A large-load, long-endurance hydrogen fuel cell drone

Abstract

The present invention discloses a large-load, long-endurance hydrogen fuel cell drone; the present invention relates to the field of hydrogen energy technology; a large-load, long-endurance hydrogen fuel cell drone, mainly composed of a drone body UAV1, a cargo hold 2, a hydrogen fuel cell group 3, an unlocking component 4, and a traction air supply pipe 8. The drone body UAV1 is designed with a special installation space to accommodate the hydrogen fuel cell group 3, which converts hydrogen into electrical energy through an electrochemical reaction to provide power for the drone. One end of the traction air supply pipe 8 is connected to a ground pump station, and the other end is connected to the hydrogen fuel cell group 3 through a special interface; by introducing a self-locking air supply pump and a flexible unlocking component, the technology of the present invention enables the drone to quickly and safely disconnect from the traction air supply pipe when needed, thereby getting rid of the limitations of the ground air supply system. It enables the drone to fly for a longer time and a longer distance, greatly expanding its scope of application.

Description

Technical Field

[0001] The present invention relates to the field of hydrogen energy technology, and in particular to unmanned aerial vehicles that use hydrogen fuel cells as energy sources, and in particular to a large-load, long-endurance hydrogen fuel cell unmanned aerial vehicle. Background Art

[0002] Hydrogen fuel cell-based drones use hydrogen fuel cells as a power source. Their working principle is to convert hydrogen and oxygen into electrical energy through chemical reactions, with the only product being water. The drone uses hydrogen fuel cells as a power source and is equipped with a graphene material stack. Through the hydrogen-oxygen electrochemical reaction, it provides the drone with sufficient cruising capability and enables long-term uninterrupted flight operations.

[0003] Hydrogen fuel cells have a higher energy density, so hydrogen fuel multi-rotor drones have a longer endurance and can meet longer flight mission requirements. In addition, since hydrogen fuel cells do not generate high temperatures or high pressures during operation, hydrogen fuel multi-rotor drones have higher safety. At the same time, the only product of hydrogen fuel cells is water, so hydrogen fuel multi-rotor drones do not produce any pollutants during flight and are environmentally friendly.

[0004] In an unmanned environment, hydrogen fuel cell-based drones can perform various long-term cruising missions. Due to its long endurance, environmental protection, and high safety, this type of drone is very suitable for infrastructure inspection, wide-area mapping, emergency search and rescue, public supervision, mine operations, agriculture, animal husbandry, and logistics distribution. In these scenarios, drones can be quickly deployed to the target area to conduct aerial reconnaissance, data collection, disaster assessment, and other tasks to provide key information for relevant decision-making. For example, CN202420384206.8 discloses a hydrogen fuel cell drone (publication date 2024-11-22); CN202311395596.5 discloses a hydrogen fuel cell drone (publication date 2023-12-19); CN201821103489.5 discloses a hydrogen fuel cell external device for a multi-rotor drone (publication date 2019-06-07);

[0005] Although hydrogen fuel cells provide drones with longer flight time and higher energy density, traditional hydrogen fuel cell drones still have problems with short flight distance and insufficient endurance. Although hydrogen fuel cells have a high energy density, their system efficiency is still affected by many factors, such as the stack performance of the onboard hydrogen energy group, hydrogen utilization, auxiliary power weight configuration, etc. At the same time, the storage and transportation of hydrogen requires special equipment and conditions, which increases the overall weight and cost of the drone.

[0006] To this end, a large-load and long-endurance hydrogen fuel cell UAV is proposed. Summary of the invention

[0007] In view of this, the embodiments of the present invention hope to provide a large-load and long-endurance hydrogen fuel cell drone to solve or alleviate the technical problems existing in the prior art, namely, how to increase the cruising distance of hydrogen energy drones, and at least provide a beneficial option for this;

