A hydrogen fuel cell temperature control structure for drones

Abstract

The present invention relates to the field of hydrogen fuel cell technology, and specifically to a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle (UAV), comprising a heat dissipation mounting shell, wherein a guide heat dissipation chamber and a storage chamber are provided inside the heat dissipation mounting shell, the storage chamber is used for limiting the installation of the hydrogen fuel cell, and a circulation temperature control device is installed inside the heat dissipation mounting shell. The circulation temperature control device comprises a circulation pipe evenly distributed inside the heat dissipation mounting shell, the circulation pipe is used for guiding coolant, a circulation conveying device is installed on the circulation pipe, an air guide device is installed on the top of the heat dissipation mounting shell, the air guide device comprises a one-way air inlet shell installed on the top of the heat dissipation mounting shell, the one-way air inlet shell is used for guiding airflow to the guide heat dissipation chamber, a transmission guide head is installed at the bottom of the one-way air inlet shell, a fan is installed on the transmission guide head, and the transmission guide head is transmission-connected to the circulation conveying device. The present invention can effectively improve the heat dissipation efficiency, while reducing additional power consumption and improving the endurance of the UAV.

Description

Technical Field

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

[0002] The working principle of hydrogen fuel cells is to convert the chemical energy of hydrogen and oxygen into electrical energy through an electrochemical reaction. In drones, this electrical energy is used to drive the electric motor, which in turn drives the propeller to rotate and achieve the flight of the drone.

[0003] Chinese patent number CN115425252A discloses a hydrogen-powered fuel cell structure for unmanned aerial vehicles, which includes a battery housing, a fuel cell stack, and an air drive component. The battery housing is provided with an air groove, and the fuel cell stack is adapted to the air groove so that all air flowing into the battery housing flows into the fuel cell stack through the air groove, thereby improving the reaction efficiency of the fuel cell stack. The air drive component is installed on the battery housing, and the air after the reaction of the fuel cell stack is discharged out of the battery housing through the air drive component. 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-mentioned device can achieve heat dissipation protection through multiple air-driven components, when the air-driven components continue to drive heat dissipation, they need to continuously consume additional electrical energy, resulting in additional power consumption, which will affect battery life. In addition, the heat dissipation method of the 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] To address the above problems, a hydrogen fuel cell temperature control structure for drones is provided. The temperature control structure can effectively improve the heat dissipation efficiency, reduce additional power consumption, and improve the endurance of the drone.

[0006] In order to solve the problems of the prior art, the present invention provides a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle, which is installed on the outside of the hydrogen fuel cell and includes a heat dissipation mounting shell. The interior of the heat dissipation mounting shell is provided with a guide heat dissipation chamber and a storage chamber. The storage chamber is used to limit the installation of the hydrogen fuel cell. A circulation temperature control device is installed inside the heat dissipation mounting shell. The circulation temperature control device includes circulation pipes evenly distributed inside the heat dissipation mounting shell. The circulation pipes are used to guide coolant. A circulation conveying device is installed on the circulation pipes. An air guide device is installed on the top of the heat dissipation mounting shell. The air guide device includes a one-way air inlet shell installed on the top of the heat dissipation mounting shell. The one-way air inlet shell is used to guide airflow to the guide heat dissipation chamber. A transmission guide head is installed at the bottom of the one-way air inlet shell. A fan is installed on the transmission guide head. The transmission guide head is transmission-connected to the circulation conveying device.

[0007] Preferably, a spiral guide groove is provided inside the one-way air inlet housing, a plurality of air inlet guide holes are provided on the outside of the one-way air inlet housing, and an air inlet floating membrane is provided in each air inlet guide hole.

[0008] Preferably, the transmission guide head includes a guide sleeve installed at the air outlet end of the one-way air inlet housing, a diffusion cone head is provided inside the guide sleeve, a first rotating mounting shaft is rotatably installed on the diffusion cone head, the first rotating mounting shaft is connected to the fan, a first telescopic rod is slidably installed on the upper limit of the first rotating mounting shaft, a transmission docking joint is installed on the first telescopic rod, and a first spring is installed between the transmission docking joint and the first rotating mounting shaft.

[0009] Preferably, the flow pipe includes an outer flow pipe distributed outside the heat dissipation installation shell, and the flow pipe also includes an inner flow pipe distributed inside the heat dissipation installation shell. The outer flow pipe and the inner flow pipe are connected to each other, and the inner flow pipe is connected to the circulation conveying device.

