Hydrogen fuel unmanned aerial vehicle capable of increasing loading capacity of unmanned aerial vehicle

Abstract

The hydrogen fuel unmanned aerial vehicle capable of increasing the loading capacity of the unmanned aerial vehicle comprises an unmanned aerial vehicle body and a loading mechanism, and an air bag assembly is arranged at the top of the unmanned aerial vehicle body; the unmanned aerial vehicle comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a rack top plate, two strip-shaped driving boxes are symmetrically and fixedly arranged on the surface of the rack top plate, extension shells are fixedly connected to the two ends of each strip-shaped driving box, supporting arms are rotatably connected to the surfaces of the extension shells, and driving motors are fixedly arranged at the two ends of each supporting arm. According to the unmanned aerial vehicle, helium with the air bag filling density smaller than that of air is adopted, and the multiple air bags are arranged at the top of the unmanned aerial vehicle, so that the resultant force of the unmanned aerial vehicle in the gravity direction is zero, and the effective loading capacity of the unmanned aerial vehicle is improved on the premise that the weight of the unmanned aerial vehicle is not increased. The design is particularly suitable for the fields of transportation of capital construction materials in mountainous areas, rescue and relief work and the like, and effectively solves the problem that a traditional unmanned aerial vehicle is insufficient in loading capacity due to energy storage limitation.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a hydrogen fuel UAV capable of increasing the load-bearing capacity of the UAV. Background Art

[0002] Drone technology has made significant progress in recent years and is widely used in a variety of fields, including aerial photography, logistics and transportation, agricultural monitoring, and disaster relief. However, due to limitations in weight and energy storage, traditional drones often have limited payload capacity, making it difficult to meet the high-load requirements of some specialized applications.

[0003] In scenarios like transporting infrastructure materials in mountainous areas and performing disaster relief operations, drones are required to carry heavy cargo, such as construction materials and relief supplies. Traditional drones, due to their insufficient payload capacity, are unable to fulfill these tasks. Furthermore, in the tourism sector, as people's expectations for experiential experiences increase, large sightseeing airships, with their unique perspectives and expansive views, are becoming increasingly popular. However, the payload capacity and flexibility of existing sightseeing airships still need to be improved.

[0004] Although some drones with high load-carrying capacity already exist on the market, such as the cargo-carrying multi-rotor drone patented in CN114180043A, most of these drones increase their load-carrying capacity by increasing their size and weight, which not only increases manufacturing costs but also limits their application scenarios. The present invention provides a drone capable of increasing its load-carrying capacity. Summary of the Invention

[0005] The purpose of the present invention is to provide a hydrogen-fueled drone that can increase the drone's load capacity. By adopting airbag components and a special structural design, the airship significantly improves the drone's load capacity and enhances its safety and flexibility. It is particularly suitable for the transportation of infrastructure materials in mountainous areas, disaster relief, and sightseeing tourism.

[0006] To achieve the above-mentioned object, the present invention provides the following technical solution: a hydrogen fuel UAV capable of increasing the load-bearing capacity of the UAV, comprising a UAV body and a carrying mechanism, wherein an airbag assembly is provided on the top of the UAV body; The drone body includes a frame top plate, two strip-shaped drive boxes are symmetrically fixedly arranged on the surface of the frame top plate, both ends of the strip-shaped drive boxes are fixedly connected to an extension shell, the surface of the extension shell is rotatably connected to a support arm, both ends of the support arm are fixedly provided with a drive motor, the rotating shaft of the drive motor is fixedly provided with a blade, and an adjustment mechanism is provided inside the strip-shaped drive box, and the adjustment mechanism is used to adjust the inclination angle of the blade; The airbag assembly includes a first storage shell fixedly connected to the upper surface of the frame top plate, the left and right sides of the first storage shell are rotatably connected to the second storage shell by hinges, the first and second airbags are fixedly arranged inside the first and second storage shells respectively, the inner wall of the first storage shell is fixedly connected to a limiting partition, and a helium storage tank, a first air pump and two second air pumps are arranged below the limiting partition.

[0007] Preferably, the output end of the first air pump is fixedly connected to a first air inflation tube, and the end of the first air inflation tube away from the first air pump extends to the interior of the first airbag; the output end of the second air pump is fixedly connected to a second air inflation tube, and the end of the second air inflation tube away from the second air pump extends to the interior of the second airbag; the input ends of the first air pump and the second air pump are both fixedly connected to an air intake pipe, and the ends of the air intake pipe away from the first air pump and the second air pump are both fixedly connected to the input end of the helium storage tank; an electromagnetic pressure relief valve is fixedly provided on the surface of the air intake pipe.

