Electric power inspection multi-rotor unmanned aerial vehicle based on hydrogen energy cell stack

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses an electric power inspection multi-rotor unmanned aerial vehicle based on a hydrogen energy cell stack, the electric power inspection multi-rotor unmanned aerial vehicle comprises a base, an unmanned aerial vehicle main body, a movable hanging bracket and an inspection camera, an isolation frame is arranged at the top of the unmanned aerial vehicle main body, and a cell stack body and a fixing frame used for clamping a hydrogen tank are fixed below the isolation frame. A mounting cavity and a condensation cavity which are communicated are formed in the battery stack body, single batteries are arranged in the mounting cavity, an isolation cylinder is arranged below a top plate of the condensation cavity, a rotating shaft is rotationally mounted in the isolation cylinder and connected with a positioning rod and a shifting wheel through a bevel gear set, and a spiral strip attached to a bottom plate of the condensation cavity is fixed to the lower end of the rotating shaft; the thumbwheel is driven to rotate relative to airflow during flight, the rotating shaft and the spiral strip are driven to rotate through the bevel gear set, condensate water at the bottom of the condensation cavity is continuously scraped and pushed to the water outlet to be discharged, condensate water is prevented from being left and frozen, and smooth exhaust of the cell stack and operation reliability in a low-temperature environment are ensured.

Description

A multi-rotor drone for power line inspection based on hydrogen fuel cell stack Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a multi-rotor UAV for power inspection based on a hydrogen fuel cell stack. Background Technology

[0002] In recent years, with the continuous maturation of hydrogen energy technology, multi-rotor drones based on hydrogen fuel cell stacks have shown significant advantages in the field of power line inspection. With the high energy density, long endurance, and environmentally friendly and pollution-free characteristics of hydrogen fuel cell systems, they can effectively overcome the inherent limitations of traditional lithium battery drones, such as short endurance and long charging cycles. They meet the needs of long-distance and large-scale refined inspection of power transmission lines and are gradually becoming an important technical equipment in the field of energy infrastructure operation and maintenance.

[0003] The aforementioned and existing related technologies have the following drawbacks: During the operation of the hydrogen fuel cell stack of existing rotary-wing UAVs, the water vapor produced by the electrochemical reaction is condensed into liquid water, which is difficult to completely discharge in the exhaust pipe, resulting in a certain degree of residual accumulation. When the UAV operates in a low-temperature environment, this residual condensate is very easy to freeze, thereby blocking the gas flow channel and drainage structure, leading to poor gas supply to the fuel cell stack, power reduction, or even system shutdown, which seriously affects the UAV's subsequent endurance and operational reliability in cold regions or winter conditions. Summary of the Invention

[0004] The technical problem to be solved by this invention is that the existing technology has the disadvantage that the condensate produced by the hydrogen fuel cell stack of the drone will remain, and it is easy to freeze and block the gas passage in the low temperature environment, thus affecting the drone's subsequent flight time. To this end, we propose a multi-rotor drone for power inspection based on hydrogen fuel cell stack.

[0005] To achieve the above objectives, this application adopts the following technical solution: a multi-rotor UAV for power inspection based on a hydrogen fuel cell stack, comprising a base and a UAV body fixedly connected to the top of the base, a movable hanger fixedly connected to the lower end of the base, an inspection camera rotatably mounted at the bottom end of the movable hanger, several rotors evenly spaced and fixedly connected to the four sides of the UAV body, an isolation frame fixedly connected to the top of the UAV body, a fuel cell stack body and a fixed frame fixedly connected to the upper end of the top plate of the UAV body at the lower end of the isolation frame, a hydrogen tank movablely fitted inside the fixed frame, a gas guide valve pipe fixedly connected to the outlet end of the hydrogen tank, and the gas guide valve pipe connected to the gas inlet end of the fuel cell stack body;

