High-power and large-load solid-gas coupling hydrogen energy unmanned aerial vehicle

Abstract

The invention discloses a high-power and large-load solid-gas coupling hydrogen energy unmanned aerial vehicle, and relates to the field of unmanned aerial vehicles, the high-power and large-load solid-gas coupling hydrogen energy unmanned aerial vehicle comprises a main body, a cover plate is fixedly connected to the top of the main body, and a cabin door is rotatably connected to the bottom of the main body through a hinge; a hydrogen storage assembly for improving the cruising ability and the energy utilization efficiency of the unmanned aerial vehicle is arranged at the top of the heat conduction plate, a fuel cell assembly is arranged at the top of the heat conduction plate, a grabbing assembly for automatically grabbing goods is arranged at the bottom of the heat conduction plate, and heat dissipation grooves are symmetrically formed in the outer wall of the main body; by arranging the heat dissipation assembly, real-time adjustment of the angle of the heat dissipation plate can be achieved, the heat dissipation efficiency can be optimized according to the flight state of the unmanned aerial vehicle, the adjustment accuracy of the heat dissipation plate is ensured, energy waste caused by excessive heat dissipation or system overheating caused by insufficient heat dissipation is avoided, when the heat dissipation plate is unfolded, the flow guide wing effect can be formed, hot air exhaust is accelerated, and the heat dissipation efficiency of the unmanned aerial vehicle is improved. During closing, airflow interference is reduced, and flight resistance is reduced.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a high-power, high-payload solid-gas coupled hydrogen-powered UAV. Background Technology

[0002] With the increasing global demand for clean energy and energy-efficient technologies, hydrogen energy, as a clean, efficient, and renewable energy source, has broad application prospects in the field of drones. However, most traditional drones use lithium batteries or fossil fuels as power sources, which have problems such as short flight time, low energy efficiency, and environmental pollution. Hydrogen-powered drones, with their advantages of high energy density, zero emissions, and long flight time, have become an important way to solve the above problems. In hydrogen storage technology for hydrogen-powered drones, solid-state hydrogen storage and gaseous hydrogen storage each have their own advantages and disadvantages. Solid-state hydrogen storage has advantages such as high hydrogen storage density, good safety, and simple operation, but it has problems such as slow hydrogen release rate and complex system. Gaseous hydrogen storage, on the other hand, has advantages such as fast hydrogen release rate and mature technology, but its hydrogen storage density is relatively low and there are safety hazards. Summary of the Invention

[0003] (a) Technical problems to be solved To address the problems existing in the prior art, the present invention provides a high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle.

[0004] (II) Technical Solution To achieve the above objectives, the present invention provides the following technical solution: a high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle (UAV), comprising a main body, a cover plate fixedly connected to the top of the main body, a hatch rotatably connected to the bottom of the main body via a hinge, a heat-conducting plate fixedly connected inside the main body, a hydrogen storage component that improves the UAV's endurance and energy utilization efficiency being provided on the top of the heat-conducting plate, a fuel cell component being provided on the top of the heat-conducting plate, a gripping component for automatically grasping cargo being provided at the bottom of the heat-conducting plate, heat dissipation grooves symmetrically formed on the outer wall of the main body, heat dissipation plates being rotatably connected at equal intervals via bearings inside the heat dissipation grooves, a quick-release component for quickly assembling and disassembling the cover plate being provided on the top of the main body, and a heat dissipation component for adjusting the heat dissipation angle of the heat dissipation plates being provided at the bottom of the heat-conducting plate; The heat dissipation assembly includes fixed plates symmetrically fixedly connected inside the heat dissipation groove. Three rotating seats are equidistantly connected to the sides of the two fixed plates that are close to each other via bearings. The outer walls of the rotating seats are fixedly connected to the outer walls of the heat-conducting plates. Limiting posts are fixedly connected to the sides of the three rotating seats that are away from the fixed plates. Connecting strips are rotatably connected to the outer walls of the limiting posts via bearings. A driving assembly for driving the connecting strips to rotate is provided on the outer wall of one of the fixed plates.

