Safe hydrogen fuel cell unmanned aerial vehicle and fuel system

Abstract

The invention relates to the field of hydrogen fuel cell unmanned aerial vehicles, in particular to a safety hydrogen fuel cell unmanned aerial vehicle and a fuel system, and further comprises a temperature sensor, a traction unit and a storage battery. The temperature sensor is arranged on the hydrogen fuel cell, and a safe temperature is preset; the multiple traction units are correspondingly arranged above the hydrogen fuel cell and the hydrogen tank respectively, each traction unit comprises a traction rope, the different traction units pull the hydrogen fuel cell and the hydrogen tank through the traction ropes of the traction units respectively, and when the temperature detected by the temperature sensor is higher than the safe temperature, the traction units pull the hydrogen fuel cell and the hydrogen tank. The traction ropes in all the traction units are released at the same time, and the hydrogen tank is disconnected from the hydrogen fuel cell; the storage battery is arranged in the unmanned aerial vehicle, the hydrogen fuel cell and the storage battery can supply power to the unmanned aerial vehicle, and the hydrogen fuel cell and the storage battery do not work at the same time during power supply. According to the invention, the risk of'collision and explosion 'on the ground caused by the traditional pop-up design is avoided, and core parts do not need to be abandoned to reduce the emergency cost.

Description

Technical Field

[0001] This invention relates to the field of hydrogen fuel cell drones, specifically to a safe hydrogen fuel cell drone and its fuel system. Background Technology

[0002] When using hydrogen fuel cell drones, due to the special nature of hydrogen fuel cells, hydrogen tanks are usually mounted on the bottom of the drone. However, various unexpected situations can occur during drone flight. One of the more serious situations is that the hydrogen fuel cell temperature becomes too high. If the hydrogen fuel cell temperature is too high, the hydrogen in the hydrogen tank will become unstable due to heat. When the cooling system fails, the reaction goes out of control, or the load changes suddenly (such as sudden acceleration or carrying high-power devices), the temperature of the hydrogen fuel cell will suddenly rise.

[0003] Chinese Patent Publication No. CN208602711U discloses a safety device for a hydrogen fuel cell drone, including an electromagnetic elastic component and an electric push rod disposed within a hydrogen tank mounting base. The hydrogen tank is mounted on the upper part of the drone body via the hydrogen tank mounting base, and clamping blocks are respectively disposed on both sides of the hydrogen tank. The clamping blocks are connected to an electric push rod via a linkage mechanism. The electromagnetic elastic component is disposed directly below the hydrogen tank.

[0004] Electric push rods are horizontally mounted on both sides of the hydrogen tank mounting base, and drive the clamping blocks to clamp and separate relative to the hydrogen tank via a linkage mechanism. The electromagnetic elastic component includes an electromagnet and a spring structure, the spring structure being used to eject the hydrogen tank from the hydrogen tank mounting base.

[0005] The aforementioned solution uses the ejection of the hydrogen tank to prevent deflagration or explosion. However, once ejected, the hydrogen tank completely separates from the drone. If the drone is flying at high altitude, the impact force of the falling hydrogen tank on ground objects due to gravity is significant. Even if the hydrogen is released during ejection, the tank itself can still cause damage to ground objects or pedestrians. Furthermore, the release rate of hydrogen from the ejected tank is limited, requiring time to completely dissipate. If the hydrogen is not completely dissipated upon landing, an explosion may occur, causing even greater damage to ground objects and pedestrians. Therefore, while the existing method of ejecting the hydrogen tank protects the drone, it neglects the safety of ground objects and pedestrians. Additionally, while ejecting the hydrogen tank stops supplying the hydrogen fuel cell, the fuel cell remains at a high temperature. Without timely and effective cooling measures, the high temperature of the fuel cell can also affect the drone's structure, preventing it from returning to base in an emergency. Summary of the Invention

[0006] To address the aforementioned issues, a safe hydrogen fuel cell drone and fuel system are provided. Through a traction unit, the hydrogen fuel cell and hydrogen tank are stably towed, allowing for a smooth descent without crashing in the event of a high-temperature malfunction. This avoids the ground impact and explosion risks associated with traditional pop-up designs, while also eliminating the need to discard core components, thus reducing emergency costs. After the hydrogen fuel cell separates from the drone, it forms an airflow channel, achieving efficient heat dissipation combined with hydrogen supply cutoff. The heat no longer affects the internal battery, ensuring emergency power output to support the drone's safe return.