[0008] The technical solution of the present invention is implemented as follows: a large-load, long-endurance hydrogen fuel cell drone, mainly composed of a drone body UAV1, a cargo hold 2, a hydrogen fuel cell group 3, an unlocking component 4, and a traction air supply pipe 8. The drone body UAV1 is designed with a special installation space to accommodate the hydrogen fuel cell group 3, which converts hydrogen into electrical energy through an electrochemical reaction to provide power for the drone. One end of the traction air supply pipe 8 is connected to a ground pump station, and the other end is connected to the hydrogen fuel cell group 3 through a special interface to achieve a continuous supply of hydrogen. The unlocking component 4 is installed at the connection between the drone and the traction air supply pipe 8, and can quickly and safely disconnect the connection between the two according to instructions. In actual applications, the drone is connected to the ground pump station through the traction air supply pipe 8 before taking off to ensure a stable supply of hydrogen. When the drone needs to perform a specific task or enter a complex environment, the unlocking component 4 will be activated to separate the traction air supply pipe 8 from the hydrogen fuel cell group 3, and the drone can fly freely.

[0009] When in use, the UAV1 obtains energy based on the continuous gas supply to the hydrogen fuel cell group 3 by the pump station and the traction gas supply pipe 8; the maximum flight altitude, distance, etc. of the UAV1 depend on the length of the traction gas supply pipe 8, so the UAV1 is suitable for automatic cruising missions in uninhabited areas; when necessary, the unlocking component 4 disconnects the traction gas supply pipe 8 from the hydrogen fuel cell group 3 to allow the UAV1 to perform specific flight missions.

[0010] In one embodiment: UAV1 (unmanned aerial vehicle) can be of various types to adapt to different application scenarios and mission requirements. Specifically, UAV1 can be a multi-rotor unmanned aerial vehicle, which generates lift through multiple rotors, has the ability to hover, take off and land vertically, and flexibly turn, and is very suitable for delicate operations in complex environments; UAV1 can also be a fixed-wing unmanned aerial vehicle, which has a high flight speed and a long flight distance, and is suitable for large-scale, long-distance cruise missions; in addition, UAV1 can also be a vertical take-off and landing unmanned aerial vehicle, which combines the advantages of multi-rotor and fixed-wing unmanned aerial vehicles, and can take off and land vertically and fly efficiently in the air; unmanned helicopters have stronger load capacity and more stable flight performance, and are suitable for scenarios that require carrying a large amount of equipment or performing high-precision operations; unmanned airships and unmanned paragliders are suitable for specific low-altitude flights and long-term hovering tasks, such as environmental monitoring, geographic surveying and mapping, etc. In practical applications, the most suitable type of unmanned aerial vehicle can be selected as UAV1 according to the specific needs of the task and the on-site environment.

[0011] In one embodiment: UAV1 (unmanned aerial vehicle) is integrated with multiple key components to enhance its functionality and application scope. First, UAV1 is equipped with a high-definition camera unit 5, which usually includes a high-resolution camera, an image processor and a storage device, and can capture and record video and image data during flight in real time. The installation position and design of the camera unit 5 take into account the flight stability and shooting angle of the unmanned aerial vehicle to ensure the acquisition of high-quality and clear image data. Secondly, UAV1 is also equipped with an advanced flight controller 6, which is the "brain" of the unmanned aerial vehicle, responsible for receiving and processing data from various sensors, such as gyroscopes, accelerometers, GPS, etc., and controlling the flight attitude, speed and direction of the unmanned aerial vehicle according to preset flight plans and real-time instructions. Finally, UAV1 is also integrated with a wireless communication unit 7, which supports a variety of wireless communication protocols, such as Wi-Fi, 4G / 5G networks, etc., for real-time data transmission and communication with a ground control station or other unmanned aerial vehicles, including flight status, shooting data, control instructions, etc.

[0012] In one embodiment, the hydrogen fuel cell group 3 is the core energy supply component of the drone, and its structural design is compact and efficient. The hydrogen fuel cell group 3 includes a sturdy cabin 301, which is used to protect the internal core components and is easy to install on the drone. The cabin 301 is equipped with a hydrogen fuel cell 302, which is a key component for converting hydrogen into electrical energy. The hydrogen inlet end of the hydrogen fuel cell 302 is connected to the gas supply system 303 through a precise pipeline to ensure a stable supply of hydrogen. The gas supply system 303 is designed with a plug-in interface that matches the gas core 801, so that the traction gas supply pipe 8 can be easily connected to the gas supply system 303 through the gas core 801, thereby realizing the transportation of hydrogen. When the drone needs to take off or perform a flight mission, the pump station pumps hydrogen to the gas core 801 through the traction gas supply pipe 8, and then enters the hydrogen inlet end of the hydrogen fuel cell 302 through the gas supply system 303, providing the necessary raw materials for the electrochemical reaction.