[0006] The battery stack body has an interconnected mounting cavity and a condensation cavity inside. A battery cell is fixedly installed in the mounting cavity. An isolation cylinder is fixedly connected to the lower end of the top plate of the condensation cavity. A rotating shaft is rotatably installed on the top plate of the condensation cavity inside the isolation cylinder. A bevel gear set is fixedly connected to the outer wall of the rotating shaft inside the isolation cylinder. The lower end of the rotating shaft extends through to the lower end of the bottom plate of the isolation cylinder and is fixedly connected to a spiral strip. The lower end of the spiral strip is set to fit against the bottom plate of the condensation cavity. A positioning rod is fixedly connected to the other end of the bevel gear set. The end of the positioning rod extends through to the outside of the side wall of the battery stack body and is fixedly connected to a dial wheel. An arc-shaped cover is fixedly connected to the side wall of the battery stack body outside the dial wheel.

[0007] Preferably, the arc-shaped cover has a crescent-shaped structure, with the opening of the arc-shaped cover facing downwards, and the bottom port of the arc-shaped cover is flush with the radial horizontal axis of the dial.

[0008] Preferably, a vent is provided on one side of the mounting cavity, and a fan is fixedly connected to the inner wall of the vent. The fan is electrically connected to the microcontroller inside the drone body.

[0009] Preferably, a condenser plate is fixedly connected to the lower end of the top plate of the condensation chamber, and the condenser plate is sleeved around the outside of the isolation cylinder. A drain and exhaust port is opened at the center of the spiral strip on the bottom plate of the condensation chamber. A drain and exhaust pipe is fixedly connected to the bottom of the battery stack body below the drain and exhaust port. The lower end of the drain and exhaust pipe extends into the interior of the UAV body and then passes through the bottom of its bottom plate. The bottom port of the drain and exhaust pipe is located on the outside of one end of the back plate of the inspection camera.

[0010] Preferably, several detachable brackets are fixedly connected at even intervals along the edge of the top plate of the drone body, and a protective baffle is fixedly connected to the top of the detachable brackets, with the lower end of the protective baffle attached to the top of the isolation frame.

[0011] Preferably, a moisture-absorbing cotton cylinder is fixedly connected to the outer wall of the rotating shaft at the lower end of the isolation cylinder, and an auxiliary component is fixedly connected to the outer wall of the rotating shaft at the upper end of the moisture-absorbing cotton cylinder. The auxiliary component is used to squeeze the moisture-absorbing cotton cylinder.

[0012] Preferably, the auxiliary component includes a hanging rod fixedly connected to the outer wall of the upper rotating shaft of the absorbent cotton tube, a sleeve fixedly connected to the end of the hanging rod, a movable rod movably fitted inside the sleeve, a U-shaped frame fixedly connected to the bottom of the movable rod, a cam movably connected between the inner walls of the bottom of the U-shaped frame, and several connecting rods fixedly connected to the side wall of the movable rod at the upper end of the U-shaped frame, each connecting rod having a compression ring fixedly connected to its end, the compression ring being fitted around the outer wall of the absorbent cotton tube.

[0013] Preferably, the cam is located in a gap between adjacent sides of the inner and outer rings of the spiral strip, the lower end of the cam is fitted to the bottom plate of the condensation chamber, and the inner diameter of the extrusion ring is smaller than the outer diameter of the absorbent cotton tube.

[0014] Preferably, the fixing frame has a U-shaped structure. Elastic straps are evenly spaced and fixedly connected to the outer wall of the top port of the fixing frame. A slot is opened on the side plate of one end of the fixing frame. Support plates are fixedly connected to the top two sides of the fixing frame away from the slot. A positioning shaft is rotatably connected between the side walls at the top of the support plates. A lightweight flip plate is fixedly connected to the side wall of one end of the positioning shaft. A support plate is fixedly connected to the outer wall of the bottom of the fixing frame end of the lightweight flip plate. The lower end of the lightweight flip plate is set to fit against the top surface of the support plate.