[0007] To address the problems of existing technologies, the present invention provides a safe hydrogen fuel cell drone, including a hydrogen fuel cell and a fuel system disposed below the drone body, the fuel system including a hydrogen tank;

[0008] It also includes a temperature sensor, a traction unit, and a battery;

[0009] A temperature sensor is installed on the hydrogen fuel cell and a preset safe temperature is set.

[0010] Multiple traction units are provided and are respectively positioned above the hydrogen fuel cell and the hydrogen tank. Each traction unit includes a traction rope. Different traction units pull the hydrogen fuel cell and the hydrogen tank respectively through their own traction ropes. When the temperature sensor detects that the temperature is higher than the safe temperature, the traction ropes in all traction units are released at the same time, and the hydrogen tank is disconnected from the hydrogen fuel cell.

[0011] The battery is built into the drone. Both the hydrogen fuel cell and the battery can power the drone, but they do not work at the same time.

[0012] Preferably, there is a vertical distance between the released hydrogen fuel cell and the released hydrogen tank.

[0013] Preferably, multiple temperature sensors are provided and distributed on multiple end faces of the hydrogen fuel cell.

[0014] Preferably, a vent valve is provided at the tail end of the hydrogen tank to allow hydrogen to be discharged to the outside.

[0015] Preferably, there are two hydrogen tanks arranged symmetrically about the hydrogen fuel cell.

[0016] Preferably, a heat insulation sleeve is provided on the outside of the hydrogen tank, and the heat insulation sleeve is made of high temperature resistant heat insulation material.

[0017] Preferably, extension plates are provided on both sides of the hydrogen fuel cell, and the extension plates are fixedly connected to the drone body. A limiting slide rail is vertically fixed on the side wall of the extension plate near the hydrogen fuel cell. An extension ear is provided on the side wall of the hydrogen fuel cell, and the extension ear extends into the limiting slide rail and slides in cooperation with the limiting slide rail. The bottom of the limiting slide rail has a limiting function for the extension ear.

[0018] Preferably, a multi-stage telescopic rod is vertically installed on one side of the heat insulation shell, and the two ends of the multi-stage telescopic rod are fixedly connected to the UAV body and the heat insulation shell, respectively.

[0019] Preferably, a connection assembly is provided between the hydrogen tank and the hydrogen fuel cell, the connection assembly including a connecting pipe and a solenoid valve;

[0020] The two ends of the connecting pipe are connected to the hydrogen tank and the hydrogen fuel cell, respectively, and the connecting pipe has a spiral structure.

[0021] There are two solenoid valves, which are respectively located at both ends of the connecting pipe.

[0022] The present invention also relates to a fuel system as part of a safe hydrogen fuel cell drone.

[0023] The advantages of this invention compared to the prior art are:

[0024] 1. This invention utilizes a traction unit to stably traction the hydrogen fuel cell and hydrogen tank. In the event of a high-temperature failure, both can descend smoothly without falling, avoiding the ground impact and explosion risks associated with traditional pop-up designs, while also eliminating the need to discard core components, thus reducing emergency costs. After the hydrogen fuel cell separates from the drone, it forms an airflow channel, achieving efficient heat dissipation combined with the hydrogen supply cutoff. Its heat no longer affects the internal battery, ensuring emergency power output to support the drone's successful return. After the hydrogen tank descends to its lowest position, it is systematically vented and reset, further mitigating the risk of hydrogen ignition and improving emergency flight stability.