[0013] In one embodiment, the air supply system 303 is specially designed as a self-locking air supply pump. This design not only ensures the stability and safety of hydrogen during transportation, but also greatly improves the convenience of UAV operation. The self-locking air supply pump has the function of automatically locking and unlocking the air path. When the traction air supply pipe 8 is connected to the air core 801, the air path of the air supply pump flows normally, ensuring that the supply of hydrogen will not be interrupted due to unstable connection or external interference during unmanned flight. Similarly, when it is necessary to disconnect the traction air supply pipe 8 to perform a specific flight mission, the air path is locked to prevent leakage.

[0014] In one embodiment, the unlocking assembly 4 includes a servo electric cylinder 401 and a pneumatic claw 402 fixedly connected to its piston rod. This design not only ensures the stability and safety of the connection between the gas core 801 and the hydrogen inlet end of the hydrogen fuel cell 302, but also realizes the rapid and accurate unlocking of the gas core 801 under specific conditions. As a driving element, the servo electric cylinder 401 has precise control performance and stable output force, which can ensure that the pneumatic claw 402 is accurate and reliable when grasping and releasing the gas core 801. The pneumatic claw 402 can tightly grasp the gas core 801 through its special structural design to prevent it from falling off due to vibration or external interference during flight.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. Significantly improved cruising distance: By introducing a self-locking air supply pump and a flexible unlocking component, the technology of the present invention enables the UAV to quickly and safely disconnect from the towing air supply pipe when needed, thereby getting rid of the limitations of the ground air supply system. This enables the UAV to fly for a longer time and a longer distance, greatly expanding its application range.

[0017] 2. Enhanced stability of energy supply: The design of the self-locking air supply pump ensures the stability and continuity of hydrogen during transportation, reducing the risk of energy interruption due to connection problems. The use of pneumatic claws and servo cylinders further enhances the tightness and reliability of the connection, ensuring a stable supply of hydrogen.

[0018] 3. Improved energy conversion efficiency: The optimized hydrogen fuel cell design improves energy conversion efficiency, allowing more chemical energy to be converted into electrical energy. This not only extends the flight time of the drone, but also reduces energy waste and improves the energy efficiency of the overall system.

[0019] 4. Enhanced safety and reliability: The automatic locking and unlocking function reduces the need for manual intervention and the risk of operational errors. At the same time, the self-locking air supply pump will further self-lock the air path when disconnected to prevent hydrogen leakage, ensuring the safety and environmental protection of the system. The design of the unlocking component makes it faster and more accurate for the drone to connect and disconnect the towing air supply pipe. This design not only simplifies the operating process, but also improves the flexibility and adaptability of the drone, enabling it to better cope with various complex environments and mission requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a three-dimensional schematic diagram of the present invention;

[0022] Figure 2 It is a half-cutaway perspective schematic diagram of the present invention;

[0023] Figure 3 It is a three-dimensional schematic diagram of the cooperation between the hydrogen fuel cell group and the unlocking assembly of the present invention;

[0024] Figure 4 It is a three-dimensional schematic diagram of the cooperation between the unlocking component and the air core of the present invention.

[0025] Figure numerals: 1. UAV; 2. Cargo compartment; 3. Hydrogen fuel cell group; 301. Cabin; 302. Hydrogen fuel cell; 303. Air supply system; 4. Unlocking assembly; 401. Servo cylinder; 402. Pneumatic clamp; 5. Camera unit; 6. Flight controller; 7. Wireless communication unit; 8. Traction air supply pipe; 801. Air core. DETAILED DESCRIPTION

[0026] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below;

[0027] Example: The main reasons why the cruising range of conventional hydrogen fuel cell drones is limited include:

[0028] (1) Limited hydrogen storage: The amount of hydrogen carried by a drone directly limits its flight time.

[0029] (2) Energy conversion efficiency: The energy conversion efficiency of the hydrogen fuel cell and the stability of the hydrogen supply system will affect the endurance of the UAV.