[0008] Preferably, the first inflation tube and the second inflation tube are both made of rubber hose material, and a gas filling tube is fixedly embedded on the surface of the helium storage tank. The gas filling tube extends to the outside of the first storage shell at one end away from the helium storage tank, and the gas inlet port of the gas filling tube is threadedly connected to the sealing cover.

[0009] Preferably, a rectangular mounting shell is fixedly provided on the lower surface of the top plate of the rack, and a limiting assembly is provided inside the rectangular mounting shell. The limiting assembly is used to limit and fix the two second storage shells. The limiting assembly includes a positioning bar fixedly connected to the lower surface of the second storage shell, and a first dual-axis motor fixedly connected to the inside of the rectangular mounting shell. Both ends of the first dual-axis motor are fixedly connected to a limiting screw rod, and the surface of the limiting screw rod is threadedly connected to a positioning plug block.

[0010] Preferably, a rectangular positioning hole is provided on the surface of the positioning bar, the size of the rectangular positioning hole matches the positioning plug, and limiting guide holes matching the positioning plug are provided on the left and right sides of the rectangular mounting shell, and the positioning plug is slidably connected to the inner wall of the limiting guide hole.

[0011] Preferably, the adjustment mechanism includes a second dual-axis motor fixed to the inner wall of the bar-shaped drive box, and a transmission shaft rotatably connected to the inner wall of the extension shell, both ends of the second dual-axis motor are fixedly connected to the drive rods, and the ends of the two drive rods away from each other are fixedly provided with driving bevel gears, and one end of the transmission shaft is fixedly provided with a driven bevel gear, the position of the driven bevel gear corresponds to the driving bevel gear, and the driving bevel gear is meshed with the driven bevel gear.

[0012] Preferably, a worm is fixedly connected to one end of the transmission shaft away from the driven bevel gear, an adjusting shaft is fixedly connected between two support arms at corresponding positions, the adjusting shaft is rotatably connected between the two extension shells, and two worm wheels are fixedly connected to the surface of the adjusting shaft, the position of the worm wheel corresponds to the worm, and the worm is meshed with the worm wheel.

[0013] Preferably, the carrying mechanism includes a carrying box and two electric telescopic rods symmetrically arranged inside a rectangular mounting shell, the ends of the two electric telescopic rods away from each other are fixedly connected to a limiting support plate, the upper surface of the carrying box is fixedly connected to two suspension brackets, the positions of the suspension brackets correspond to the limiting support plates, and the surfaces of the suspension brackets are provided with rectangular limiting holes matching the limiting support plates, the limiting support plates are inserted and installed inside the rectangular limiting holes, four anti-collision shells are fixedly provided on the surface of the carrying box, a buffer air cushion is provided inside the anti-collision shells, an air cushion controller and a gas generator are provided on the surface of the suspension bracket, and the gas generator is connected to the buffer air cushion through an air duct.

[0014] Preferably, an installation groove is provided on the inner wall of the rectangular limiting hole, a reset spring is fixedly connected to the inner bottom wall of the installation groove, a trigger block is fixedly connected to the top of the reset spring, and a micro switch is fixedly embedded in the inner top wall of the rectangular limiting hole, the position of the micro switch corresponds to the trigger block, and the micro switch is electrically connected to the air cushion controller and the gas generator respectively.

[0015] Preferably, the lower surface of the frame top plate is fixedly connected to a first guide rod, both sides of the suspension bracket are fixedly connected to a first guide block, the first guide block is slidably connected to the surface of the first guide rod, the inner wall of the rectangular mounting shell is fixedly connected to a second guide rod, and both sides of the limiting support plate are fixed to a second guide block, the second guide block is slidably connected to the surface of the second guide rod.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. Enhanced payload capacity: By using airbags filled with helium, which has a lower density than air, and placing multiple airbags on top of the drone, the net force acting against gravity is reduced to zero. This increases the drone's payload capacity without increasing its weight. This design is particularly suitable for transporting infrastructure materials and performing emergency rescue in mountainous areas, effectively addressing the limited payload capacity of traditional drones due to energy storage limitations.