[0005] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the drive assembly includes a fixed column fixedly connected to the outer wall of a fixed plate. The outer wall of the fixed column is rotatably connected to a first electric push rod via a bearing. The output end of the first electric push rod is fixedly connected to a drive seat. The interior of the drive seat is rotatably connected to the outer wall of one of the limiting columns via a bearing.

[0006] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the gripping component includes two electrically operated telescopic rods symmetrically and fixedly connected to the inner side of the main body. A lifting plate is fixedly connected to the output end of each of the electrically operated telescopic rods. A connecting column is fixedly connected to the bottom of the lifting plate. A connecting disc is rotatably connected to the outer wall of the connecting column via a bearing. Clamping claws are symmetrically and slidably connected to the bottom of the lifting plate. Limiting strips are symmetrically and rotatably connected to the inside of the connecting disc via bearings. The end of the limiting strip away from the connecting disc is rotatably connected to the outer wall of the clamping claw via a bearing. A groove is formed at the bottom of the lifting plate. A second electrically operated push rod is fixedly connected inside the groove. A connecting plate is fixedly connected to the outer wall of one of the clamping claws. The outer wall of the connecting plate is slidably connected to the inner side of the groove. The output end of the second electrically operated push rod is fixedly connected to the outer wall of the connecting plate.

[0007] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the bottom of the lifting plate is symmetrically and fixedly connected to two guide rails, and the top of the clamping claw is slidably connected to the outer wall of the guide rails.

[0008] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the quick-release assembly includes symmetrically formed slots inside the main body. A sliding groove is formed on the side of the cover plate near the slots. A locking block is slidably connected to the inner side of the sliding groove. A limiting rod is fixedly connected to the side of the locking block away from the slots. A limiting spring is sleeved on the outer side of the limiting rod. A toggle groove is symmetrically formed on the top of the cover plate. A toggle block is fixedly connected to the outer wall of the limiting rod. The upper end of the toggle block extends to the top of the cover plate and is slidably connected to the inner side of the toggle groove. The locking block engages with the slots.

[0009] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle described in this invention, the end of the limiting spring away from the limiting rod is fixedly connected to the inner side of the sliding groove, and the other end of the limiting spring is fixedly connected to the outer wall of the limiting rod.

[0010] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the hydrogen storage component includes a solid-state hydrogen storage module and a gaseous hydrogen storage module. The solid-state hydrogen storage module uses advanced solid-state hydrogen storage materials of metal hydrides with high hydrogen storage density to ensure high energy density while providing a stable hydrogen supply. The gaseous hydrogen storage module uses a high-pressure gas cylinder hydrogen storage tank to supplement the shortcomings of the solid-state hydrogen storage module in rapid hydrogen release and to serve as a backup energy source.

[0011] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered UAV described in this invention, the fuel cell assembly is made of carbon fiber composite material, which enables the fuel cell system to have a high power density, which is 2 to 3 times that of a power battery system of the same weight, and can provide longer flight time and greater payload capacity.

[0012] As a preferred embodiment of the high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle (UAV) of the present invention, the outer wall of the main body is provided with a plurality of wings at equal intervals, the bottom of the main body is symmetrically and fixedly connected with a support frame, and the outer wall of the support frame is symmetrically and fixedly connected with an anti-slip sleeve.

[0013] As a preferred embodiment of the high-power, heavy-load solid-gas coupled hydrogen-powered unmanned aerial vehicle described in this invention, two illumination lamps are symmetrically fixedly connected to the bottom of the main body.