[0030] (3) Connection stability: During flight, insufficient connection stability of the hydrogen supply system may result in hydrogen leakage or supply interruption.

[0031] To do this, see Figure 1-4 This embodiment discloses a large-load, long-endurance hydrogen fuel cell UAV, including a UAV1 and a cargo hold 2 carried by the UAV1, the UAV1 is powered by a hydrogen fuel cell group 3 carried inside the UAV1, and the hydrogen fuel cell group 3 is supplied with gas through a traction gas supply pipe 8 connected to a pump station on the ground;

[0032] The UAV 1 can detach the traction air supply pipe 8 from the hydrogen fuel cell stack 3 through the unlocking assembly 4;

[0033] When in use, UAV1 obtains energy based on the continuous gas supply from the pump station and the traction gas supply pipe 8 to the hydrogen fuel cell group 3; the maximum flight altitude, distance, etc. of UAV1 depend on the length of the traction gas supply pipe 8, so this UAV1 is suitable for automatic cruising missions in uninhabited areas; when necessary, the unlocking component 4 will disconnect the traction gas supply pipe 8 from the hydrogen fuel cell group 3 to allow UAV1 to perform specific flight missions.

[0034] Specifically: The core of this technology is to use a ground pump station to provide a continuous supply of hydrogen to the drone through the traction air supply pipe 8, thereby solving the problem of short endurance of traditional hydrogen fuel cell drones. The hydrogen fuel cell stack 3 converts hydrogen into electrical energy and thermal energy through an electrochemical reaction, where the electrical energy is used to drive the motor and other electronic equipment of the drone, and the thermal energy is discharged through the heat dissipation system. The design of the unlocking component 4 allows the drone to disconnect from the traction air supply pipe 8 when necessary, which is usually achieved through a mechanical or electromagnetic mechanism to ensure that no hydrogen leakage or damage occurs during the disconnection process. In this way, the drone can perform more flexible and extensive flight missions without being restricted by the traction air supply pipe 8.

[0035] Preferably, the traction air supply pipe 8 has an outer diameter of 1.34 mm, an inner diameter of 0.85 mm, a pipe wall wrapped with carbon fiber, and a tensile rupture strength of 250 kg.

[0036] It is understandable that in the above technical solution: through the continuous gas supply from the ground pump station and the traction air supply pipe 8, the UAV can achieve long-term and long-distance flight, which is particularly suitable for automatic cruising tasks in unmanned areas, such as environmental monitoring, border patrols, disaster assessments, etc. Secondly, the design of the unlocking component 4 enables the UAV to quickly detach from the traction air supply pipe 8 when performing specific tasks, thereby improving the flexibility of the task and the ability to respond to emergencies. In addition, as a clean energy source, hydrogen fuel cells only emit water, which is pollution-free to the environment and conforms to the concept of green and sustainable development.

[0037] In the technical solution provided in this embodiment, please refer to Figures 2 to 4 :UAV1 (unmanned aerial vehicle) can adopt various types to adapt to different application scenarios and mission requirements. Specifically, UAV1 can be a multi-rotor drone, which generates lift through multiple rotors and has the ability to hover, take off and land vertically, and flexibly turn, which is very suitable for delicate operations in complex environments; UAV1 can also be a fixed-wing drone, which has a high flight speed and a long flight distance, suitable for large-scale and long-distance cruising missions; in addition, UAV1 can also be a vertical take-off and landing drone, which combines the advantages of multi-rotor and fixed-wing drones, and can take off and land vertically and fly efficiently in the air; unmanned helicopters have stronger load capacity and more stable flight performance, which are suitable for scenarios that need to carry a large amount of equipment or perform high-precision operations; unmanned airships and unmanned paragliders are suitable for specific low-altitude flights and long-term hovering tasks, such as environmental monitoring, geographic surveying and mapping, etc. In actual applications, the most suitable type of drone can be selected as UAV1 according to the specific needs of the mission and the on-site environment.