[0010] Preferably, the circulating conveying device includes a one-way compression component installed on the diversion and heat dissipation chamber, the one-way compression component is connected to the internal flow pipe, the one-way compression component is used to drive the flow of coolant, and a kinetic energy conversion device is also installed on the one-way compression component, which is connected to the transmission diversion head.

[0011] Preferably, the one-way compression assembly includes a compression sleeve installed in the diversion and heat dissipation chamber, the compression sleeve is provided with a one-way liquid inlet valve and a one-way liquid outlet valve, a one-way piston is slidably installed inside the compression sleeve, and a transmission telescopic rod is also installed on the one-way piston, and the end of the transmission telescopic rod away from the one-way piston is transmission-connected to 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, the inner wall of the mounting sleeve is provided with an inclined circulation groove, a rotating block is also installed inside the mounting sleeve, a guide ball is installed on the rotating block, the guide ball is slidably connected along the inclined circulation groove, a second telescopic rod is installed on the rotating block, and a second rotating mounting shaft is also rotatably installed on the mounting sleeve, the second rotating mounting shaft is limitedly slidably connected to the second telescopic rod, and a limiting card joint is provided on the top of the second rotating mounting shaft.

[0013] Preferably, a plurality of outer wall heat dissipation fitting blocks are installed on the outer side of the heat dissipation mounting shell, a plurality of inner wall heat dissipation fitting blocks are installed on the inner side of the heat dissipation mounting shell, a removable limiting clamp is provided on the outer side of the outer wall heat dissipation fitting block, a rotating exhaust pipe is installed on the bottom of the heat dissipation mounting shell, and a guide blade is provided on the rotating exhaust pipe.

[0014] Preferably, the outer side of the outer wall heat dissipation fitting block is provided with an arc-shaped windward surface, the arc-shaped windward surface is provided with a pipe distribution groove for installing the circulation pipe, the top of the outer wall heat dissipation fitting block is provided with a limiting edge, and the side of the outer wall heat dissipation fitting block away from the arc-shaped windward surface is provided with a first thermal pad.

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

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 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, avoiding the occurrence of local overheating. At the same time, the air guide device guides the airflow into the guide heat dissipation chamber to air-cool the interior of the heat dissipation mounting shell, and cooperates with the coolant heat dissipation to form a dual heat dissipation mechanism. This multi-mode heat dissipation method can significantly improve the heat dissipation efficiency, ensure the stable operation of the hydrogen fuel cell within the appropriate temperature range, and thus improve the performance and service life of the battery.

[0018] 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, realizing the circulation of the coolant without the need for additional power consumption. When the temperature of the hydrogen fuel cell is too high or the UAV is moving at a low speed, the fan motor is started to accelerate the airflow and the flow of coolant inside the diversion heat dissipation chamber, further improving the cooling effect. This adaptive heat dissipation adjustment method can not only meet the heat dissipation needs under different working conditions, but also minimize additional power consumption and improve the endurance of the UAV.

[0019] 3. The heat sink housing and air guide device of the present invention are detachably connected, making installation and removal simple and convenient. To install or replace a hydrogen fuel cell, the heat sink housing is simply removed from the air guide device, the fuel cell is inserted or removed, and the heat sink housing is then reinstalled. This design not only facilitates installation and maintenance of the hydrogen fuel cell but also improves the reliability and maintainability of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a three-dimensional schematic diagram of a hydrogen fuel cell temperature control structure for a drone of the present invention.

[0021] Figure 2 It is a three-dimensional schematic diagram of a hydrogen fuel cell temperature control structure for a drone of the present invention in a disassembled state.

[0022] Figure 3 This is a front view of a hydrogen fuel cell temperature control structure for a drone according to the present invention.

[0023] Figure 4 yes Figure 3 Plane sectional view at section AA.

[0024] Figure 5 This is a front view of an air guide device in a hydrogen fuel cell temperature control structure for a drone according to the present invention.

[0025] Figure 6 yes Figure 5 A three-dimensional plan view of the BB section.

[0026] Figure 7 This is a front view of a heat dissipation mounting shell in a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle according to the present invention.

[0027] Figure 8 yes Figure 7 Plane cutaway perspective view at the CC section.

[0028] Figure 9 yes Figure 8 A partial enlarged view of point D in the middle.

[0029] Figure 10 yes Figure 8 A partial enlarged view of point E in the middle.

[0030] Figure 11 It is a three-dimensional schematic diagram of an outer wall heat dissipation bonding block in a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle according to the present invention.

[0031] Figure 12 It is a three-dimensional schematic diagram of an inner wall heat dissipation bonding block in a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle according to the present invention.