[0015] Preferably, a crossbar is fixedly connected to the side walls at both ends of the bottom of the lightweight flip plate, and a limit suspension rod is fixedly connected to the outer wall of the fixed frame above the crossbar. A counterweight cylinder is movably sleeved on the outer wall of the end of the limit suspension rod. An installation groove is opened at the top of the support plate corresponding to the counterweight cylinder. The lower end of the counterweight cylinder is suspended in the installation groove, and an electromagnet is fixedly connected to the bottom plate of the installation groove.

[0016] The technical effects and advantages of this invention are as follows:

[0017] In this invention, a connected mounting cavity and a condensation cavity are set within the battery stack body. A transmission and drainage mechanism consisting of a dial wheel, a positioning rod, a bevel gear set, a rotating shaft, and a spiral strip is arranged in the condensation cavity. The dial wheel is exposed to the airflow outside the UAV, so that during the flight of the UAV, the relative airflow can naturally drive the dial wheel to rotate. In turn, the bevel gear set drives the rotating shaft and spiral strip to rotate continuously. The lower end of the spiral strip is set to fit against the bottom plate of the condensation cavity, which can actively and continuously scrape away the condensate accumulated in the condensation cavity and push it to the drainage and exhaust port for discharge, just like an auger. This achieves a passive drainage function without additional power consumption. This structure effectively avoids the long-term retention of condensate at the bottom of the cavity, fundamentally solving the problem of residual condensate freezing and blocking the gas flow channel and drainage structure in a low-temperature environment, ensuring smooth exhaust of the battery stack and stable power output. Attached Figure Description

[0018] The disclosure of this invention is illustrated with reference to the accompanying drawings. It should be understood that the drawings are for illustrative purposes only and are not intended to limit the scope of protection of this invention. In the drawings, the same reference numerals are used to refer to the same parts:

[0019] Figure 1 is a schematic diagram of the overall structure of a multi-rotor UAV for power inspection based on a hydrogen fuel cell stack according to the present invention.

[0020] Figure 2 is a schematic diagram of the battery stack body, fixing frame and hydrogen tank installation structure of a power inspection multi-rotor UAV based on hydrogen energy battery stack according to the present invention.

[0021] Figure 3 is a schematic diagram of the battery stack body structure of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0022] Figure 4 is a partial cross-sectional view of the battery stack body of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0023] Figure 5 is a schematic diagram of the installation structure of the rotating shaft, spiral strip, and dial of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0024] Figure 6 is a schematic diagram of the auxiliary components and isolation cylinder installation structure of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0025] Figure 7 is a schematic diagram of the detachable support structure of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0026] Figure 8 is a schematic diagram of the mounting frame and hydrogen tank installation structure of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0027] Figure 9 is a schematic diagram of the fixed frame structure of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0028] Figure 10 is an enlarged structural schematic diagram of point A in Figure 9 of a power inspection multi-rotor UAV based on a hydrogen energy battery stack according to the present invention.

[0029] In the diagram: 1. Base; 11. Movable hanger; 12. Inspection camera; 2. Drone body; 21. Rotor; 22. Detachable bracket; 23. Protective baffle; 3. Isolation frame; 4. Battery stack body; 41. Mounting cavity; 42. Battery cell; 43. Condensation cavity; 44. Isolation cylinder; 45. Rotating shaft; 451. Bevel gear set; 452. Moisture-absorbing cotton tube; 46. Spiral strip; 47. Positioning rod; 48. Dial wheel; 49. Auxiliary Components; 491. Hanging rod; 492. Sleeve; 493. Moving rod; 494. U-shaped frame; 495. Cam; 496. Connecting rod; 497. Extrusion ring; 5. Fixing frame; 51. Support plate; 52. Positioning shaft; 53. Lightweight flip plate; 531. Crossbar; 54. Support plate; 55. Limiting suspension rod; 56. Counterweight cylinder; 57. Electromagnet; 6. Hydrogen tank; 7. Gas valve pipe; 8. Fan; 9. Arc-shaped cover; 10. Condenser fin. Detailed Implementation

[0030] It is readily understood that, based on the technical solution of this invention, those skilled in the art can propose various interchangeable structural methods and implementations without altering the essential spirit of the invention. Therefore, the following detailed embodiments and accompanying drawings are merely illustrative examples of the technical solution of this invention and should not be considered as the entirety of the invention or as limitations or restrictions on the technical solution of this invention.