[0014] (III) Beneficial Effects This invention provides a high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle (UAV). It possesses the following beneficial effects: 1. By setting up heat dissipation components, the angle of the heat dissipation plate can be adjusted in real time. The heat dissipation efficiency can be optimized according to the flight status of the UAV, ensuring the accuracy of the heat dissipation plate adjustment and avoiding energy waste due to excessive heat dissipation or system overheating due to insufficient heat dissipation. When the heat dissipation plate is deployed, it can form a "guide wing" effect to accelerate the discharge of hot air. When it is closed, it reduces airflow interference and reduces flight drag. 2. By setting up hydrogen storage components, it is possible to fly for longer periods of time without changing energy sources or refueling, and to complete missions over a wider area. This reduces the trouble of mission interruptions due to insufficient energy or frequent returns to refuel, and improves work efficiency. 3. By setting up gripping components, it can operate at different heights, easily handling both picking up goods from the ground and operating on targets at heights, greatly improving the utilization rate of warehouse space and the efficiency of goods handling; 4. By setting up quick-release components, the module that needs maintenance can be quickly and accurately located, thereby quickly determining whether there are problems such as overheating or short circuits, and carrying out targeted repairs, which improves the accuracy and efficiency of maintenance. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0017] Figure 2 This is a schematic diagram of the heat dissipation groove of the present invention.

[0018] Figure 3 This is a schematic diagram of the structure of the illumination lamp of the present invention.

[0019] Figure 4 This is a schematic diagram of the gripping component of the present invention.

[0020] Figure 5 This is a schematic diagram of the hydrogen storage component of the present invention.

[0021] Figure 6 This is a schematic diagram of the connecting disk of the present invention.

[0022] Figure 7 This is a schematic diagram of the card slot structure of the present invention.

[0023] Figure 8 This is the present invention. Figure 7 Enlarged view of point A in the middle.

[0024] Figure 9 This is a structural schematic diagram of the quick-release component of the present invention.

[0025] In the diagram: 1. Main body; 2. Cover plate; 3. Door; 4. Heat conduction plate; 5. Hydrogen storage assembly; 501. Solid hydrogen storage module; 502. Gaseous hydrogen storage module; 6. Fuel cell assembly; 7. Gripping assembly; 701. Electric telescopic rod; 702. Lifting plate; 703. Connecting column; 704. Connecting plate; 705. Clamping claw; 706. Limiting strip; 707. Groove; 708. Second electric push rod; 709. Connecting plate; 8. Quick release assembly; 801. Slot. 802. Sliding groove; 803. Locking block; 804. Limiting rod; 805. Limiting spring; 806. Actuating groove; 807. Actuating block; 9. Heat dissipation assembly; 901. Fixing plate; 902. Rotating seat; 903. Limiting post; 904. Connecting strip; 10. Drive assembly; 1001. Fixing post; 1002. First electric push rod; 1003. Drive seat; 11. Wing; 12. Support frame; 13. Illuminating lamp; 14. Heat dissipation groove; 15. Heat dissipation plate. Detailed Implementation

[0026] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0027] Example 1 Reference Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 7 and Figure 8 This is the first embodiment of the present invention, which provides a high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle (UAV), including a main body 1. A cover plate 2 is fixedly connected to the top of the main body 1, and a hatch 3 is rotatably connected to the bottom of the main body 1 via a hinge. A heat-conducting plate 4 is fixedly connected inside the main body 1. A hydrogen storage component 5, which improves the UAV's endurance and energy utilization efficiency, is disposed on the top of the heat-conducting plate 4. A fuel cell component 6 is disposed on the top of the heat-conducting plate 4, and a gripping component 7 for automatically gripping cargo is disposed at the bottom of the heat-conducting plate 4. Heat dissipation grooves 14 are symmetrically formed on the outer wall of the main body 1, and heat dissipation plates 15 are rotatably connected to the heat dissipation grooves 14 at equal intervals via bearings. A cover plate 3 is disposed on the top of the main body 1 for quick cover opening. The quick-release assembly 8 for disassembling and assembling plate 2, and the heat dissipation assembly 9 at the bottom of heat conduction plate 4 for adjusting the heat dissipation angle of heat dissipation plate 15. The heat dissipation assembly 9 includes a fixed plate 901 symmetrically fixedly connected inside the heat dissipation groove 14. Three rotating seats 902 are equidistantly connected to the side of the two fixed plates 901 that are close to each other through bearings. The outer wall of the rotating seats 902 is fixedly connected to the outer wall of heat conduction plate 4. Limiting posts 903 are fixedly connected to the side of the three rotating seats 902 away from the fixed plate 901. The outer wall of the limiting post 903 is rotatably connected to the connecting strip 904 through bearings. The outer wall of one of the fixed plates 901 is provided with a driving assembly 10 for driving the connecting strip 904 to rotate.