[0032] Figure 13 This is a front view of a circulating conveying device in a temperature control structure of a hydrogen fuel cell for an unmanned aerial vehicle according to the present invention.

[0033] Figure 14 yes Figure 13 Plane sectional view at the FF section.

[0034] The numbers in the figure are:

[0035] 1. Hydrogen fuel cell; 2. Air guide device; 21. One-way air intake housing; 211. Spiral guide groove; 212. Air intake guide hole; 213. Air intake floating membrane; 22. Transmission guide head; 221. Guide sleeve; 222. Diffusion cone head; 223. First rotating mounting shaft; 224. First telescopic rod; 2241. Transmission docking joint; 225. First spring; 23. Fan; 3. Circulation temperature control device; 31. Circulation pipe; 311. External circulation pipe; 312. Internal circulation pipe; 32. Circulation conveying device; 321. One-way compression assembly; 3211. Compression sleeve; 3212. One-way liquid inlet valve; 3213. One-way liquid outlet valve; 3214. One-way piston; 3215. One-way circulation 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 rotating mounting shaft; 3226, second telescopic rod; 3227, limit clamp joint; 4, heat dissipation mounting shell; 41, rotating exhaust pipe; 421, guide blade; 42, limit clamp ring; 43, limit clamping mechanism; 431, movable clamping block; 432, second spring; 44, outer wall heat dissipation fitting block; 441, curved windward surface; 442, limit clamp edge; 443, pipeline distribution groove; 45, inner wall heat dissipation fitting block; 451, wave heat dissipation fin; 46, third spring. DETAILED DESCRIPTION

[0036] In order to further understand the features, technical means, specific objectives and functions achieved by the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] See also Figures 1 to 14 As shown, a hydrogen fuel cell temperature control structure for an unmanned aerial vehicle is installed on the outside of a hydrogen fuel cell 1, including a heat dissipation mounting shell 4, the interior of the heat dissipation mounting shell 4 is provided with a guide heat dissipation chamber and a storage chamber, the storage chamber is used to limit the installation of the hydrogen fuel cell 1, and the interior of the heat dissipation mounting shell 4 is provided with a circulation temperature control device 3, the circulation temperature control device 3 includes a circulation pipe 31 evenly distributed inside the heat dissipation mounting shell 4, the circulation pipe 31 is used to guide the coolant, and a circulation conveying device 32 is installed on the circulation pipe 31, and an air guide device 2 is installed on the top of the heat dissipation mounting shell 4. The air guide device 2 includes a one-way air inlet shell 21 installed on the top of the heat dissipation mounting shell 4, the one-way air inlet shell 21 is used to guide the airflow to the guide heat dissipation chamber, and a transmission guide head 22 is installed at the bottom of the one-way air inlet shell 21, and a fan 23 is installed on the transmission guide head 22, and the transmission guide head 22 is transmission-connected to the circulation conveying device 32.

[0038] The circulation pipe 31 is used to guide the coolant. A circulating conveying device 32 is installed on the circulation pipe 31. The circulating 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, achieving uniform and effective cooling and heat dissipation without consuming additional electrical energy. The air guide device 2 includes a one-way air inlet shell 21 installed on the top of the heat dissipation mounting shell 4, and the one-way air inlet shell 21 is used to guide the airflow to the guide heat dissipation chamber. A transmission guide head 22 is installed at the bottom of the one-way air inlet shell 21, and a fan 23 is installed on the transmission guide head 22.

[0039] The air guide device 2 is fixedly mounted on the bottom of the drone, and the heat sink mounting shell 4 is detachably connected to the air guide device 2. When the hydrogen fuel cell 1 needs to be installed, the heat sink mounting shell 4 is removed from the air guide device 2, multiple hydrogen fuel cells 1 are placed into the storage chamber, and then the heat sink mounting shell 4 is mounted to the bottom of the air guide device 2 to ensure stable encapsulation and fixation of the hydrogen fuel cell 1.

[0040] 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, realizing air cooling of the outer wall. At the same time, the air guide device 2 guides the airflow into the transmission guide head 22. 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 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 influence of the airflow. The rotation of the fan 23 drives the transmission guide head 22 to rotate. 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.

[0041] When the temperature of the hydrogen fuel cell 1 is too high or the drone is moving at a low speed, the motor of the fan 23 is started. After the motor of the fan 23 is started, it accelerates the airflow inside the heat dissipation chamber and accelerates the movement of the circulation conveying device 32, so that the coolant flows faster, further improving the cooling effect and achieving the cooling protection effect of adaptive switching adjustment.

[0042] Through the above principle, the temperature control structure of the hydrogen fuel cell 1 can effectively solve the problems of single heat dissipation mode, 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.