[0025] 2. Through the orderly venting and resetting mechanism of the hydrogen tank and the multi-layered structural protection design, the stability and overall safety performance of the UAV during emergency return are further improved. When the hydrogen tank descends to its lowest position, it is safely vented through the vent valve, and the vented hydrogen is kept away from the UAV body, avoiding safety hazards; after venting is completed, the traction unit lifts and resets it, ensuring the counterweight balance of the UAV during flight and optimizing the stability of return.

[0026] 3. By setting up multi-stage telescopic rods and limiting slide rails, it is ensured that both the hydrogen fuel cell and the hydrogen tank can descend stably. At the same time, the hydrogen fuel cell and the hydrogen tank are not at the same height after descending, which avoids the hydrogen fuel cell igniting the hydrogen discharged from the hydrogen tank at a high temperature. Attached Figure Description

[0027] Figure 1 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone according to the present invention. Figure 1 .

[0028] Figure 2 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone according to the present invention. Figure 2 .

[0029] Figure 3 This invention relates to a safe hydrogen fuel cell drone. Figure 2 A magnified view of a portion of point A in the middle.

[0030] Figure 4 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone of the present invention after the drone body has been removed.

[0031] Figure 5 This invention relates to a safe hydrogen fuel cell drone. Figure 4 A magnified view of a portion of point B in the middle.

[0032] Figure 6 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone of the present invention after removing the drone body and part of the heat insulation shell.

[0033] Figure 7 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone of the present invention after the drone body has been removed and the hydrogen fuel cell has been disassembled.

[0034] Figure 8 This invention relates to a safe hydrogen fuel cell drone. Figure 7 A magnified view of a portion of point C.

[0035] Figure 9 This is a partial cross-sectional three-dimensional schematic diagram of a safe hydrogen fuel cell drone of the present invention after the drone body has been removed.

[0036] Figure 10 This is a three-dimensional schematic diagram of a safe hydrogen fuel cell drone of the present invention in an emergency situation.

[0037] The following are the labels in the diagram: 1. Hydrogen fuel cell; 2. Hydrogen tank; 21. Vent valve; 22. Heat insulation shell; 23. Connecting assembly; 231. Connecting pipe; 232. Solenoid valve; 3. Traction unit; 31. Traction rope; 32. Winder; 4. Extension plate; 41. Limiting slide rail; 42. Extension lug; 5. Multi-stage telescopic rod. Detailed Implementation

[0038] To further understand the features, technical means, and specific objectives and functions achieved by the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0039] Reference Figure 1 , Figure 2 , Figure 4 , Figure 5 and Figure 6A safe hydrogen fuel cell drone includes a hydrogen fuel cell 1 disposed below the drone body and a fuel system, the fuel system including a hydrogen tank 2;

[0040] It also includes a temperature sensor, traction unit 3, and a battery;

[0041] A temperature sensor is installed on hydrogen fuel cell 1, and a preset safe temperature is set.

[0042] Multiple traction units 3 are provided and are respectively positioned above the hydrogen fuel cell 1 and the hydrogen tank 2. Each traction unit 3 includes a traction rope 31. Different traction units 3 pull the hydrogen fuel cell 1 and the hydrogen tank 2 respectively through their own traction ropes 31. When the temperature sensor detects that the temperature is higher than the safe temperature, the traction ropes 31 in all traction units 3 are released at the same time, and the hydrogen tank 2 is disconnected from the hydrogen fuel cell 1.

[0043] The battery is built into the drone. Both the hydrogen fuel cell 1 and the battery can power the drone, but they do not work at the same time when powering the drone.