[0028] Specifically, the drive assembly 10 includes a fixed column 1001 fixedly connected to the outer wall of the fixed plate 901. A first electric push rod 1002 is rotatably connected to the outer wall of the fixed column 1001 via a bearing. A drive seat 1003 is fixedly connected to the output end of the first electric push rod 1002. The interior of the drive seat 1003 is rotatably connected to the outer wall of one of the limiting columns 903 via a bearing. The hydrogen storage assembly 5 includes a solid-state hydrogen storage module 501 and a gaseous hydrogen storage module 502. The solid-state hydrogen storage module 501 uses advanced solid-state hydrogen storage materials with high hydrogen storage density, ensuring high energy density while providing a stable hydrogen supply. The gaseous hydrogen storage module 502 uses a high-pressure gas cylinder hydrogen storage tank to supplement the shortcomings of the solid hydrogen storage module 501 in rapid hydrogen release and to serve as a backup energy source. The fuel cell assembly 6 uses carbon fiber composite material, which gives the fuel cell system a high power density, which is 2 to 3 times that of a power battery system of the same weight, and can provide longer driving time and greater load capacity. Several wings 11 are equidistantly arranged on the outer wall of the main body 1. A support frame 12 is symmetrically fixedly connected to the bottom of the main body 1. Anti-slip sleeves are symmetrically fixedly connected to the outer wall of the support frame 12. Two illumination lamps 13 are symmetrically fixedly connected to the bottom of the main body 1.

[0029] Furthermore, when the drone encounters situations requiring rapid acceleration, climbing, or high-load tasks that drastically increase energy demand, the hydrogen release rate of the solid-state hydrogen storage module 501 may not be able to meet the high power requirements of the fuel cell in time. At this point, the gaseous hydrogen storage module 502 comes into play. The gaseous hydrogen storage module 502 uses a high-pressure gas cylinder storage tank, which can rapidly release a large amount of hydrogen in a short time to supplement the insufficient hydrogen release of the solid-state hydrogen storage module 501, ensuring that the fuel cell has a sufficient hydrogen supply to maintain stable power output and guarantee the normal operation of the drone under various working conditions. Simultaneously, the gaseous hydrogen storage module 502 also serves as a backup energy source. When the solid-state hydrogen storage module 501 malfunctions or its hydrogen storage is insufficient, it can promptly step in to provide necessary energy support for the drone, improving its reliability and safety. After hydrogen is transported from the hydrogen storage component 5 to the fuel cell component 6, a chemical reaction occurs inside the fuel cell. At the anode, hydrogen is decomposed into protons and electrons. Protons migrate to the cathode through the electrolyte membrane, while electrons form an electric current through the external circuit. The system provides power to the drone's motors, control system, and other components. During flight, internal components such as the fuel cell assembly 6 generate a significant amount of heat. This heat is first transferred to the heat-conducting plate 4 inside the main body 1 via thermal conduction. The heat-conducting plate 4 has excellent thermal conductivity, enabling it to quickly absorb and conduct heat to its bottom. When the internal temperature is detected to be too high or the external ambient temperature is favorable for heat dissipation, the extension or retraction of the first electric push rod 1002 is activated. This, in turn, drives the rotating seat 902 to rotate via the drive seat 1003, the limiting post 903, and the connecting bar 904. This changes the heat dissipation angle of the heat sink 15. When the heat sink 15 rotates to a larger heat dissipation angle, its contact area with the air increases, allowing it to dissipate heat more effectively into the surrounding environment. Conversely, when the internal temperature of the drone is low or the external ambient temperature is low, and a large amount of heat dissipation is not required, the control system controls the first electric push rod 1002 to rotate the heat sink 15 to a smaller heat dissipation angle, reducing unnecessary heat loss, maintaining a suitable internal temperature for the drone, and improving energy efficiency.