[0038] Multi-rotor drones are suitable for urban environments, complex terrains, and delicate operations; fixed-wing drones are suitable for large-scale, long-distance cruising and monitoring tasks; vertical take-off and landing drones combine the advantages of the first two, and can be flexibly operated in urban environments and can fly long distances; unmanned helicopters are suitable for scenarios that require carrying heavy equipment or performing high-precision operations; unmanned airships and unmanned paragliders are suitable for low-altitude flights, long-term hovering, and specific environmental monitoring tasks. By selecting the appropriate type of drone as UAV1, and combining the design of hydrogen fuel cell stacks and traction air supply pipes, this technology can meet the application needs of drones in different fields and scenarios, and achieve more efficient and environmentally friendly flight operations.

[0039] Preferably, the outer shell of the hydrogen fuel cell stack 3 is the outer shell of the UAV 1; a pipeline for gas supply is arranged in the outer shell of the hydrogen fuel cell stack 3, thereby further improving the quality and efficiency advantages.

[0040] In the technical solution provided in this embodiment, please refer to Figure 2-4 :UAV1 is equipped with a camera unit 5 for filming. UAV1 is equipped with a flight controller 6 for flight control. UAV1 is equipped with a wireless communication unit 7 for wireless communication.

[0041] Specifically: The working principle of the camera unit 5 is based on optical imaging technology. The camera captures external light and converts it into electrical signals, which are then digitized, compressed and stored by the image processor. The flight controller 6 is based on advanced control algorithms and sensor fusion technology. It calculates the best control instructions by analyzing the flight status and environmental information of the drone in real time, and realizes precise control of the drone through actuators such as motor drivers and servos. The wireless communication unit 7 uses radio waves for data transmission, converts digital signals into analog signals suitable for wireless transmission through modulation and demodulation technology, and then transmits and receives through antennas to achieve communication connection with the ground or other drones. The integration and working principles of these components together constitute the core functional system of UAV1.

[0042] It is understandable that in the above technical solution: the addition of the camera unit 5 enables UAV1 to have powerful shooting and recording capabilities, which can be widely used in environmental monitoring, geographic mapping, disaster assessment, agricultural plant protection and other fields, providing users with high-quality image data. The high-precision control capability and stability of the flight controller 6 ensure the safe flight and precise operation of the UAV in complex environments, and improve the reliability and efficiency of the UAV. The wireless communication unit 7 realizes real-time data transmission and remote control between the UAV and the ground control station, so that users can grasp the flight status and mission progress of the UAV at any time, and adjust or intervene as needed.

[0043] In the technical solution provided in this embodiment, please refer to Figure 2-4 : The hydrogen fuel cell group 3 includes a cabin 301 and a hydrogen fuel cell 302 mounted therein, the hydrogen inlet end of the hydrogen fuel cell 302 is connected to the gas supply system 303, the gas supply system 303 is connected to the gas core 801 by plugging and unplugging, and the gas core 801 is connected to the traction gas supply pipe 8;

[0044] Specifically: The working principle of the hydrogen fuel cell 302 is based on electrochemical reactions, and its internal structure includes an anode, a cathode, and an electrolyte membrane. After hydrogen is input into the hydrogen fuel cell 302, the hydrogen undergoes an oxidation reaction on the anode and is decomposed into hydrogen ions and electrons. These electrons flow to the cathode (negative electrode) through an external circuit, forming an electric current to provide electrical energy for the drone. At the same time, hydrogen ions migrate to the cathode through an electrolyte membrane (usually a special film that allows hydrogen ions to pass through and prevents electrons from passing through). At the cathode, hydrogen ions combine with oxygen introduced from the air, undergo a reduction reaction to generate water, and release a large amount of heat energy. The potential difference (ie, voltage) generated in this process drives the flow of current in the external circuit, thereby realizing the conversion of chemical energy to electrical energy. This conversion process is efficient and environmentally friendly, only produces water as a byproduct, and does not pollute the environment.

