating block (3223); a second rotating mounting shaft (3225) is also rotatably mounted on the mounting sleeve (3221); the second rotating mounting shaft (3225) is slidably connected to the second telescopic rod (3226); a limiting clamping joint (3227) is provided on the top of the second rotating mounting shaft (3225).

7. The hydrogen fuel cell temperature control structure for drone according to claim 1, characterized in that: A plurality of outer wall heat dissipation fitting blocks (44) are mounted on the outer side of the heat dissipation mounting shell (4), a plurality of inner wall heat dissipation fitting blocks (45) are mounted on the inner side of the heat dissipation mounting shell (4), a detachable limit clamping ring (42) is sleeved on the outer side of the outer wall heat dissipation fitting block (44), a rotating exhaust pipe (41) is mounted on the bottom of the heat dissipation mounting shell (4), and a guide blade (421) is provided on the rotating exhaust pipe (41).

8. The hydrogen fuel cell temperature control structure for drone according to claim 7, characterized in that: An arc-shaped windward surface (441) is provided on the outer side of the outer wall heat dissipation fitting block (44); a pipe distribution groove (443) for installing a circulation pipe (31) is provided on the arc-shaped windward surface (441); a limiting clamping edge (442) is provided on the top of the outer wall heat dissipation fitting block (44); and a first heat conductive pad is provided on the side of the outer wall heat dissipation fitting block (44) away from the arc-shaped windward surface (441).

9. The hydrogen fuel cell temperature control structure for drone according to claim 7, characterized in that: A wave heat dissipation fin (451) is provided on one side of the inner wall heat dissipation fitting block (45), an installation interlayer for installing a circulation pipe (31) is provided inside the inner wall heat dissipation fitting block (45), and a second heat conduction pad is provided on the side of the inner wall heat dissipation fitting block (45) away from the wave heat dissipation fin (451).

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