[0043] 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 on the outside of the one-way air intake housing 21 . An air intake floating membrane 213 is provided in each air intake guide hole 212 .

[0044] The one-way air inlet housing 21 is internally provided with a spiral guide groove 211 and externally provided with multiple air inlet guide holes 212. Each air inlet guide hole 212 is equipped with an air inlet floating membrane 213. When the drone is in flight, external air flows into the air inlet guide holes 212 of the one-way air inlet housing 21. At this point, the air inlet guide holes 212 are subjected to air pressure, causing the air inlet floating membrane 213 to open, allowing air to enter the one-way air inlet housing 21 through the air inlet guide holes 212. Furthermore, due to the one-way opening of the air inlet floating membrane 213, air can only enter in one direction and cannot flow out of the air inlet guide holes 212 in the opposite direction, thus ensuring the air pressure entering the one-way air inlet housing 21.

[0045] Airflow entering the one-way air intake housing 21 forms a vortex flow under the guidance of the spiral guide groove 211. The spiral guide groove 211 allows the airflow to flow along a specific vortex path, effectively ensuring the stability of the airflow. Furthermore, the stable vortex flow provides stable airflow power for the transmission guide head 22 mounted at the bottom of the one-way air intake housing 21 and the fan 23 mounted thereon, ensuring the stability of the fan 23's rotation. This in turn diffuses and guides external air into the heat dissipation chamber of the heat dissipation mounting housing 4, providing air cooling and heat dissipation within the heat dissipation mounting housing 4.

[0046] See also Figures 1 to 6 As shown, the transmission guide head 22 includes a guide sleeve 221 installed at the air outlet end of the one-way air inlet housing 21, and a diffusion cone head 222 is provided inside the guide sleeve 221. A first rotating mounting shaft 223 is rotatably mounted on the diffusion cone head 222, and the first rotating mounting shaft 223 is connected to the fan 23. A first telescopic rod 224 is slidably mounted on the upper limit of the first rotating mounting shaft 223, and a transmission docking joint 2241 is installed on the first telescopic rod 224. A first spring 225 is installed between the transmission docking joint 2241 and the first rotating mounting shaft 223.

[0047] A limiting slot is provided inside the first rotating mounting shaft 223 , and a limiting block is provided on the outside of the first telescopic rod 224 . When the first telescopic rod 224 is connected to the first rotating mounting shaft 223 , the limiting block will be slidably connected to the limiting slot to achieve a limited sliding connection.

[0048] The guide sleeve 221 is fixedly installed at the air outlet end of the one-way air inlet housing 21, and is responsible for guiding the vortex airflow formed inside the one-way air inlet housing 21 into the guide heat dissipation chamber. A diffusion cone head 222 is provided inside the guide sleeve 221, and the top of the diffusion cone head 222 is an inclined surface. When the airflow passes through the one-way air inlet housing 21 and enters the guide sleeve 221, the flowing airflow will first contact the inclined surface at the top of the diffusion cone head 222. The airflow will diffuse under the guidance of the inclined surface. The diffused airflow will flow downward from the gap between the guide sleeve 221 and the diffusion cone head 222, so that the airflow entering the guide heat dissipation chamber can diffuse and flow evenly. The diffused airflow helps the airflow to better contact the inner wall of the guide heat dissipation chamber, thereby improving the air cooling and heat dissipation efficiency. The diffusion cone head 222 effectively prevents the flowing airflow from flowing directly from the middle of the guide heat dissipation chamber, resulting in the airflow being unable to effectively contact the inner wall of the guide heat dissipation chamber.

[0049] A first telescopic rod 224 is slidably mounted on the upper limit position of the first rotating mounting shaft 223. A transmission docking joint 2241 is further mounted on the first telescopic rod 224. A first spring 225 is installed between the transmission docking joint 2241 and the first rotating mounting shaft 223. The first spring 225 provides a preload force to ensure that the transmission docking joint 2241 is properly positioned in the initial state and has the ability to adaptively retract.

[0050] When the heat dissipation mounting shell 4 is fixedly connected to the air guide device 2, the transmission guide head 22 is automatically inserted into the air guide and heat dissipation cavity 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.

[0051] The coordinated design of the first telescopic rod 224 and the first spring 225 enables the transmission docking joint 2241 to perform stable adaptive contraction movement, thereby avoiding damage to the equipment caused by forced docking when the transmission docking joint 2241 is not accurately docked to the designated position.