[0044] In existing technologies, when the battery of a hydrogen fuel cell drone 1 malfunctions and overheats, the core approach is to quickly eject the hydrogen tank 2 via a mechanical trigger mechanism. This cuts off the fuel supply and prevents the hydrogen inside from deflagrizing or exploding due to high temperatures, thus prioritizing the protection of the drone itself and its onboard equipment. However, this design has significant safety vulnerabilities: when drones perform high-altitude operations such as power line inspections and terrain mapping, their flight altitude often reaches tens or even hundreds of meters. After ejection, the hydrogen tank 2 will completely detach from the drone and accelerate downwards under the continuous force of gravity. Even if the tank is made of lightweight alloy, the kinetic energy accumulated during its descent is still sufficient to cause severe impact damage to ground buildings and precision equipment. If the crash site is a densely populated area such as a residential area, farmland, or industrial zone, it could directly threaten pedestrian safety. Even if the hydrogen release valve is activated simultaneously during ejection, the mass and descent speed of the tank itself do not decrease significantly during the gas discharge process. The impact of the tank alone could cause personal injury or property damage, making the safety hazard undeniable.

[0045] Furthermore, to prevent an explosion upon impact after hydrogen tank 2 is ejected, it is necessary to expel the gas from tank 2. Due to factors such as tank structure design, release channel diameter, and pressure changes, the hydrogen expulsion speed is inherently limited, typically requiring several seconds or even tens of seconds to completely empty. However, the landing time of a tank falling from a height is extremely short, often resulting in it hitting the ground before all the gas has been expelled. At this point, the remaining hydrogen inside the tank may be ignited by sparks from the impact, or accumulate in low-lying areas or enclosed spaces such as factory corners or residential building corridors, reaching its explosive limit. Once an explosion occurs, its destructive power far exceeds that of a simple tank impact: it will not only cause secondary damage to surrounding objects but may also ignite nearby flammable materials such as vegetation, cardboard boxes, and fuel, causing a fire to spread and posing a dual threat of "impact + explosion" to the lives of people on the ground. This design, which directly transfers the risks of the drone to the ground environment, clearly ignores the core requirement of overall safety protection and fails to consider the safety of ground objects and pedestrians.

[0046] Furthermore, current technology only focuses on the ejection of hydrogen tank 2 for safety, completely neglecting the high-temperature handling issue of the hydrogen fuel cell 1 itself. After hydrogen tank 2 ejects, although the hydrogen supply is cut off, preventing the fuel from continuously participating in the reaction, the hydrogen fuel cell 1 remains at a high temperature due to the malfunction. At this high temperature, the fuel cell cannot output stable power, causing the drone to lose its energy support for continuous flight. Even if the operator attempts to initiate an emergency return procedure, it will be impossible due to the power system failure. This not only results in the drone's own crash loss, but if the drone is carrying high-precision mapping equipment, confidential data storage modules, or express parcels, a crash could also cause additional property damage, information leakage, or cargo damage, further expanding the scope of the accident. Even if an emergency battery is installed inside the drone, a successful return cannot be guaranteed. This is because the existing hydrogen fuel cell 1 is not detachable from the drone body; therefore, the high temperature of the hydrogen fuel cell 1 will have a high-temperature effect on the drone itself, causing the battery to operate at a high temperature, and the risk of crash remains high.

[0047] To avoid the aforementioned situation, the existing hydrogen fuel cell drone 1 was optimized. When the hydrogen fuel cell 1 malfunctions and overheats, both the hydrogen fuel cell 1 and the hydrogen tank 2 can detach from the drone simultaneously. However, due to the traction unit 3 and the traction rope 31, neither the hydrogen fuel cell 1 nor the fuel system will fall off; instead, they will fly with the drone. This avoids the direct jettisoning of the hydrogen fuel cell 1 and hydrogen tank 2, preventing damage to ground objects or people, and also reduces the cost of using the drone in emergency situations. The specific structure and working process of this invention are as follows:

[0048] During normal use, if the hydrogen fuel cell 1 at the bottom of the drone malfunctions and overheats, a temperature sensor will monitor the temperature of the hydrogen fuel cell 1 in real time. When the detected temperature exceeds a preset safe temperature, the traction unit 3 will be activated. The traction unit 3 includes a traction rope 31 and a retractor 32. The traction rope 31 is wound around the retractor 32, and the retractor 32 releases the traction rope 31. The traction rope 31 is made of metal. Since both the hydrogen fuel cell 1 and the hydrogen tank 2 are tractioned by the traction rope 31, the hydrogen fuel cell 1 and the hydrogen tank 2 move linearly in the vertical direction, preventing sudden drops. While ensuring the hydrogen fuel cell 1 and hydrogen tank 2 separate from the drone without falling, a traditional pop-up structure, although improving separation efficiency, still requires the traction rope 31. When the hydrogen fuel cell 1 and hydrogen tank 2 descend to a certain height, the rope reaches its maximum length, causing them to suddenly stop moving under its pull. This results in a significant impact on the drone, potentially leading to a rapid crash. Using a traction unit 3 to autonomously lower the hydrogen fuel cell 1 and hydrogen tank 2 avoids this problem.

[0049] As the hydrogen fuel cell 1 and hydrogen tank 2 gradually descend under the action of the traction unit 3, the distance between the hydrogen fuel cell 1 and the drone gradually increases, forming an airflow channel. Because the drone is at high altitude, the gradually increasing airflow channel provides a better cooling environment for the hydrogen fuel cell 1. Simultaneously, when both the hydrogen fuel cell 1 and hydrogen tank 2 descend, the hydrogen tank 2 stops supplying hydrogen to the hydrogen fuel cell 1. At this point, although the hydrogen fuel cell 1 is still at a high temperature, the fuel supply has been cut off. Therefore, even though the remaining hydrogen is exhausted, the high temperature of the hydrogen fuel cell 1 is controlled. The heat from the hydrogen fuel cell 1, now separated from the drone, cannot affect the drone itself, ensuring that the battery built into the drone can function normally, thus guaranteeing the drone's successful return in an emergency.

[0050] Additionally, it's worth noting that after hydrogen tank 2 separates from the drone and descends to its lowest position, it vents its gas. Tank 2 actively expels the hydrogen inside, ensuring that the expelled hydrogen does not disperse around the drone, thus guaranteeing safe flight. Once tank 2 has completely vented its hydrogen, the traction unit 3 lifts it back to its original position, leaving only hydrogen fuel cell 1 separated from the drone. This improves the drone's stability during emergency return-to-home maneuvers.

[0051] Reference Figures 1-10 There is a vertical distance between the hydrogen fuel cell 1 and the hydrogen tank 2 after the hydrogen is released.

[0052] The bottom of the ejected hydrogen fuel cell 1 is higher than the top of the ejected hydrogen tank 2, ensuring that the ejected hydrogen fuel cell 1 and hydrogen tank 2 are not parallel. This is because the ejected hydrogen fuel cell 1 is still at a high temperature. If the hydrogen tank 2 and hydrogen fuel cell 1 were kept horizontal, the high-temperature hydrogen fuel cell 1 would still pose a threat to the hydrogen tank 2. By staggering the ejected hydrogen fuel cell 1 and hydrogen tank 2 in vertical height, the high-temperature hydrogen fuel cell 1 is prevented from affecting the hydrogen tank 2 which is releasing gas, and the high temperature is also prevented from igniting the released hydrogen.

[0053] Reference Figures 1-10 Multiple temperature sensors are installed and distributed on multiple end faces of the hydrogen fuel cell 1.

[0054] By setting temperature sensors on multiple end faces of the hydrogen fuel cell 1, the temperature changes of the hydrogen fuel cell 1 can be detected more comprehensively, avoiding the occurrence of blind spots. The specific number of temperature sensors needs to be set according to the actual situation.

[0055] Reference Figure 4 and Figure 6 A vent valve 21 is installed at the tail of the hydrogen tank 2 to allow hydrogen to be discharged to the outside.