[0030] Example 2 Reference Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 6 , Figure 7 and Figure 9This is the second embodiment of the present invention, which is based on the previous embodiment. The gripping component 7 includes two electric telescopic rods 701 symmetrically and fixedly connected to the inner side of the main body 1. The output end of the electric telescopic rod 701 is fixedly connected to a lifting plate 702. The bottom of the lifting plate 702 is fixedly connected to a connecting column 703. The outer wall of the connecting column 703 is rotatably connected to a connecting disk 704 through a bearing. The bottom of the lifting plate 702 is symmetrically and slidably connected to a gripping claw 705. The inside of the connecting disk 704 is symmetrically and rotatably connected to a limiting strip 706 through a bearing. The end of the limiting strip 706 away from the connecting disk 704 is rotatably connected to the outer wall of the gripping claw 705 through a bearing. The bottom of the lifting plate 702 has a groove 707. The inside of the groove 707 is fixedly connected to a second electric push rod 708. The outer wall of one of the gripping claws 705 is fixedly connected to a connecting plate 709. The outer wall of the connecting plate 709 is slidably connected to the inner side of the groove 707. The output end of the second electric push rod 708 is fixedly connected to the outer wall of the connecting plate 709.

[0031] Specifically, the bottom of the lifting plate 702 is symmetrically fixedly connected to two guide rails, and the top of the clamping claw 705 is slidably connected to the outer wall of the guide rails. The quick-release assembly 8 includes symmetrical slots 801 inside the main body 1. A sliding groove 802 is provided on the side of the cover plate 2 near the slot 801. A locking block 803 is slidably connected inside the sliding groove 802. A limit rod 804 is fixedly connected on the side of the locking block 803 away from the slot 801. A limit spring 805 is sleeved on the outer side of the limit rod 804. The top of the cover plate 2 is... The device is equipped with an actuation groove 806. An actuation block 807 is fixedly connected to the outer wall of the limiting rod 804. The upper end of the actuation block 807 extends to the top of the cover plate 2 and is slidably connected to the inner side of the actuation groove 806. A locking block 803 is engaged with the locking groove 801. One end of the limiting spring 805 away from the limiting rod 804 is fixedly connected to the inner side of the sliding groove 802. The other end of the limiting spring 805 is fixedly connected to the outer wall of the limiting rod 804. An electromagnetic valve is installed inside the main body 1 and is electrically connected to the hatch 3.