[0031] Referring to Figures 1-6, the present invention provides a technical solution: a multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack. This UAV is mainly used for power line inspection and has the ability to have long flight time and adapt to complex climate environments.

[0032] The drone mainly consists of a base 1, a drone body 2, a power system, a hydrogen energy supply system, and a battery stack management system. The base 1 serves as the supporting foundation for the drone, with the drone body 2 fixedly connected to its top. Landing frames are welded to both ends of the bottom of the base 1. The drone body 2 houses electronic components including, but not limited to, a flight controller (microcontroller), motor driver, transformer, and battery. A movable hanger 11 is fixedly connected to the lower end of the base 1, suspended between the landing frames. An inspection camera 12 is rotatably mounted at the bottom end of the movable hanger 11. The movable hanger 11 allows the inspection camera 12 to rotate at multiple angles for comprehensive imaging and monitoring of various parts of the power line.

[0033] Several rotors 21 are evenly spaced and fixedly connected to the four sides of the main body 2 of the drone. The rotors 21 are driven by motors to provide lift and flight power for the drone. An isolation frame 3 is fixedly connected to the top of the main body 2 of the drone. The isolation frame 3 is used to support and isolate the core energy components. At the top of the top plate of the main body 2 of the drone, which is below the isolation frame 3, a battery stack body 4 and a fixing frame 5 are fixedly connected. The fixing frame 5 is used to fix a hydrogen tank 6. The hydrogen tank 6 stores high-pressure hydrogen. A gas guide valve pipe 7 is fixedly connected to the outlet end of the hydrogen tank 6. The gas guide valve pipe 7 is connected to the gas inlet end of the battery stack body 4 to provide the hydrogen fuel required for the reaction of the battery stack.

[0034] To protect the hydrogen energy equipment above, several detachable brackets 22 are evenly spaced and fixedly connected to the top edge of the top plate of the drone body 2. A protective baffle 23 is fixedly connected to the top of the detachable bracket 22. The lower end of the protective baffle 23 is attached to the top of the isolation frame 3 to form a physical barrier to prevent foreign objects from hitting or damaging the hydrogen tank 6 and the battery stack.

[0035] As shown in Figures 1 and 7, the detachable bracket 22 includes structures such as threaded protrusions, columns, and threaded sleeves. The threaded protrusions are uniformly welded and fixed to the upper edge of the top plate of the UAV body 2. The top of the column is welded and fixed to the protective baffle 23. The threaded sleeve is movable on the outer wall of the column. After the lower end of the column overlaps the top of the threaded protrusion, the threaded sleeve is tightened. The threaded sleeve can lock the lower end of the column and the threaded protrusion using the internal thread.

[0036] As shown in Figures 2-6, the battery stack body 4 has a connected mounting cavity 41 and a condensation cavity 43 inside. The battery cell 42 is fixedly installed in the mounting cavity 41 (the battery cell 42 is composed of end plates, current collectors and other structures, which is existing technology, and can be referred to in existing technology CN115498210B). This is the core place where the hydrogen fuel cell generates electricity through electrochemical reaction. Hydrogen and oxygen (or air) react in the battery cell 42 to generate electricity and water vapor.

[0037] The condensing chamber 43 is used to receive and process the water vapor and unreacted gas produced by the reaction. An isolation cylinder 44 is fixedly connected to the lower end of the top plate of the condensing chamber 43. The isolation cylinder 44 partially isolates the upper space of the condensing chamber 43, forming a protective cavity for the transmission mechanism. A rotating shaft 45 is rotatably installed on the top plate of the condensing chamber 43 inside the isolation cylinder 44. The rotating shaft 45 is mounted on the top plate through bearings to ensure its rotational flexibility.