[0052] When the fan 23 begins to rotate, the first rotating mounting shaft 223 rotates accordingly, driving the first telescopic rod 224 and the transmission docking joint 2241 to rotate synchronously. When the transmission docking joint 2241 rotates to the designated position of the circulating conveyor 32, the preload force of the first spring 225 pushes the transmission docking joint 2241 downward, achieving accurate docking with the circulating conveyor 32. Once docked, the continued rotation of the fan 23 drives the circulating conveyor 32 through the transmission docking joint 2241, thereby driving the coolant to circulate within the circulation conduit 31, achieving cooling and heat dissipation.

[0053] See also Figures 7 to 12As shown, the circulation pipe 31 includes an outer circulation pipe 311 distributed on the outside of the heat dissipation mounting shell 4, and the circulation pipe 31 also includes an inner circulation pipe 312 distributed inside the heat dissipation mounting 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.

[0054] The circulation pipe 31 is arranged as a whole inside and outside the heat dissipation mounting shell 4, and is specifically composed of an external circulation pipe 311 distributed on the outside of the heat dissipation mounting shell 4 and an internal circulation pipe 312 distributed inside the heat dissipation mounting shell 4. The two are connected to each other, and the internal circulation pipe 312 is directly connected to the circulation conveying device 32 to form a complete coolant circulation loop.

[0055] The outer flow tube 311 is arranged to fit 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 tube 311 and the inner flow tube 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 tube 312 through the heat dissipation mounting shell 4, and then transferred to the coolant circulating inside, causing the coolant temperature to increase. The heated coolant is transported to the outer flow tube 311 through the inner flow tube 312. Since the outer flow tube 311 is directly exposed to the external flow airflow environment, forced convection heat exchange occurs between the flowing air and the surface of the outer flow tube 311. Through the heat conduction and convection heat exchange mechanism, the flowing air effectively reduces the temperature of the coolant in the outer flow tube 311.

[0056] The cooled coolant re-enters the inner flow tube 312 at the end of the outer flow tube 311, forming a complete circulating liquid cooling path. During this circulation process, the coolant continuously absorbs the heat generated by the hydrogen fuel cell 1 and transfers it to the external airflow environment, achieving heat dissipation through gas-liquid heat exchange.

[0057] 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.

[0058] When the drone is in flight, external airflow enters the air guide device 2 through the one-way air inlet housing 21. This airflow generates axial thrust as it passes through the transmission guide head 22. Driven by the airflow, the transmission guide head 22, in conjunction with the fan, generates rotational motion. This rotational motion is synchronously transmitted to the kinetic energy conversion device 322 via mechanical transmission. The kinetic energy conversion device 322 drives the one-way compression assembly 321. During this process, the one-way compression assembly 321 drives the directional delivery of coolant, creating a continuous circulation flow between the inner flow tube 312 and the outer flow tube 311.

[0059] See also Figures 8 to 14 As shown, the one-way compression assembly 321 includes a compression sleeve 3211 installed in the diversion and heat dissipation chamber, and 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, and a transmission telescopic rod 3217 is also installed on the one-way piston 3214. The 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.

[0060] A one-way flow hole 3215 is provided on the one-way piston 3214 , and a blocking film 3216 is also installed on the one-way piston 3214 .

[0061] The kinetic energy conversion device 322 converts the rotational motion of the transmission guide head 22 into linear reciprocating motion, pushing the one-way piston 3214 downward within the compression sleeve 3211 via the transmission telescopic rod 3217. As the one-way piston 3214 descends, the internal sealing film 3216, under hydraulic pressure, presses against the one-way flow hole 3215, forming a dynamic seal and blocking the flow of coolant through the one-way flow hole 3215. The one-way outlet valve 3213 at the bottom of the compression sleeve 3211 is connected to the internal flow tube 312. The volume reduction caused by the downward movement of the piston forces the coolant to be discharged in a targeted manner through the one-way outlet valve 3213, resulting in a high-pressure fluid output. The one-way liquid inlet valve 3212 on the upper part of the compression sleeve 3211 is connected to the internal circulation pipe 312. Under the action of the negative pressure generated by the downward movement of the piston, the coolant enters the interior of the compression sleeve 3211 through the one-way liquid inlet valve 3212. At this time, the coolant entering the compression sleeve 3211 is above the one-way piston 3214. When the transmission telescopic rod 3217 drives the one-way piston 3214 upward, the one-way piston 3214 will squeeze the coolant above, and the coolant above cannot flow out from the one-way liquid inlet valve 3212. For this reason, when the coolant is squeezed, it will exert pressure on the one-way circulation hole 3215. The sealing film 3216 will move downward under the influence of the hydraulic pressure and break away from the one-way circulation hole 3215, so that the coolant flows through the one-way circulation hole 3215 into the bottom of the one-way piston 3214, providing medium replenishment for the next compression and completing the circulation preparation.