[0032] Furthermore, when the drone reaches the target cargo and needs to grab it, it first opens the hatch 3 via the solenoid valve, then activates the electric telescopic rod 701 to retract, causing the lifting plate 702 to move downwards. Once it reaches the appropriate position, the output end of the second electric push rod 708 extends, pushing the connecting plate 709, which is fixedly connected to it, to slide within the groove 707. Because the connecting plate 709 is fixedly connected to one of the gripping claws 705, the gripping claw 705 will move to one side under the guidance of the guide rail. Simultaneously, because one end of the limiting strip 706 is rotatably connected to the outer wall of the gripping claw 705, the other end... The connecting plate 704 is rotatably connected. When the gripping claw 705 moves, it drives the connecting plate 704 to rotate around the connecting post 703 via the limiting strip 706. The rotation of the connecting plate 704, in turn, drives another gripping claw 705 to move in the opposite direction via another set of limiting strips 706, thereby causing the two gripping claws 705 to move away from each other and open. When the gripping claw 705 is open enough to completely surround the target goods, the electric telescopic rod 701 continues to descend. Then, the output end of the second electric push rod 708 retracts, pulling the connecting plate 709 and the gripping claw 705 connected to it. Moving in the opposite direction, similarly, through the transmission action of the limit bar 706 and the connecting plate 704, the other gripping claw 705 also moves towards the center. The two gripping claws 705 gradually approach and clamp the target cargo. During the clamping process, after successfully grabbing the cargo, the electric telescopic rod 701 extends, driving the lifting plate 702 and the cargo to move upward, grabbing the grabbed cargo into the main body 1. Then, the solenoid valve drives the hatch 3 to close. When it is necessary to remove the cover plate 2, the operation is performed by moving the actuating block 807 on the top of the cover plate 2. The actuating block 807 slides in the actuating groove 806. The movement of the limiting rod 804 causes it to move away from the slot 801. The movement of the limiting rod 804 causes the locking block 803 to move inward into the sliding groove 802, while compressing the limiting spring 805. As the actuating block 807 continues to move, the locking block 803 gradually moves out of the slot 801. When the locking block 803 is completely disengaged from the slot 801, the locking connection between the cover plate 2 and the main body 1 is released. At this time, the cover plate 2 can move freely in the vertical direction. After the locking block 803 is disengaged from the slot 801, the cover plate 2 can be gently lifted upward by hand to remove it from the main body 1.