[0017] 2. Flexible Buoyancy Adjustment: Each airbag is equipped with a solenoid valve to control the inflation and discharge of gas, allowing the drone to flexibly adjust its buoyancy based on flight requirements and payload. This helps the drone maintain a stable flight attitude during takeoff, landing, and flight, improving flight safety and reliability. The first and second storage shells on the top of the drone allow the airbags to be stored in the shells after flight, making them easy to store and carry. Furthermore, the drone is equipped with a load capacity monitoring device that monitors the load capacity in real time, providing strong support for the aircraft's safe flight.

[0018] 3. Cargo Platform Safety Protection: The drone features a cargo platform beneath its body, equipped with a crash shell and air cushion. If the platform needs to be detached in an emergency, the air cushion quickly inflates, forming a protective layer on the cargo box, effectively protecting the cargo from damage during landing and minimizing financial losses.

[0019] 4. Drive component inclination adjustment: By setting up an adjustment mechanism, the support arm on the surface of the extension shell can be rotated using the adjustment mechanism to make the drone blades form an inclination angle with the horizontal plane. This design enables the drone to quickly adjust its flight direction, improving its flight flexibility and adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 It is a side structural schematic diagram of the present invention; Figure 3 It is a schematic diagram of the top view of the structure of the present invention; Figure 4 It is a partial bottom view structural diagram of the present invention; Figure 5 This is a schematic diagram of the front cross-section structure of the airbag assembly of the present invention; Figure 6 This is a schematic diagram of the internal structure of the first storage shell of the present invention; Figure 7 This is a schematic diagram of the side cross-section structure of the suspension bracket of the present invention; Figure 8 for Figure 3 Schematic diagram of the enlarged structure at A in the middle; Figure 9 for Figure 3 Schematic diagram of the enlarged structure at B in the middle; In the figure: 1. UAV body; 2. Carrying mechanism; 3. Airbag assembly; 4. Adjustment mechanism; 5. Limit assembly; 101, rack top plate; 102, bar-shaped drive box; 103, extension shell; 104, support arm; 106, drive motor; 107, propeller blade; 108, rectangular mounting shell; 201, carrying box; 202, electric telescopic rod; 203, limit support plate; 204, suspension bracket; 205, rectangular limit hole; 206, anti-collision shell; 207, air cushion controller; 208, mounting slot; 209, return spring; 210, trigger block; 211, micro switch; 212, first guide rod; 213, first guide block; 214, second guide block; 215, second guide rod; 216, air guide tube; 301, first storage shell; 302, second storage shell; 303, first airbag; 304, second airbag; 305, limiting partition; 306, helium storage tank; 307, first air pump; 308, second air pump; 309, first air pipe; 310, second air pipe; 311, air inlet pipe; 312, electromagnetic pressure relief valve; 401, second dual-axis motor; 402, transmission shaft; 403, driving rod; 404, driving bevel gear; 405, driven bevel gear; 406, worm; 407, adjustment shaft; 408, worm gear; 501, positioning bar; 502, first dual-axis motor; 503, limit screw; 504, positioning plug; 505, rectangular positioning hole. DETAILED DESCRIPTION

[0021] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0022] See also Figures 1-9 The present invention provides a technical solution: a hydrogen fuel drone capable of increasing the load-bearing capacity of the drone. The drone body 1 structure is the core part of the entire airship. Its main structure includes a frame top plate 101, a bar-shaped drive box 102, an extension shell 103, a support arm 104, a drive motor 106, blades 107 and a rectangular mounting shell 108.

[0023] The top frame 101 serves as the foundation for the drone 1. Two symmetrical, linear drive boxes 102 are fixedly mounted on its upper surface. Each linear drive box 102 is fixedly connected to an extension shell 103 at both ends. Support arms 104 are rotatably connected to the surface of extension shells 103. Drive motors 106 are fixedly mounted on each end of each support arm 104. Propeller blades 107 are fixed to the rotating shafts of these motors, providing flight propulsion.

[0024] The rectangular mounting shell 108 is fixed to the lower surface of the frame top plate 101 , and is provided with a limiting assembly 5 for limiting and fixing the airbag assembly 3 , as well as components of the carrying mechanism 2 such as the electric telescopic rod 202 .

[0025] It is worth mentioning that the airbag assembly 3 is a key part for improving the load-bearing capacity of the airship. It includes a first storage shell 301, a second storage shell 302, a first airbag 303, a second airbag 304, a helium storage tank 306, a first air pump 307, a second air pump 308, etc. The inner wall of the first storage shell 301 is fixedly connected to a limiting partition 305.