[0062] See also Figures 8 to 14As shown, the kinetic energy conversion device 322 includes 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, and a rotating block 3223 is also installed inside the mounting sleeve 3221, and a guide ball 3224 is installed on the rotating block 3223, and the guide ball 3224 is slidably connected along the inclined circulation groove 3222, and a second telescopic rod 3226 is installed on the rotating block 3223, and a second rotating mounting shaft 3225 is also rotatably mounted on the mounting sleeve 3221, and the second rotating mounting shaft 3225 is limitedly slidably connected to the second telescopic rod 3226, and a limiting card joint 3227 is provided on the top of the second rotating mounting shaft 3225.

[0063] The limit card joint 3227 is provided with a hexagonal groove, which is used to dock with the transmission docking joint 2241 to ensure the stability of the transmission.

[0064] The limited sliding connection between the second rotating mounting shaft 3225 and the second telescopic rod 3226 is similar to the connection between the first rotating mounting shaft 223 and the first telescopic rod 224, and will not be further described here. When the drone is in flight, external airflow enters the air guide device 2 through the one-way air inlet housing 21 and acts on the transmission guide head 22, generating rotational motion. The rotational motion of the transmission guide head 22 is transmitted to the second rotating mounting shaft 3225 in the kinetic energy conversion device 322.

[0065] The rotation of the second rotatable mounting shaft 3225 drives the synchronous rotation of the second telescopic rod 3226. Mounted on the second telescopic rod 3226 is a rotating block 3223, equipped with guide balls 3224 that slidably engage with the inclined circulation grooves 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 due to the interaction between the guide balls 3224 and the inclined circulation grooves 3222. Specifically, the guide balls 3224 move along the trajectory of the inclined circulation grooves 3222, causing the rotating block 3223 to simultaneously move up and down during rotation.

[0066] The rotating block 3223 is rotationally connected to the transmission telescopic rod 3217. The lifting motion of the rotating block 3223 is transmitted to the transmission telescopic rod 3217 via the second telescopic rod 3226. Because the second telescopic rod 3226 maintains a mechanical connection with the rotating block 3223 and the transmission telescopic rod 3217, the up-and-down movement 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 this process, the kinetic energy conversion device 322 converts the rotational motion of the transmission guide head 22 into linear reciprocating motion, which is then used to drive the one-way compression assembly 321.

[0067] See also 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 mounting shell 4, a plurality of inner wall heat dissipation fitting blocks 45 are installed on the inner side of the heat dissipation mounting shell 4, a removable limiting clamp 42 is provided on the outer side of the outer wall heat dissipation fitting block 44, a rotating exhaust pipe 41 is installed on the bottom of the heat dissipation mounting shell 4, and a guide blade 421 is provided on the rotating exhaust pipe 41.

[0068] The heat sink housing 4 is equipped with multiple position-limiting engaging mechanisms 43. These mechanisms include multiple movable blocks 431 slidably mounted on the heat sink housing 4. A second spring 432 is installed between each movable block 431 and the heat sink housing 4. The second spring 432 is used to push the movable block 431, allowing it to move elastically. The movable block 431 is used to engage the fixed position-limiting ring 42, ensuring the stability of the position-limiting ring 42.

[0069] The gap between the inner wall heat dissipation block 45 and the outer wall heat dissipation block 44 of the heat dissipation mounting housing 4 forms a storage chamber. Both the inner wall heat dissipation block 45 and the outer wall heat dissipation block 44 are in direct contact with the outer wall of the hydrogen fuel cell 1, providing positional restraint and heat conduction to the hydrogen fuel cell 1. A third spring 46 is provided between the inner wall heat dissipation block 45 and the heat dissipation mounting housing 4.

[0070] When the hydrogen fuel cell 1 is in operation, the heat generated is transferred to the inner wall heat dissipation bonding block 45 and the outer wall heat dissipation bonding block 44. During the flight of the drone, the outer wall heat dissipation bonding block 44 is directly exposed to the external airflow, realizing natural convection heat dissipation. At the same time, the air guide device 2 guides the airflow into the transmission guide head 22 through the one-way air inlet shell 21. The airflow passes through the fan 23 and enters the diversion heat dissipation chamber, cooling the inner wall heat dissipation bonding block 45 inside the heat dissipation mounting shell 4. The airflow then passes through the diversion heat dissipation chamber and enters the rotating exhaust pipe 41. The rotating exhaust pipe 41 will discharge the airflow. The guide blades 421 are affected by the external airflow and will automatically adjust the rotating exhaust to a downwind position, so that the air outlet of the rotating exhaust pipe 41 remains in a downwind state to avoid backflow of airflow. During this process, the inner wall heat dissipation bonding block 45 and the outer wall heat dissipation bonding block 44 are in continuous contact with the external airflow, effectively increasing the heat dissipation area and improving the heat dissipation efficiency.