[0056] When hydrogen tank 2 separates from the drone and descends to its lowest position, vent valve 21 opens, at which point hydrogen tank 2 is disconnected from hydrogen fuel cell 1, and hydrogen in hydrogen tank 2 is discharged through vent valve 21.

[0057] Reference Figure 1 and Figure 2 There are two hydrogen tanks 2, which are symmetrical about the hydrogen fuel cell 1.

[0058] Two hydrogen tanks 2 are provided, and the two hydrogen tanks 2 are symmetrically arranged about the hydrogen fuel cell 1, which ensures the balance of the counterweight under the drone and improves the stability of the drone flight.

[0059] Reference Figure 9 A heat insulation sleeve is installed on the outside of the hydrogen tank 2. The heat insulation sleeve is made of high temperature resistant heat insulation material.

[0060] By installing a heat insulation sleeve on the outside of the hydrogen tank 2, the impact of the high temperature of the hydrogen fuel cell 1 on the hydrogen tank 2 is further avoided. This is because when the hydrogen fuel cell 1 first malfunctions and heats up, it is located between the two hydrogen tanks 2. At this time, the heat generated by the hydrogen fuel cell 1 will affect the hydrogen tank 2. In addition, since both the hydrogen fuel cell 1 and the hydrogen tank 2 are separated from the UAV body by the traction unit 3, their movement speed during separation is slower than that of a traditional ejection method. Therefore, when the hydrogen fuel cell 1 and the hydrogen tank 2 descend synchronously, the heat insulation sleeve surrounding the hydrogen tank 2 can provide insulation, preventing the heat from the hydrogen fuel cell 1 from affecting the hydrogen tank 2.

[0061] Reference Figure 8 An extension plate 4 is provided on both sides of the hydrogen fuel cell 1. The extension plate 4 is fixedly connected to the drone body. A limiting slide rail 41 is vertically fixed on the side wall of the extension plate 4 near the hydrogen fuel cell 1. An extension ear 42 is provided on the side wall of the hydrogen fuel cell 1. The extension ear 42 extends into the limiting slide rail 41 and slides with the limiting slide rail 41. The bottom of the limiting slide rail 41 has a limiting function for the extension ear 42.

[0062] By setting up an extension plate 4 and fixing a limiting slide rail 41 on the extension plate 4, the hydrogen fuel cell 1 slides on the limiting slide rail 41 via the extension ear 42. This improves the stability of the hydrogen fuel cell 1 during lifting and lowering, and also limits the extension ear 42 by the limiting slide rail 41, preventing the extension ear 42 from sliding out from the bottom of the limiting slide rail 41. This prevents the hydrogen fuel cell 1 from falling if the traction rope 31 in the traction unit 3 breaks accidentally.

[0063] Reference Figure 8 and Figure 10 A multi-stage telescopic rod 5 is vertically installed on one side of the heat insulation shell 22. The two ends of the multi-stage telescopic rod 5 are fixedly connected to the UAV body and the heat insulation shell 22, respectively.

[0064] Without the multi-stage telescopic boom 5, the hydrogen tank 2 is only pulled by the traction rope 31. During normal drone flight, the traction rope 31 is fully retracted, and the hydrogen tank 2 is in contact with the drone body, so the hydrogen tank 2 does not shake. However, in an emergency, if the hydrogen tank 2 needs to be released, as the distance between the hydrogen tank 2 and the drone body increases, the shaking frequency of the hydrogen tank 2 will gradually increase under the pull of the traction rope 31. This causes the traction rope 31 to wear easily when the hydrogen tank 2 shakes, and it also affects the normal flight of the drone. With the multi-stage telescopic boom 5 installed, the above situation can be avoided. Guided by the multi-stage telescopic boom 5, the hydrogen tank 2 can only move along the extension direction of the multi-stage telescopic boom 5 without shaking.