[0045] It is understandable that in the above technical solution: the hydrogen fuel cell group 3 is used as the power source of the UAV, and its efficient and environmentally friendly energy conversion method enables the UAV to achieve long-term and long-distance flight. By traction of the air supply pipe 8 and the connection with the ground pump station, the UAV can continuously obtain hydrogen supply during the flight, thereby avoiding the problem of short battery life of traditional batteries. In addition, the high energy density and stable output performance of the hydrogen fuel cell 302 ensure the stable flight and efficient operation of the UAV in various complex environments. At the same time, since the emission of the hydrogen fuel cell is only water, this type of UAV also has significant advantages in environmental protection, and is particularly suitable for application scenarios with high requirements for environmental protection, such as environmental monitoring, ecological protection, etc. By continuously optimizing the design and performance of the hydrogen fuel cell group 3, the endurance and operating efficiency of the UAV can be further improved, providing strong support for the widespread application of UAVs.

[0046] In the technical solution provided in this embodiment, please refer to Figure 2-4 : The air supply system 303 is specially designed as a self-locking air supply pump. This design not only ensures the stability and safety of hydrogen during transportation, but also greatly improves the convenience of UAV operation. The self-locking air supply pump has the function of automatically locking and unlocking the air path. When the traction air supply pipe 8 is connected to the air core 801, the air path of the air supply pump flows normally, ensuring that the supply of hydrogen will not be interrupted due to unstable connection or external interference during unmanned flight. Similarly, when it is necessary to disconnect the traction air supply pipe 8 to perform a specific flight mission, the air path is locked to prevent leakage.

[0047] In the technical solution provided in this embodiment, please refer to Figures 2 to 4 : The unlocking component 4 includes a servo electric cylinder 401 and a pneumatic claw 402 fixedly connected to its piston rod; the pneumatic claw 402 grabs the air core 801.

[0048] Under normal conditions, since the gas core 801 and the hydrogen inlet end of the hydrogen fuel cell 302 are plug-in connected, the pneumatic clamp 402 should hold the gas core 801 tightly and the piston rod of the servo electric cylinder 401 is at the initial end of the stroke to prevent the gas core 801 from falling; when it is necessary for UAV1 to perform special flight missions, the piston rod of the servo electric cylinder 401 is extended to the limit end of the stroke to disengage the gas core 801 from the self-locking air supply pump. At this time, the self-locking air supply pump further self-locks the air path to prevent hydrogen leakage; then the pneumatic clamp 402 releases the gas core 801, so that the gas core 801 and the traction air supply pipe 8 are separated from the UAV1.

[0049] Specifically: Under normal conditions, since the gas core 801 and the hydrogen inlet end of the hydrogen fuel cell 302 are connected by plugging, in order to ensure the stability of the connection and prevent the gas core 801 from falling, the pneumatic claw 402 will hold the gas core 801 tightly, and the piston rod of the servo electric cylinder 401 will remain at the initial end of the stroke. In this state, even if the drone encounters turbulence or vibration during flight, the pneumatic claw 402 can ensure that the gas core 801 will not fall off, thereby ensuring a stable supply of hydrogen.

[0050] Furthermore, the hydrogen fuel cell 302 is electrically connected to the propeller assembly (motor) of UAV1 through electrical wires.

[0051] When the unmanned aerial vehicle UAV1 needs to perform a special flight mission, such as disconnecting from the traction air supply pipe 8 for free flight, the unlocking component 4 will receive the corresponding control command. At this time, the piston rod of the servo electric cylinder 401 will extend to the stroke limit end, and the pneumatic claw 402 will be driven to move through mechanical transmission, so that the air core 801 gradually disengages from the self-locking air supply pump. At the same time, the self-locking air supply pump will further self-lock the air path to ensure that hydrogen will not leak during the disconnection process. When the air core 801 is completely separated from the self-locking air supply pump, the pneumatic claw 402 will release the grip on the air core 801, so that the air core 801 can be smoothly disconnected from the traction air supply pipe 8, thereby realizing the free flight of the unmanned aerial vehicle.

[0052] It can be understood that in the above technical solution: the design of the unlocking component 4 not only improves the operating efficiency and convenience of the UAV when connecting and disconnecting the traction air supply pipe 8, but also ensures the stability and safety of the hydrogen supply. The coordinated use of the servo cylinder 401 and the pneumatic claw 402 makes the unlocking process more precise and reliable, avoiding safety hazards such as hydrogen leakage or supply interruption caused by connection problems. At the same time, this design also enhances the adaptability and flexibility of the UAV, enabling it to better cope with various complex environments and mission requirements. For example, when long-distance cruising or monitoring of a specific area is required, the UAV can achieve a freer and more flexible flight by quickly disconnecting from the traction air supply pipe 8.