[0026] The first storage shell 301 is fixedly connected to the upper surface of the frame top plate 101, and its left and right sides are rotatably connected to the second storage shell 302 via hinges. The first and second storage shells 301, 302 are respectively fixedly provided with a first airbag 303 and a second airbag 304.

[0027] The first and second airbags 303 and 304 are filled with helium, which has a lower density than air, to provide buoyancy for the airship. A helium storage tank 306 is fixedly attached to the lower inner wall of the first housing 301 to store helium.

[0028] The first and second air pumps 307 and 308 are connected to the first and second air bags 303 and 304, respectively, via first and second air bags 309 and 310, to control the inflation and deflation of the air bags. The electromagnetic pressure relief valve 312, located on the surface of the air intake pipe 311, is used to quickly release the gas within the air bags when needed.

[0029] It is worth noting that the adjustment mechanism 4 is used to adjust the inclination angle of the blade 107, so that the UAV can flexibly adjust the flight direction.

[0030] The second dual-axis motor 401 is fixed to the inner wall of the bar-shaped drive box 102, with a drive rod 403 fixedly connected to each end. A driving bevel gear 404 is fixedly mounted on the end of the drive rod 403 away from the second dual-axis motor 401. A transmission shaft 402 is rotatably connected to the inner wall of the extension housing 103, with a driven bevel gear 405 fixedly mounted on one end, meshing with the driving bevel gear 404.

[0031] Worm 406 is fixedly connected to the end of drive shaft 402, away from driven bevel gear 405, and meshes with worm gear 408 on adjustment shaft 407 between two corresponding support arms 104. Driving second dual-axis motor 401 rotates worm 406, which in turn drives worm gear 408 and adjustment shaft 407, ultimately adjusting the pitch angle of blades 107.

[0032] It's worth noting that the cargo carrier 2 is used to carry and secure cargo, ensuring its safety during flight. A cargo box 201 is used to hold cargo, and two suspension brackets 204 are fixedly connected to its upper surface. The electric telescopic rod 202 is symmetrically positioned within the rectangular mounting housing 108, with its end facing away from the housing 108 fixedly connected to a limit support plate 203. The limit support plate 203 is inserted into a rectangular limit hole 205 on the surface of the suspension bracket 204 to secure the cargo box 201.

[0033] The anti-collision shell 206 is fixed to the surface of the cargo box 201 and is provided with a cushioning air cushion inside. When an emergency occurs and the cargo platform needs to be separated, the cushioning air cushion can be quickly inflated to form a protective layer to protect the cargo from damage.

[0034] An installation groove 208 is formed on the inner wall of the rectangular limiting hole 205 , and a return spring 209 is fixedly connected to the inner bottom wall of the installation groove 208 .

[0035] The air cushion controller 207 and gas generator are mounted on the surface of the suspension bracket 204. The gas generator is connected to the cushion via an air duct 216. In the event of an emergency, the electric telescopic rod 202 can be used to move the limit support plate 203 away from the surface of the suspension bracket 204, thereby discarding the carrier 2 and separating it to save the drone. Simultaneously, the trigger block 210 located inside the suspension bracket 204 moves upward under the action of the return spring 209, contacting the microswitch 211. The air cushion controller 207 then activates the gas generator to rapidly inflate the cushion.

[0036] It is worth noting that the limiting assembly 5 is used to limit and fix the second storage shell 302 to ensure its stability during flight. The positioning bar 501 is fixedly connected to the lower surface of the second storage shell 302 and has a rectangular positioning hole 505 on the surface.

[0037] The first dual-axis motor 502 is fixedly connected to the interior of the rectangular mounting housing 108, with both ends fixedly connected to the limit screw 503. The positioning insert 504 is threaded onto the surface of the limit screw 503. When the first dual-axis motor 502 rotates, the positioning insert 504 moves along the limit screw 503 and inserts into the rectangular positioning hole 505, thereby limiting and fixing the second storage housing 302.

[0038] It should be further explained that the first guide rod 212 and the first guide block 213 are used to ensure the vertical stability of the suspension bracket 204. The first guide rod 212 is fixedly connected to the lower surface of the frame top plate 101, and the first guide blocks 213 are fixedly connected to both sides of the suspension bracket 204 and are slidably connected to the surface of the first guide rod 212.