[0065] Reference Figure 1 , Figure 3 and Figure 6 A connection assembly 23 is provided between the hydrogen tank 2 and the hydrogen fuel cell 1. The connection assembly 23 includes a connecting pipe 231 and a solenoid valve 232.

[0066] The two ends of the connecting pipe 231 are connected to the hydrogen tank 2 and the hydrogen fuel cell 1 respectively, and the connecting pipe 231 has a spiral structure.

[0067] There are two solenoid valves 232, which are respectively located at both ends of the connecting pipe 231.

[0068] When the temperature detected by the temperature sensor exceeds the safe temperature, the two solenoid valves 232 located at both ends of the connecting pipe 231 close simultaneously. By setting two solenoid valves 232 on the connecting pipe 231, the situation where a single solenoid valve 232 fails to close is avoided, and the use of two solenoid valves 232 provides a safety redundancy design. The spiral tube is designed with a spiral structure to ensure that the connecting pipe 231 will not be torn off when there is a height difference between the hydrogen fuel cell 1 and the hydrogen tank 2.

[0069] Reference Figures 1-10 The present invention also relates to a fuel system as part of a safe hydrogen fuel cell drone.

[0070] Working principle: When the temperature sensor detects that the temperature of the hydrogen fuel cell 1 exceeds the preset safe temperature, the emergency program is activated. First, the two solenoid valves 232 at both ends of the connecting pipe 231 between the hydrogen fuel cell 1 and the hydrogen tank 2 will close simultaneously, quickly cutting off the hydrogen supply channel. This dual solenoid valve 232 design forms a safety redundancy, which can effectively avoid the problem of a single solenoid valve 232 failing to close properly, further improving the reliability of fuel supply cut-off.

[0071] Simultaneously, the hydrogen fuel cell 1 and the two symmetrically arranged hydrogen tanks 2, respectively, are synchronously responded to by the three traction units 3. The retractor 32 in the traction unit 3 begins to release the traction rope 31 made of metal material. Under the traction, the hydrogen fuel cell 1 and the hydrogen tank 2 descend smoothly in a preset direction. The hydrogen fuel cell 1 slides with the limiting rail 41 on the extension plate 4 of the UAV body via the extension lug 42 on the side wall. The limiting rail 41 not only improves the stability of the hydrogen fuel cell 1 during ascent and descent, but also has a limiting function at its bottom to prevent the hydrogen fuel cell 1 from falling if the traction rope 31 breaks accidentally. The hydrogen tank 2 moves under the guidance of the multi-stage telescopic rod 5 vertically arranged on one side. The two ends of the multi-stage telescopic rod 5 are fixedly connected to the UAV body and the heat insulation sleeve on the outside of the hydrogen tank 2, respectively, ensuring that the hydrogen tank 2 can only move along the extension direction of the telescopic rod, avoiding swaying during descent, reducing wear on the traction rope 31, and ensuring the flight stability of the UAV. It is worth noting that after being fully lowered, the hydrogen fuel cell 1 and the hydrogen tank 2 are arranged in an alternating manner in the vertical direction, with the bottom of the fuel cell higher than the top of the hydrogen tank 2, which effectively avoids adverse effects between the two under high temperature conditions.

[0072] During the smooth descent of hydrogen fuel cell 1 and hydrogen tank 2, the distance between them and the drone body gradually increases, forming a natural airflow channel. Airflow from the high-altitude environment passes through this channel, quickly carrying away heat from the surface of hydrogen fuel cell 1, achieving efficient heat dissipation and helping the high-temperature fuel cell gradually cool down. Simultaneously, after hydrogen fuel cell 1 separates from the drone body, it no longer exerts high-temperature radiation on the battery built into the drone, ensuring the battery can operate normally in a suitable temperature environment, providing stable emergency power to the drone and allowing operators to initiate the return-to-home procedure, supporting the drone's smooth return. When hydrogen tank 2 reaches its lowest position, its tail-end vent valve 21 automatically opens, safely releasing the hydrogen inside. After the hydrogen is completely released, the traction unit 3 will restart, lifting hydrogen tank 2 back to its original position. This reduces load imbalance during drone flight, further improving flight stability during emergency return. The entire process effectively handles high-temperature malfunctions, prevents components from falling and causing injury to personnel and objects on the ground, and ensures the safety of the drone and its onboard equipment.