[0038] A bevel gear set 451 is fixedly connected to the outer wall of the rotating shaft 45 inside the isolation cylinder 44. The bevel gear set 451 is used to change the direction of power transmission. The lower end of the rotating shaft 45 extends through to the lower end of the bottom plate of the isolation cylinder 44 and is fixedly connected to a spiral strip 46. The spiral strip 46 extends in a spiral shape, and its lower end is set to fit against the bottom plate of the condensation chamber 43. When the rotating shaft 45 rotates, the spiral strip 46 rotates accordingly, scraping away the accumulated liquid at the bottom of the condensation chamber 43 like an auger and pushing it to the drain port at the center.

[0039] To drive the shaft 45 to rotate, a positioning rod 47 is fixedly connected to the other end (i.e., the output end) of the bevel gear set 451. The positioning rod 47 is horizontally positioned, and its end extends through to the outside of the side wall of the battery stack body 4 and is fixedly connected to a dial wheel 48. The dial wheel 48 is exposed to the external airflow of the drone body 2. When the drone is flying, the relative airflow blows the dial wheel 48, causing it to rotate. The rotation of the dial wheel 48 is transmitted to the bevel gear set 451 through the positioning rod 47. The bevel gear set 451 drives the shaft 45 and the spiral strip 46 to rotate, thereby realizing a passive drainage function without the need for an additional motor drive, saving energy.

[0040] In order to protect the dial wheel 48 and guide the airflow, an arc-shaped cover 9 is fixedly connected to the side wall of the battery stack body 4 outside the dial wheel 48. The arc-shaped cover 9 has a crescent-shaped structure with its opening facing downwards, and the bottom port of the arc-shaped cover 9 is flush with the radial horizontal axis of the dial wheel 48. This structure can prevent foreign objects above from interfering with the rotation of the dial wheel 48, and can also use the oncoming airflow to more effectively drive the dial wheel 48 to rotate.

[0041] To enhance the condensation effect, a vent is provided on one side of the mounting cavity 41. A fan 8 is fixedly connected to the inner wall of the vent. The fan 8 is electrically connected to the microcontroller inside the drone body 2. The fan 8 is independently powered and controlled by the microcontroller and other components inside the drone body 2. When the fan 8 is working, it forces the airflow to circulate inside the battery stack, accelerating the introduction of the humid and hot gas generated by the reaction into the condensation cavity 43, thereby improving the condensation efficiency. At the same time, after the battery stack body 4 finishes generating electricity, it can also provide a continuous airflow to quickly blow the inside of the battery stack body 4, drying off its moisture and residual water droplets, and preventing it from freezing at low temperatures and affecting the use of the equipment.

[0042] A condenser plate 10 is fixedly connected to the lower end of the top plate of the condensation chamber 43. The condenser plate 10 is wrapped around the outside of the isolation cylinder 44, increasing the heat exchange area and accelerating the condensation of water vapor. A drain and exhaust port is opened on the bottom plate of the condensation chamber 43 at the center of the spiral strip 46. A drain and exhaust pipe is fixedly connected to the bottom of the battery stack body 4 at the lower end of the drain and exhaust port. The lower end of the drain and exhaust pipe extends into the interior of the drone body 2 and then exits from the bottom of its bottom plate. When the drone body 2 is working, it generates a certain amount of heat. The ambient temperature is relatively high. The heat is used to relatively insulate the drain and exhaust pipe, preventing the condensate inside the drain and exhaust pipe from freezing due to low temperature, and ensuring that the gas and condensate can always be discharged smoothly. The bottom port of the drain and exhaust pipe is located on the outer side of one end of the back plate of the inspection camera 12, away from the lens of the inspection camera 12. By setting the drain port here, the positional deviation between the lens of the inspection camera 12 and the drain port can be used to prevent the condensate from being blown by the airflow and sprayed onto the lens of the inspection camera 12 when it is discharged, thus ensuring the clarity of the lens of the inspection camera 12.