[0039] The second guide rod 215 and the second guide block 214 are used to ensure the horizontal stability of the position-limiting support plate 203. The second guide rod 215 is fixedly connected to the inner wall of the rectangular mounting housing 108, and the second guide blocks 214 are fixedly connected to both sides of the position-limiting support plate 203 and slidably connected to the surface of the second guide rod 215.

[0040] It's important to note that this drone can implement electronic fence security protection: an electronic fence alarm device is installed on the drone itself or works in conjunction with an electronic fence installed on the ground. This helps ensure that the drone can fly freely within the scenic area during sightseeing tours, while also preventing the drone from flying outside the scenic area, avoiding potential dangers.

[0041] Working Principle: During use, helium is first injected into the first and second airbags 303, 304 via the first and second air pumps 307, 308 to provide the airship with sufficient buoyancy. The drive motor 106 is then activated, rotating the propellers 107 to generate lift and flight power. The inclination angle of the propellers 107 is adjusted via the adjustment mechanism 4, allowing for flexible adjustment of the flight direction. When cargo needs to be carried, the cargo is placed in the cargo box 201, and the limit support plate 203 is inserted into the rectangular limit hole 205 via the electric telescopic rod 202 to secure the cargo box 201. During flight, if an emergency requires separating the cargo platform, the trigger block 210 contacts the microswitch 211, and the air cushion controller 207 activates the gas generator to rapidly inflate the cushioning air cushion, forming a protective layer to protect the cargo from damage. After the flight, the airbags can be stored in the storage shell for easy storage and carrying.

[0042] The standard parts used in the present invention can all be purchased from the market, and special-shaped parts can be customized according to the description in the specification and the drawings. The specific connection methods of each part adopt conventional means such as mature bolts, rivets, welding, etc. in the existing technology. The machinery, parts and equipment all adopt conventional models in the existing technology, and the circuit connection adopts the conventional connection method in the existing technology. It will not be described in detail here. The content not described in detail in this specification belongs to the existing technology known to professional and technical personnel in this field.

[0043] The present invention and its embodiments are described above. This description is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if a person skilled in the art is inspired by this and, without departing from the purpose of the present invention, designs structures and embodiments similar to this technical solution without inventiveness, they shall fall within the scope of protection of the present invention.

Claims

1. A hydrogen fuel UAV capable of increasing the load-bearing capacity of the UAV, comprising a UAV body (1) and a load-bearing mechanism (2), characterized in that: An airbag assembly (3) is provided on the top of the drone body (1); The drone body (1) comprises a frame top plate (101), two strip-shaped drive boxes (102) are symmetrically fixedly provided on the surface of the frame top plate (101), both ends of the strip-shaped drive boxes (102) are fixedly connected to an extension shell (103), a support arm (104) is rotatably connected to the surface of the extension shell (103), both ends of the support arm (104) are fixedly provided with a drive motor (106), and a rotating shaft of the drive motor (106) is fixedly provided with a blade (107); An adjustment mechanism (4) is provided inside the strip-shaped drive box (102), and the adjustment mechanism (4) is used to adjust the inclination angle of the blade (107); The airbag assembly (3) comprises a first storage shell (301) fixedly connected to the upper surface of the frame top plate (101); the left and right sides of the first storage shell (301) are rotatably connected to the second storage shell (302) via hinges; a first airbag (303) and a second airbag (304) are fixedly arranged inside the first storage shell (301) and the second storage shell (302), respectively; the inner wall of the first storage shell (301) is fixedly connected to a limiting partition (305); a helium storage tank (306), a first air pump (307) and two second air pumps (308) are arranged below the limiting partition (305).

2. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 1, characterized in that: The output end of the first air pump (307) is fixedly connected to a first air tube (309), and one end of the first air tube (309) away from the first air pump (307) extends to the interior of the first air bag (303). The output end of the second air pump (308) is fixedly connected to a second air tube (310), and one end of the second air tube (310) away from the second air pump (308) extends to the interior of the second air bag (304). The input ends of the first air pump (307) and the second air pump (308) are both fixedly connected to an air inlet pipe (311), and one end of the air inlet pipe (311) away from the first air pump (307) and the second air pump (308) is fixedly connected to the input end of the helium storage tank (306). An electromagnetic pressure relief valve (312) is fixedly provided on the surface of the air inlet pipe (311).

3. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 2, characterized in that: The first inflation tube (309) and the second inflation tube (310) are both made of rubber hose material. A gas filling tube is fixedly embedded on the surface of the helium storage tank (306). One end of the gas filling tube away from the helium storage tank (306) extends to the outside of the first storage shell (301), and the gas inlet port of the gas filling tube is threadedly connected to the sealing cover.

4. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 3, characterized in that: A rectangular mounting shell (108) is fixedly provided on the lower surface of the frame top plate (101), and a limiting assembly (5) is provided inside the rectangular mounting shell (108). The limiting assembly (5) is used to limit and fix the two second storage shells (302), and the limiting assembly (5) includes a positioning bar (501) fixedly connected to the lower surface of the second storage shell (302), and a first dual-axis motor (502) fixedly connected to the inside of the rectangular mounting shell (108), both ends of the first dual-axis motor (502) are fixedly connected to a limiting screw rod (503), and the surface of the limiting screw rod (503) is threadedly connected to a positioning plug (504).

5. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 4, characterized in that: A rectangular positioning hole (505) is provided on the surface of the positioning strip (501), the size of the rectangular positioning hole (505) matches the positioning plug (504), and limiting guide holes matching the positioning plug (504) are provided on both the left and right sides of the rectangular mounting shell (108), and the positioning plug (504) is slidably connected to the inner wall of the limiting guide hole.

6. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 5, characterized in that: The adjustment mechanism (4) comprises a second dual-axis motor (401) fixed to the inner wall of the bar-shaped drive box (102), and a transmission shaft (402) rotatably connected to the inner wall of the extension shell (103), wherein both ends of the second dual-axis motor (401) are fixedly connected to the drive rods (403), and the ends of the two drive rods (403) that are away from each other are fixedly provided with driving bevel gears (404), and one end of the transmission shaft (402) is fixedly provided with a driven bevel gear (405), and the position of the driven bevel gear (405) corresponds to that of the driving bevel gear (404), and the driving bevel gear (404) is meshed with the driven bevel gear (405).

7. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 6, characterized in that: A worm (406) is fixedly connected to one end of the transmission shaft (402) away from the driven bevel gear (405), and an adjustment shaft (407) is fixedly connected between two support arms (104) at corresponding positions. The adjustment shaft (407) is rotatably connected between the two extension shells (103), and two worm wheels (408) are fixedly connected to the surface of the adjustment shaft (407). The position of the worm wheel (408) corresponds to the worm (406), and the worm (406) is meshed with the worm wheel (408).

8. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 7, characterized in that: The object carrying mechanism (2) comprises an object carrying box (201), and two electric telescopic rods (202) symmetrically arranged inside a rectangular mounting shell (108), the ends of the two electric telescopic rods (202) away from each other are fixedly connected to a limit support plate (203), the upper surface of the object carrying box (201) is fixedly connected to two suspension brackets (204), the positions of the suspension brackets (204) correspond to the limit support plate (203), and the surfaces of the suspension brackets (204) are provided with rectangular limit holes (205) matching the limit support plate (203), and the limit support plate (203) is inserted and installed inside the rectangular limit holes (205), four anti-collision shells (206) are fixedly arranged on the surface of the object carrying box (201), and a buffer air cushion is arranged inside the anti-collision shells (206), and an air cushion controller (207) and a gas generator are arranged on the surface of the suspension bracket (204), and the gas generator is connected to the buffer air cushion through an air guide tube (216).

9. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 8, characterized in that: The inner wall of the rectangular limiting hole (205) is provided with a mounting groove (208), the inner bottom wall of the mounting groove (208) is fixedly connected to a return spring (209), the top end of the return spring (209) is fixedly connected to a trigger block (210), and the inner top wall of the rectangular limiting hole (205) is fixedly embedded with a micro switch (211), the position of the micro switch (211) corresponds to the trigger block (210), and the micro switch (211) is electrically connected to the air cushion controller (207) and the gas generator, respectively.

10. The hydrogen fuel UAV capable of increasing the UAV's load capacity according to claim 9, characterized in that: A first guide rod (212) is fixedly connected to the lower surface of the frame top plate (101), first guide blocks (213) are fixedly connected to both sides of the suspension bracket (204), and the first guide blocks (213) are slidably connected to the surface of the first guide rod (212). A second guide rod (215) is fixedly connected to the inner wall of the rectangular mounting shell (108), and second guide blocks (214) are fixedly connected to both sides of the position-limiting support plate (203), and the second guide blocks (214) are slidably connected to the surface of the second guide rod (215).

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