[0071] The outer wall heat dissipation fitting block 44 and the inner wall heat dissipation fitting block 45 are both slidably connected to the heat dissipation mounting shell 4 .

[0072] When the heat dissipation mounting shell 4 and the air guide device 2 are installed together, the transmission guide head 22 of the air guide device 2 will press against the inner wall heat dissipation bonding block 45, so that the inner wall heat dissipation bonding block 45 remains in contact with the hydrogen fuel cell 1. At this time, the third spring 46 will be compressed. At the same time, the outer wall heat dissipation bonding block 44 and the hydrogen fuel cell 1 are kept in contact through the installation of the limiting clamp 42.

[0073] The heat sink housing 4 is detachably connected to the air guide device 2, facilitating installation and replacement of the hydrogen fuel cell 1. To replace the hydrogen fuel cell 1, the heat sink housing 4 and air guide device 2 are separated. The third spring 46 releases pressure, pushing the inner heat sink contact block 45 back into place, releasing contact with the hydrogen fuel cell 1. The retaining ring 42 is then removed, allowing the outer heat sink contact block 44 to be adjusted and disengaged from the hydrogen fuel cell 1. The hydrogen fuel cell 1 is now disassembled.

[0074] See also Figures 7 to 11 As shown, the outer side of the outer wall heat dissipation fitting block 44 is provided with an arc-shaped windward surface 441, the arc-shaped windward surface 441 is provided with a pipe distribution groove 443 for installing the circulation pipe 31, the top of the outer wall heat dissipation fitting block 44 is provided with a limiting clamping edge 442, and the side of the outer wall heat dissipation fitting block 44 away from the arc-shaped windward surface 441 is provided with a first thermal pad.

[0075] The pipe distribution groove 443 on the arc-shaped windward surface 441 is used for installing the outer flow pipe 311 of the flow pipe 31 .

[0076] The outer wall heat dissipation bonding block 44 is in direct contact with the outer wall of the hydrogen fuel cell 1 , and enhances the heat conduction effect through the first thermal pad, thereby conducting the heat generated during the operation of the hydrogen fuel cell 1 to itself.

[0077] The outer heat dissipation block 44 has a curved windward surface 441, which effectively ensures contact with the airflow while maintaining smooth airflow. During flight, the outer heat dissipation block 44 is directly exposed to the external airflow. This contact with the airflow enables natural convection cooling, dissipating heat conducted to the block to the external environment.

[0078] A limiting clamping edge 442 is provided on the top of the outer wall heat dissipation fitting block 44. The limiting clamping ring 42 can be installed on the limiting clamping edge 442. The installation of the limiting clamping ring 42 can effectively limit the position of multiple outer wall heat dissipation fitting blocks 44. The limiting clamping mechanism 43 ensures the stability of the installation of the limiting clamping ring 42, thereby ensuring 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, it is necessary to adjust the position of the outer wall heat dissipation fitting block 44. At this time, the limiting clamping ring 42 can be removed from the limiting clamping edge 442 to adjust the position of the outer wall heat dissipation fitting block 44. 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.

[0079] 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 and 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 wavy 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 inlet 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 wavy heat dissipation fin 451. The wavy heat dissipation fin 451 increases the contact area with the airflow, destroys the airflow boundary layer, and promotes heat transfer, thereby achieving 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.

[0080] Specific working principle:

[0081] The circulation pipe 31 is used to guide the coolant. A circulating conveying device 32 is installed on the circulation pipe 31. The circulating 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, achieving uniform and effective cooling and heat dissipation without consuming additional electrical energy. The air guide device 2 includes a one-way air inlet shell 21 installed on the top of the heat dissipation mounting shell 4, and the one-way air inlet shell 21 is used to guide the airflow to the guide heat dissipation chamber. A transmission guide head 22 is installed at the bottom of the one-way air inlet shell 21, and a fan 23 is installed on the transmission guide head 22.