[0043] To further remove moisture from the gas, a moisture-absorbing cotton cylinder 452 is fixedly connected to the outer wall of the rotating shaft 45 at the lower end of the isolation cylinder 44. The moisture-absorbing cotton cylinder 452 is made of highly absorbent material and is used to absorb residual moisture in the airflow. An auxiliary component 49 is fixedly connected to the outer wall of the rotating shaft 45 at the upper end of the moisture-absorbing cotton cylinder 452. The auxiliary component 49 is used to squeeze the moisture-absorbing cotton cylinder 452 to squeeze out the absorbed moisture.

[0044] The auxiliary component 49 includes a hanging rod 491 fixedly connected to the outer wall of the upper rotating shaft 45 of the absorbent cotton cylinder 452. A sleeve 492 is fixedly connected to the end of the hanging rod 491. A movable rod 493 is movably fitted inside the sleeve 492. The movable rod 493 can slide up and down inside the sleeve 492. A U-shaped frame 494 is fixedly connected to the bottom of the movable rod 493. A cam 495 is movably connected between the inner walls of the bottom of the U-shaped frame 494. The cam 495 is located in a gap between the adjacent sides of the inner and outer rings of the spiral strip 46, and the lower end of the cam 495 is set to fit against the bottom plate of the condensation chamber 43. Several connecting rods 496 are fixedly connected to the side wall of the movable rod 493 at the upper end of the U-shaped frame 494. Each connecting rod 496 is fixedly connected to a compression ring 497 at its end. The compression ring 497 is sleeved on the outer wall of the absorbent cotton cylinder 452, and the inner diameter of the compression ring 497 is smaller than the outer diameter of the absorbent cotton cylinder 452.

[0045] Specifically, the lower half of the dial 48 is exposed to the external airflow of the drone body 2. When the drone is flying, the relative airflow blows the dial 48 to make it rotate. The rotation of the dial 48 is transmitted to the bevel gear set 451 through the positioning rod 47. The bevel gear set 451 drives the rotating shaft 45 and the spiral strip 46 to rotate. When the spiral strip 46 rotates, the cam 495 is directly driven to rotate by the friction of the base plate. Due to the height difference of the profile of the cam 495, when it rotates, it will push up the U-shaped frame 494, which in turn drives the compression ring 497 to move up and down through the moving rod 493 and the hanging rod 491.

[0046] Therefore, when the squeezing ring 497 moves downward, it tightly squeezes the absorbent cotton cylinder 452, squeezing out the absorbed moisture; when the squeezing ring 497 moves upward, the absorbent cotton cylinder 452 returns to its fluffy state, thus continuing to absorb moisture from the airflow. The periodic squeezing action of the squeezing ring 497 enables the absorbent cotton cylinder 452 to continuously dehumidify water vapor, scraping away the accumulated liquid at the bottom of the condensation chamber 43 like an auger and pushing it to the drain outlet at the center. This allows the water vapor generated by the hydrogen fuel cell stack to be quickly and centrally discharged after condensation, preventing residual condensate from freezing the drain outlet.

[0047] As shown in Figures 1-2 and 8-10, to facilitate the replacement and fixation of the hydrogen tank 6, the fixing frame 5 has a U-shaped structure. Elastic straps are evenly spaced and fixedly connected to the outer wall of the top port of the fixing frame 5 for initially holding the hydrogen tank 6. A latch is provided on the side plate at one end of the fixing frame 5 for securing the end of the hydrogen tank 6. Support plates 51 are fixedly connected to the top two sides of the fixing frame 5 away from the latch. A positioning shaft 52 is rotatably connected between the side walls at the top of the support plates 51. A lightweight flap 53 is fixedly connected to the side wall at one end of the positioning shaft 52. A support plate 54 is fixedly connected to the outer wall at the bottom of the fixing frame 5 at the lower end of the lightweight flap 53. The lower end of the lightweight flap 53 is set to fit against the top surface of the support plate 54 to form a limiting block on the tail end of the hydrogen tank 6.