[0073] The above embodiments only illustrate one or more implementations 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 those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A safe hydrogen fuel cell unmanned aerial vehicle, comprising a hydrogen fuel cell (1) and a fuel system arranged below the unmanned aerial vehicle body, the fuel system comprising a hydrogen tank (2); characterized in that further comprising a temperature sensor, a traction unit (3) and a storage battery; the temperature sensor is arranged on the hydrogen fuel cell (1) and is pre-set with a safe temperature; the traction unit (3) is arranged above the hydrogen fuel cell (1) and the hydrogen tank (2) respectively and comprises a traction rope (31), different traction units (3) respectively pull the hydrogen fuel cell (1) and the hydrogen tank (2) through their own traction ropes (31), when the temperature sensor detects that the temperature is higher than the safe temperature, the traction ropes (31) in all traction units (3) are released at the same time, the hydrogen tank (2) is disconnected from the hydrogen fuel cell (1); the storage battery is built-in in the unmanned aerial vehicle, the hydrogen fuel cell (1) and the storage battery can both supply power to the unmanned aerial vehicle, and they do not work at the same time when supplying power.

2. The safe hydrogen fuel cell drone of claim 1, wherein, The released hydrogen fuel cell (1) and the released hydrogen tank (2) have a distance in the vertical direction.

3. The safe hydrogen fuel cell drone of claim 1, wherein, The temperature sensor is arranged on multiple sides of the hydrogen fuel cell (1).

4. The safe hydrogen fuel cell drone of claim 1, wherein, A gas vent valve (21) is arranged at the tail of the hydrogen tank (2) to discharge hydrogen to the outside.

5. The safe hydrogen fuel cell drone of claim 1, wherein, The hydrogen tank (2) is arranged in two and is symmetrical about the hydrogen fuel cell (1).

6. The safe hydrogen fuel cell drone of claim 1, wherein, A heat insulation sleeve is arranged outside the hydrogen tank (2), and the heat insulation sleeve is made of high-temperature resistant heat insulation material.

7. The safe hydrogen fuel cell drone of claim 1, wherein, Extension plates (4) are arranged on both sides of the hydrogen fuel cell (1), the extension plates (4) are fixedly connected with the unmanned aerial vehicle body, limit sliding rails (41) are vertically and fixedly arranged on the side wall of the extension plate (4) close to the hydrogen fuel cell (1), extension ears (42) are arranged on the side wall of the hydrogen fuel cell (1) and extend into the limit sliding rails (41) and slide with the limit sliding rails (41), and the bottom of the limit sliding rails (41) limits the extension ears (42).

8. The safe hydrogen fuel cell drone of claim 6, wherein, A multi-stage telescopic rod (5) is vertically arranged on one side of the heat insulation shell (22), and both ends of the multi-stage telescopic rod (5) are fixedly connected with the unmanned aerial vehicle body and the heat insulation shell (22) respectively.

9. The safe hydrogen fuel cell drone of claim 1, wherein, A connecting assembly (23) is arranged between the hydrogen tank (2) and the hydrogen fuel cell (1), and the connecting assembly (23) comprises a connecting pipe (231) and an electromagnetic valve (232); both ends of the connecting pipe (231) are in communication with the hydrogen tank (2) and the hydrogen fuel cell (1) respectively, and the connecting pipe (231) has a spiral structure; the electromagnetic valve (232) is arranged in two, and the two electromagnetic valves (232) are arranged at both ends of the connecting pipe (231).

10. A fuel system characterized by, The system is part of the safe hydrogen fuel cell unmanned aerial vehicle according to any one of claims 1-9.

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