[0082] The air guide device 2 is fixedly mounted on the bottom of the drone, and the heat sink mounting shell 4 is detachably connected to the air guide device 2. When the hydrogen fuel cell 1 needs to be installed, the heat sink mounting shell 4 is removed from the air guide device 2, multiple hydrogen fuel cells 1 are placed into the storage chamber, and then the heat sink mounting shell 4 is mounted to the bottom of the air guide device 2 to ensure stable encapsulation and fixation of the hydrogen fuel cell 1.

[0083] 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, realizing air cooling of the outer wall. At the same time, the air guide device 2 guides the airflow into the transmission guide head 22. 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 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 influence of the airflow. The rotation of the fan 23 drives the transmission guide head 22 to rotate. 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.

[0084] When the temperature of the hydrogen fuel cell 1 is too high or the drone's flight speed is low, the fan 23 motor is activated. This accelerates the airflow inside the heat dissipation chamber and the movement of the circulating conveyor 32, accelerating the flow of the coolant and further improving the cooling effect, achieving a cooling protection effect through adaptive switching adjustment.

[0085] Through the above principle, the temperature control structure of the hydrogen fuel cell 1 can effectively solve the problems of single heat dissipation mode, 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.

[0086] The above embodiments merely represent one or more embodiments of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of protection of the present invention. It should be noted that a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present invention, and such modifications and improvements fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the appended claims.

Claims

1. A hydrogen fuel cell temperature control structure for a drone, mounted on the outside of a hydrogen fuel cell (1), characterized in that: The heat dissipation device comprises a heat dissipation installation shell (4), wherein a heat dissipation chamber and a storage chamber are provided inside the heat dissipation installation shell (4), wherein the storage chamber is used for limiting the installation of a hydrogen fuel cell (1), wherein a circulating temperature control device (3) is installed inside the heat dissipation installation shell (4), wherein the circulating temperature control device (3) comprises a circulation pipe (31) evenly distributed inside the heat dissipation installation shell (4), wherein the circulation pipe (31) is used for guiding a coolant, wherein a circulating conveying device (32) is installed on the circulation pipe (31), wherein an air guide device (2) is installed on the top of the heat dissipation installation shell (4), wherein the air guide device (2) comprises a one-way air inlet shell (21) installed on the top of the heat dissipation installation shell (4), wherein the one-way air inlet shell (21) is used for guiding airflow to the heat dissipation chamber, wherein a transmission guide head (22) is installed on the bottom of the one-way air inlet shell (21), wherein a fan (23) is installed on the transmission guide head (22), and wherein the transmission guide head (22) is in transmission connection with the circulating conveying device (32); The circulating conveying device (32) includes 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 pipe (31), the one-way compression component (321) is used to drive the flow of the 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 guide head (22); A spiral guide groove (211) is provided inside the one-way air inlet housing (21), and a plurality of air inlet guide holes (212) are provided on the outside of the one-way air inlet housing (21), and an air inlet floating membrane (213) is provided in each air inlet guide hole (212); 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 mounting shaft (223) is rotatably mounted on the diffusion cone head (222); the first rotation mounting 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 mounting 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 mounting shaft (223).

2. The hydrogen fuel cell temperature control structure for a drone according to claim 1, characterized in that: The circulation pipe (31) includes an outer circulation pipe (311) distributed outside the heat dissipation installation shell (4), and the circulation pipe (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).

3. The hydrogen fuel cell temperature control structure for a 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) being provided with a one-way liquid inlet valve (3212) and a one-way liquid outlet valve (3213), a one-way piston (3214) being slidably mounted inside the compression sleeve (3211), a transmission telescopic rod (3217) being further mounted on the one-way piston (3214), and an end of the transmission telescopic rod (3217) away from the one-way piston (3214) being in transmission connection with the movable end of the kinetic energy conversion device (322).

4. The hydrogen fuel cell temperature control structure for a drone according to claim 3, characterized in that: The kinetic energy conversion device (322) includes 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 further 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 rotatably mounted on the mounting sleeve (3221), the second rotating mounting shaft (3225) is limitedly slidably connected to the second telescopic rod (3226), and a limiting clamping joint (3227) is provided on the top of the second rotating mounting shaft (3225).

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

6. The hydrogen fuel cell temperature control structure for a drone according to claim 5, characterized in that: The outer side of the outer wall heat dissipation fitting block (44) is provided with an arc-shaped windward surface (441), the arc-shaped windward surface (441) is provided with a pipe distribution groove (443) for installing the circulation pipe (31), the top of the outer wall heat dissipation fitting block (44) is provided with a limit clamping edge (442), and the side of the outer wall heat dissipation fitting block (44) away from the arc-shaped windward surface (441) is provided with a first thermal pad.

7. The hydrogen fuel cell temperature control structure for a drone according to claim 5, 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 the 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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