[0048] To achieve automatic locking, crossbars 531 are fixedly connected to the side walls at both ends of the bottom of the lightweight flap 53. A limit suspension rod 55 is fixedly connected to the outer wall of the end of the fixing frame 5 above the crossbars 531. A counterweight cylinder 56 is movably sleeved on the outer wall of the end of the limit suspension rod 55. The weight of the counterweight cylinder 56 is greater than the weight of the lightweight flap 53. An installation groove is opened at the top of the support plate 54 corresponding to the counterweight cylinder 56. The lower end of the counterweight cylinder 56 is suspended in the installation groove. An electromagnet 57 is fixedly connected to the bottom plate of the installation groove. The electromagnet 57 is electrically connected to the microcontroller inside the UAV body 2.

[0049] When it is necessary to lock the hydrogen tank 6, after the hydrogen tank 6 clamp is above the fixing frame 5, the end of the lightweight flap 53 is locked in the slot. At this time, the drone is not started, the electromagnet 57 is not energized and loses its magnetic force. Lower the lightweight flap 53 so that the crossbar 531 slides under the counterweight cylinder 56. Manually push the lightweight flap 53 to fit against the side wall of the end of the fixing frame 5. The crossbar 531 pushes the counterweight cylinder 56 upward until the crossbar 531 moves from one side of the counterweight cylinder 56 to the side of the fixing frame 5. The counterweight cylinder 56 is then under the influence of gravity. Under the action of the action, it falls into the mounting groove and presses against the crossbar 531 of the lightweight flap 53 at an angle to one side (restricting the lightweight flap 53 from flipping up), thereby locking the lightweight flap 53 in the closed position to firmly press against the hydrogen tank 6. In order to ensure the necessary stability of the hydrogen tank 6 when the drone is flying, the electromagnet 57 is synchronously energized when the drone starts to obtain magnetic force, which firmly attracts and fixes the counterweight cylinder 56 in the mounting groove, thereby preventing the crossbar 531 from moving in the opposite direction and causing the lightweight flap 53 to flip up, thus completing the stable locking of the hydrogen tank 6.

[0050] When it is necessary to replace the hydrogen tank 6, the drone stops and the electromagnet 57 is de-energized. The electromagnet 57 loses its strong magnetic force, and the operator only needs to reverse the horizontal bar 531 to make it lift the counterweight cylinder 56 upward, releasing the constraint on the lightweight flip plate 53. The operator can then easily flip open the lightweight flip plate 53 to take out the hydrogen tank 6, making the operation convenient.

[0051] The technical scope of this invention is not limited to the content described above. Those skilled in the art can make various modifications and variations to the above embodiments without departing from the technical concept of this invention, and all such modifications and variations should fall within the protection scope of this invention.

Claims

1. A multi-rotor unmanned aerial vehicle (UAV) for power line inspection based on a hydrogen fuel cell stack, characterized in that, The system includes a base and a drone body fixedly connected to the top of the base. A movable hanger is fixedly connected to the lower end of the base, and a patrol camera is rotatably mounted at the bottom end of the movable hanger. Several rotors are evenly spaced and fixedly connected to the four side walls of the drone body. An isolation frame is fixedly connected to the top of the drone body. A battery stack body and a fixed frame are fixedly connected to the upper end of the top plate of the drone body below the isolation frame. A hydrogen tank is movably fitted inside the fixed frame, and a gas guide valve pipe is fixedly connected to the outlet end of the hydrogen tank. The gas guide valve pipe is connected to the gas inlet end of the battery stack body. The battery stack body has interconnected... The mounting cavity and the condensation cavity are provided. A battery cell is fixedly installed in the mounting cavity. An isolation cylinder is fixedly connected to the lower end of the top plate of the condensation cavity. A rotating shaft is rotatably installed on the top plate of the condensation cavity inside the isolation cylinder. A bevel gear set is fixedly connected to the outer wall of the rotating shaft inside the isolation cylinder. The lower end of the rotating shaft extends through to the lower end of the bottom plate of the isolation cylinder and is fixedly connected to a spiral strip. The lower end of the spiral strip is set to fit against the bottom plate of the condensation cavity. A positioning rod is fixedly connected to the other end of the bevel gear set. The end of the positioning rod extends movably through to the outside of the side wall of the battery stack body and is fixedly connected to a dial wheel. An arc-shaped cover is fixedly connected to the side wall of the battery stack body outside the dial wheel.