[0033] Working principle: When the drone encounters situations that require a rapid increase in energy demand, such as rapid acceleration, climbing, or performing high-load tasks, the hydrogen release rate of the solid hydrogen storage module 501 may not be able to meet the high power demand of the fuel cell in time. At this time, the gaseous hydrogen storage module 502 comes into play. The gaseous hydrogen storage module 502 uses a high-pressure gas cylinder hydrogen storage tank, which can quickly release a large amount of hydrogen in a short time to make up for the lack of hydrogen release in the solid hydrogen storage module 501, ensuring that the fuel cell can obtain sufficient hydrogen supply, maintain stable power output, and ensure the normal operation of the drone under various working conditions. At the same time, the gaseous hydrogen storage module 502 also serves as a backup energy source. When the solid hydrogen storage module 501 fails or the hydrogen storage is insufficient, it can take over in time to provide necessary energy support for the drone, improving the reliability and safety of the drone. When hydrogen is transported from hydrogen storage component 5 to fuel cell component 6, a chemical reaction occurs inside the fuel cell. Hydrogen is decomposed into protons and electrons at the anode. The protons migrate to the cathode through the electrolyte membrane, while the electrons form an electric current through the external circuit, providing power to the drone's motor, control system, and other components. During flight, the internal components of the drone, such as the fuel cell assembly 6, generate a large amount of heat. This heat is first transferred to the heat-conducting plate 4 inside the main body 1 through heat conduction. The heat-conducting plate 4 has good thermal conductivity and can quickly absorb and conduct heat to its bottom. When the internal temperature is detected to be too high or the external ambient temperature is conducive to heat dissipation, the extension or retraction of the first electric push rod 1002 will drive the rotating seat 902 to rotate through the drive seat 1003, the limiting post 903 and the connecting bar 904, thereby changing the heat dissipation angle of the heat sink 15. When the heat sink 15 rotates to a larger heat dissipation angle, its contact area with the air increases, which can more effectively dissipate heat to the surrounding environment. Conversely, when the internal temperature of the drone is low or the external ambient temperature is low and a large amount of heat dissipation is not required, the control system will control the first electric push rod 1002 to rotate the heat sink 15 to a smaller heat dissipation angle to reduce unnecessary heat loss, maintain a suitable internal temperature of the drone and improve energy utilization efficiency. When the drone reaches the target cargo and needs to grab it, it first opens the hatch 3 via the solenoid valve, then activates the electric telescopic rod 701 to retract, causing the lifting plate 702 to move downwards. Once it reaches the appropriate position, the output end of the second electric push rod 708 extends, pushing the connecting plate 709, which is fixedly connected to it, to slide within the groove 707. Since the connecting plate 709 is fixedly connected to one of the gripping claws 705, the gripping claw 705 will move to one side under the guidance of the guide rail. Simultaneously, because one end of the limiting strip 706 is rotatably connected to the outer wall of the gripping claw 705, and the other end is rotatably connected to the connecting plate 704, when the gripping claw 705 moves, it will cause the connecting plate 704 to rotate around the connecting post 703 via the limiting strip 706. The rotation of the connecting plate 704 will then cause the other... One gripper 705 moves in the opposite direction, causing the two gripper 705s to move away from each other and open. When the gripper 705s are open enough to completely surround the target cargo, the electric telescopic rod 701 continues to descend. Then, the output end of the second electric push rod 708 retracts, pulling the connecting plate 709 and the gripper 705 connected to it to move in the opposite direction. Similarly, through the transmission action of the limit bar 706 and the connecting plate 704, the other gripper 705 will also move towards the middle. The two gripper 705s gradually approach and clamp the target cargo. During the clamping process, after successfully grabbing the cargo, the electric telescopic rod 701 extends, driving the lifting plate 702 and the cargo to move upward, grabbing the grabbed cargo into the main body 1. Then, the solenoid valve drives the hatch 3 to close. When it is necessary to remove the cover plate 2, the operation is performed by moving the actuating block 807 on the top of the cover plate 2. The actuating block 807 slides in the actuating groove 806, causing the limiting rod 804 to move away from the slot 801. The movement of the limiting rod 804 will cause the locking block 803 to move inward to the sliding groove 802, while compressing the limiting spring 805. As the actuating block 807 continues to move, the locking block 803 gradually moves out of the slot 801. When the locking block 803 is completely disengaged from the slot 801, the locking connection between the cover plate 2 and the main body 1 is released. At this time, the cover plate 2 can move freely in the vertical direction. After the locking block 803 is disengaged from the slot 801, the cover plate 2 can be gently lifted upward by hand to remove the cover plate 2 from the main body 1.

[0034] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

Claims

1. A high-power, high-payload solid-gas coupled hydrogen-powered unmanned aerial vehicle (UAV), comprising a main body (1), a cover plate (2) fixedly connected to the top of the main body (1), a hatch (3) rotatably connected to the bottom of the main body (1) via a hinge, a heat-conducting plate (4) fixedly connected inside the main body (1), a hydrogen storage component (5) for improving the UAV's endurance and energy utilization efficiency being provided on the top of the heat-conducting plate (4), and a fuel cell component (6) being provided on the top of the heat-conducting plate (4), characterized in that: The bottom of the heat-conducting plate (4) is provided with a grabbing assembly (7) for automatically grabbing goods, the outer wall of the main body (1) is symmetrically provided with a heat dissipation groove (14), a heat dissipation plate (15) is rotationally connected inside the heat dissipation groove (14) at equal intervals through bearings, the top of the main body (1) is provided with a quick release assembly (8) for quickly disassembling and assembling the cover plate (2), and the bottom of the heat-conducting plate (4) is provided with a heat dissipation assembly (9) for adjusting the heat dissipation angle of the heat dissipation plate (15); The heat dissipation assembly (9) comprises fixed plates (901) symmetrically fixedly connected inside the heat dissipation groove (14), three rotating seats (902) rotationally connected at equal intervals on one side of the fixed plates (901) close to each other through bearings, and outer walls of the rotating seats (902) are fixedly connected with outer walls of the heat-conducting plate (4).

2. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The driving assembly (10) comprises a fixed column (1001) fixedly connected to the outer wall of the fixed plate (901), a first electric push rod (1002) rotationally connected to the outer wall of the fixed column (1001) through a bearing, and an output end of the first electric push rod (1002) is fixedly connected with a driving seat (1003).

3. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The grabbing assembly (7) comprises two electric telescopic rods (701) symmetrically fixedly connected to the inner side of the main body (1), an output end of the electric telescopic rod (701) is fixedly connected with a lifting plate (702), the bottom of the lifting plate (702) is fixedly connected with a connecting column (703), the outer wall of the connecting column (703) is rotationally connected with a connecting disc (704) through a bearing, the bottom of the lifting plate (702) is symmetrically connected with a clamping jaw (705) through a sliding connection, the inner side of the connecting disc (704) is symmetrically connected with a limiting strip (706) through a bearing rotation, one end of the limiting strip (706) away from the connecting disc (704) is rotationally connected with the outer wall of the clamping jaw (705) through a bearing, the bottom of the lifting plate (702) is provided with a groove (707), the inner side of the groove (707) is fixedly connected with a second electric push rod (708), the outer wall of one of the clamping jaws (705) is fixedly connected with a connecting plate (709), the outer wall of the connecting plate (709) is connected with the inner side of the groove (707) through a sliding connection, and the output end of the second electric push rod (708) is fixedly connected with the outer wall of the connecting plate (709).

4. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 3, characterized in that: The bottom of the lifting plate (702) is symmetrically fixedly connected with two guide rails, and the top of the clamping jaw (705) is connected with the outer wall of the guide rail through a sliding connection.

5. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The quick release assembly (8) comprises a clamping groove (801) symmetrically arranged in the main body (1), a sliding groove (802) is arranged on one side of the cover plate (2) close to the clamping groove (801), a clamping block (803) is slidably connected to the inner side of the sliding groove (802), a limiting rod (804) is fixedly connected to the side of the clamping block (803) away from the clamping groove (801), a limiting spring (805) is sleeved on the outer side of the limiting rod (804), a pushing groove (806) is symmetrically arranged on the top of the cover plate (2), a pushing block (807) is fixedly connected to the outer wall of the limiting rod (804), the upper end of the pushing block (807) extends to the top of the cover plate (2) and is slidably connected with the inner side of the pushing groove (806), and the clamping block (803) is clamped with the clamping groove (801).

6. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 5, characterized in that: One end of the limiting spring (805) away from the limiting rod (804) is fixedly connected with the inner side of the sliding groove (802), and the other end of the limiting spring (805) is fixedly connected with the outer wall of the limiting rod (804).

7. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The hydrogen storage assembly (5) comprises a solid-state hydrogen storage module (501) and a gaseous hydrogen storage module (502), the solid-state hydrogen storage module (501) adopts a high hydrogen storage density metal hydride advanced solid-state hydrogen storage material, which ensures high energy density and provides stable hydrogen supply, and the gaseous hydrogen storage module (502) adopts a high-pressure hydrogen storage tank to supplement the insufficient of the solid-state hydrogen storage module (501) in rapid hydrogen release and as a backup energy source.

8. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The fuel cell assembly (6) adopts carbon fiber composite material, so that the fuel cell system has higher power density, which is 2-3 times of the same weight power battery system, can provide longer endurance time and greater load capacity.

9. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The outer wall of the main body (1) is equidistantly provided with a plurality of wings (11), the bottom of the main body (1) is symmetrically fixedly connected with a support frame (12), and the outer wall of the support frame (12) is symmetrically fixedly connected with an anti-skid sleeve.

10. The high-power, heavy-load solid-air coupling hydrogen energy unmanned aerial vehicle according to claim 1, characterized in that: The bottom of the main body (1) is symmetrically fixedly connected with two irradiation lamps (13).

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