[0053] The parameters of the drone described in this embodiment are as follows:

[0054] model 4 rotors Wheelbase 1508mm span 2108mm Rack weight 16kg Maximum load 15kg Maximum take-off weight 31kg Maximum cruising range without load 480min Maximum load endurance 80min power 1200W

[0055] The fuel cell stack parameters of the hydrogen fuel cell group 3 described in this embodiment are as follows:

[0056]

[0057]

[0058] In summary, in response to the related problems in the traditional technology, this specific implementation is based on the large-load and long-endurance hydrogen fuel cell drone provided above, and adopts the following technical means or features to achieve the solution:

[0059] The ground pump station (which can be fixed or equipped with other unmanned or manned vehicles for cruising) continuously supplies energy to UAV1 (i.e., hydrogen fuel cell group 3), so that when UAV1 is in a normal hovering state, the amount of hydrogen stored in the hydrogen fuel cell group 3 will basically not change. When the UAV needs to perform special tasks or fly long distances, the unlocking component 4 can quickly and accurately disconnect the air core 801 from the self-locking air supply pump. This makes the overall hovering time of UAV1 longer to meet the needs of large load and long endurance. This mechanism allows the UAV to fly freely without being restricted by the traction air supply pipe 8, thereby greatly increasing its cruising distance.

[0060] The automatic locking and unlocking function of the unlocking component 4 reduces the need for manual intervention, reduces the risk of operating errors, and improves the safety and reliability of the system. During the disconnection process, the self-locking gas supply pump will further self-lock the gas path to prevent hydrogen leakage, ensuring the safety and environmental protection of the system.

[0061] The above-mentioned embodiments only express the implementation methods of the relevant practical applications of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be subject to the attached claims.

Claims

1. A large-load, long-endurance hydrogen fuel cell drone, comprising a UAV (1) and a cargo hold (2) carried thereon, wherein the UAV (1) is powered by a hydrogen fuel cell stack (3) carried therein, and is characterized in that: The hydrogen fuel cell group (3) is supplied with gas through a traction gas supply pipe (8) connected to a pump station on the ground; The UAV (1) can detach the traction air supply pipe (8) from the hydrogen fuel cell group (3) through an unlocking component (4).

2. The drone according to claim 1, characterized in that: The UAV (1) is one of a multi-rotor UAV, a fixed-wing UAV, a vertical take-off and landing UAV, an unmanned helicopter, an unmanned airship or an unmanned paraglider; the outer shell of the hydrogen fuel cell group (3) is the outer shell of the UAV (1); A pipeline for gas supply is arranged in the shell of the hydrogen fuel cell group (3).

3. The drone according to claim 2, characterized in that: The UAV (1) is equipped with a camera unit (5) for filming.

4. The drone according to claim 2, characterized in that: The UAV (1) is equipped with a flight controller (6) for flight control.

5. The drone according to claim 2, characterized in that: The UAV (1) is equipped with a wireless communication unit (7) for wireless communication.

6. The drone according to claim 1, characterized in that: The hydrogen fuel cell group (3) comprises a cabin (301) and a hydrogen fuel cell (302) mounted therein, wherein a hydrogen inlet end of the hydrogen fuel cell (302) is connected to a gas supply system (303); The air supply system (303) is connected to the air core (801) by plugging and unplugging, and the air core (801) is connected to the traction air supply pipe (8); The hydrogen fuel cell (302) is electrically connected to the propeller assembly of the UAV (1) via electrical wires.

7. The drone according to claim 6, characterized in that: The air supply system (303) is a self-locking air supply pump.

8. The drone according to claim 6, characterized in that: The unlocking assembly (4) comprises a servo electric cylinder (401) and a pneumatic claw (402) fixedly connected to its piston rod; The pneumatic claw (402) grasps the pneumatic core (801).

9. The drone according to any one of claims 1 to 8, characterized in that: The traction air supply pipe (8) has an outer diameter of 1.34 mm and an inner diameter of 0.85 mm, and the pipe wall is wrapped with carbon fiber.

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