2. The multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: The arc-shaped cover has a crescent-shaped structure with its opening facing downwards, and the bottom port of the arc-shaped cover is flush with the radial horizontal axis of the dial.

3. The multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: A vent is provided on one side of the mounting cavity, and a fan is fixedly connected to the inner wall of the vent. The fan is electrically connected to the microcontroller inside the drone body.

4. The multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: A condenser plate is fixedly connected to the lower end of the top plate of the condensing chamber. The condenser plate is sleeved around the outside of the isolation cylinder. A drain and exhaust port is opened at the center of the spiral strip on the bottom plate of the condensing chamber. A drain and exhaust pipe is fixedly connected to the bottom of the battery stack body below the drain and exhaust port. The lower end of the drain and exhaust pipe extends into the interior of the UAV body and then passes through the bottom of its bottom plate. The bottom port of the drain and exhaust pipe is located on the outside of one end of the back plate of the inspection camera.

5. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: Several detachable brackets are fixedly connected at even intervals along the edge of the top plate of the drone body. A protective baffle is fixedly connected to the top of the detachable brackets, and the lower end of the protective baffle is attached to the top of the isolation frame.

6. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: A moisture-absorbing cotton tube is fixedly connected to the outer wall of the rotating shaft at the lower end of the isolation cylinder, and an auxiliary component is fixedly connected to the outer wall of the rotating shaft at the upper end of the moisture-absorbing cotton tube. The auxiliary component is used to squeeze the moisture-absorbing cotton tube.

7. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 6, characterized in that: The auxiliary component includes a hanging rod fixedly connected to the outer wall of the upper rotating shaft of the absorbent cotton tube. A sleeve is fixedly connected to the end of the hanging rod. A movable rod is movably fitted inside the sleeve. A U-shaped frame is fixedly connected to the bottom of the movable rod. A cam is movably connected between the inner walls of the bottom of the U-shaped frame. Several connecting rods are fixedly connected to the side wall of the movable rod at the upper end of the U-shaped frame. Each connecting rod has a compression ring fixedly connected to its end. The compression ring is fitted around the outer wall of the absorbent cotton tube.

8. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 7, characterized in that: The cam is located in a gap between adjacent sides of the inner and outer rings of the spiral strip. The lower end of the cam is fitted to the bottom plate of the condensation chamber, and the inner diameter of the compression ring is smaller than the outer diameter of the absorbent cotton tube.

9. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 1, characterized in that: The fixing frame has a U-shaped structure. Elastic straps are evenly spaced and fixedly connected to the outer wall of the top port of the fixing frame. A slot is opened on the side plate at one end of the fixing frame. Support plates are fixedly connected to the top two sides of the fixing frame away from the slot. A positioning shaft is rotatably connected between the side walls at the top of the support plates. A lightweight flip plate is fixedly connected to the side wall at one end of the positioning shaft. A support plate is fixedly connected to the outer wall at the bottom of the fixing frame end of the lightweight flip plate. The lower end of the lightweight flip plate is set to fit against the top surface of the support plate.

10. A multi-rotor UAV for power line inspection based on a hydrogen fuel cell stack according to claim 9, characterized in that: A crossbar is fixedly connected to the side walls at both ends of the bottom of the lightweight flip plate. A limiting suspension rod is fixedly connected to the outer wall of the fixed frame above the crossbar. A counterweight cylinder is movably sleeved on the outer wall of the end of the limiting suspension rod. An installation groove is opened at the top of the support plate corresponding to the counterweight cylinder. The lower end of the counterweight cylinder is suspended in the installation groove. An electromagnet is fixedly connected to the bottom plate of the installation groove.

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